diff --git a/tank_design/CMakeLists.txt b/tank_design/CMakeLists.txt
index e4918e7444ef4c4d1a92ed2c7765eccd2d34360b..de33827efac3873b97ac30b0c9dced5a970c2c03 100644
--- a/tank_design/CMakeLists.txt
+++ b/tank_design/CMakeLists.txt
@@ -43,6 +43,9 @@ list(APPEND PYINSTALLER_OPTIONS "--add-data=${CMAKE_CURRENT_LIST_DIR}/src${DATA_
list(APPEND PYINSTALLER_OPTIONS "--collect-all=matplotlib")
list(APPEND PYINSTALLER_OPTIONS "--collect-all=pycoordinatesystemconversion")
+list(APPEND PYINSTALLER_OPTIONS "--collect-all=pyunitconversion")
+list(APPEND PYINSTALLER_OPTIONS "--collect-all=pyaircraftgeometry2")
+list(APPEND PYINSTALLER_OPTIONS "--collect-all=pyaixml")
# Add the target which compiles the executable using pyinstaller
add_custom_target(${MODULE_NAME} ALL
diff --git a/tank_design/src/datapostprocessing.py b/tank_design/src/datapostprocessing.py
index 597da574ba1202144f41b515c637d980148683cc..a60425f3307990b5492f6c33af8fdfa0dbe3613a 100644
--- a/tank_design/src/datapostprocessing.py
+++ b/tank_design/src/datapostprocessing.py
@@ -1,525 +1,529 @@
-"""Module providing functions for data postprocessing."""
-# Import standard modules.
-
-# Import own modules.
-from datapostprocessingmodule import method_data_postprocessing
-from datapostprocessingmodule import write_key_data_to_aircraft_exchange_file
-from datapostprocessingmodule import prepare_element_tree_for_module_key_parameter
-
-
-def data_postprocessing(paths_and_names, routing_dict, data_dict, runtime_output):
- """Perform data postprocessing and write data to an aircraft exchange file.
-
- This function is responsible for data postprocessing that involves the following steps:
- (1) Data preparation: The module manager prepares a list containing all paths to the key parameters that must
- be written to the aircraft exchange file.
- (2) Write data to the aircraft exchange file: The results of the module execution are passed on to the function
- responsible for properly writing the data to the aircraft exchange file.
- (3) Method-specific data postprocessing: User-defined method-specific postprocessing is conducted as needed.
-
- :param dict paths_and_names: Dictionary containing system paths and ElementTrees
- :param dict routing_dict: Dictionary containing routing parameters
- :param dict data_dict: Dictionary containing the result of the module execution (direct operating cost estimation)
- :param logging.Logger runtime_output: Logging object used for capturing log messages in the module
- :return: None
- """
-
- """Data preparation."""
- # Changes to this list are the sole responsibility of the module manager!
- paths_to_key_parameters_list = [
- './component_design/tank/position/x',
- './component_design/tank/position/y',
- './component_design/tank/position/z',
- './component_design/tank/mass_properties/mass',
- './component_design/tank/mass_properties/inertia/j_xx',
- './component_design/tank/mass_properties/inertia/j_yy',
- './component_design/tank/mass_properties/inertia/j_zz',
- './component_design/tank/mass_properties/inertia/j_xy',
- './component_design/tank/mass_properties/inertia/j_xz',
- './component_design/tank/mass_properties/inertia/j_yx',
- './component_design/tank/mass_properties/inertia/j_yz',
- './component_design/tank/mass_properties/inertia/j_zx',
- './component_design/tank/mass_properties/inertia/j_zy',
- './component_design/tank/mass_properties/center_of_gravity/x',
- './component_design/tank/mass_properties/center_of_gravity/y',
- './component_design/tank/mass_properties/center_of_gravity/z',
- './component_design/tank/specific/additional_fuselage_length',
- './component_design/tank/specific/tank[@ID="0"]/name',
- './component_design/tank/specific/tank[@ID="0"]/designator',
- './component_design/tank/specific/tank[@ID="0"]/position/x',
- './component_design/tank/specific/tank[@ID="0"]/position/y',
- './component_design/tank/specific/tank[@ID="0"]/position/z',
- './component_design/tank/specific/tank[@ID="0"]/direction/x',
- './component_design/tank/specific/tank[@ID="0"]/direction/y',
- './component_design/tank/specific/tank[@ID="0"]/direction/z',
- './component_design/tank/specific/tank[@ID="0"]/mass_properties/mass',
- './component_design/tank/specific/tank[@ID="0"]/mass_properties/inertia/j_xx',
- './component_design/tank/specific/tank[@ID="0"]/mass_properties/inertia/j_yy',
- './component_design/tank/specific/tank[@ID="0"]/mass_properties/inertia/j_zz',
- './component_design/tank/specific/tank[@ID="0"]/mass_properties/inertia/j_xy',
- './component_design/tank/specific/tank[@ID="0"]/mass_properties/inertia/j_xz',
- './component_design/tank/specific/tank[@ID="0"]/mass_properties/inertia/j_yx',
- './component_design/tank/specific/tank[@ID="0"]/mass_properties/inertia/j_yz',
- './component_design/tank/specific/tank[@ID="0"]/mass_properties/inertia/j_zx',
- './component_design/tank/specific/tank[@ID="0"]/mass_properties/inertia/j_zy',
- './component_design/tank/specific/tank[@ID="0"]/mass_properties/center_of_gravity/x',
- './component_design/tank/specific/tank[@ID="0"]/mass_properties/center_of_gravity/y',
- './component_design/tank/specific/tank[@ID="0"]/mass_properties/center_of_gravity/z',
- './component_design/tank/specific/tank[@ID="0"]/maximum_energy_capacity',
- './component_design/tank/specific/tank[@ID="0"]/mass_properties/centroid/x',
- './component_design/tank/specific/tank[@ID="0"]/mass_properties/centroid/y',
- './component_design/tank/specific/tank[@ID="0"]/mass_properties/centroid/z',
- './component_design/tank/specific/tank[@ID="0"]/geometry/cross_section[@ID="0"]/name',
- './component_design/tank/specific/tank[@ID="0"]/geometry/cross_section[@ID="0"]/position/x',
- './component_design/tank/specific/tank[@ID="0"]/geometry/cross_section[@ID="0"]/position/y',
- './component_design/tank/specific/tank[@ID="0"]/geometry/cross_section[@ID="0"]/position/z',
- './component_design/tank/specific/tank[@ID="0"]/geometry/cross_section[@ID="0"]/shape',
- './component_design/tank/specific/tank[@ID="0"]/geometry/cross_section[@ID="0"]/height',
- './component_design/tank/specific/tank[@ID="0"]/geometry/cross_section[@ID="0"]/width',
- './component_design/tank/specific/tank[@ID="0"]/geometry/cross_section[@ID="0"]/length'
- ]
- module_key_parameters_dict = {
- 'component_design': {
- 'tank': {
- 'attributes': {
- 'description': 'Description of aircraft tanks.',
- 'tool_level': '0'},
- 'position': {
- 'attributes': {'description':
- 'Tank reference point, position of the tanks with regard to the global reference '
- 'point.'},
- 'x': {
- 'attributes': {'description': 'Distance between the foremost tank end and the global '
- 'reference point in x-direction.'},
- 'value': '0',
- 'unit': 'm',
- 'lower_boundary': '-80',
- 'upper_boundary': '80'},
- 'y': {
- 'attributes': {'description': 'Distance between the foremost tank end and the global '
- 'reference point in y-direction.'},
- 'value': '0',
- 'unit': 'm',
- 'lower_boundary': '-40',
- 'upper_boundary': '40'},
- 'z': {
- 'attributes': {'description': 'Distance between the foremost middle tank end and the global '
- 'reference point in z-direction.'},
- 'value': '0',
- 'unit': 'm',
- 'lower_boundary': '-5',
- 'upper_boundary': '5'},
- },
- 'mass_properties': {
- 'attributes': {
- 'description': 'Mass properties of all tanks.'},
- 'mass': {
- 'attributes': {'description': 'Total tank mass.'},
- 'value': '0',
- 'unit': 'kg',
- 'lower_boundary': '0',
- 'upper_boundary': 'inf'},
- 'inertia': {
- 'attributes': {
- 'description': 'Inertia of all tanks with regard to the total center of gravity.'},
- 'j_xx': {
- 'attributes': {
- 'description': 'Inertia of all tanks in x.'},
- 'value': '0',
- 'unit': 'kgm^2',
- 'lower_boundary': '-inf',
- 'upper_boundary': 'inf'},
- 'j_yy': {
- 'attributes': {
- 'description': 'Inertia of all tanks in y.'},
- 'value': '0',
- 'unit': 'kgm^2',
- 'lower_boundary': '-inf',
- 'upper_boundary': 'inf'},
- 'j_zz': {
- 'attributes': {
- 'description': 'Inertia of all tanks in z.'},
- 'value': '0',
- 'unit': 'kgm^2',
- 'lower_boundary': '-inf',
- 'upper_boundary': 'inf'},
- 'j_xy': {
- 'attributes': {
- 'description': 'Inertia of all tanks in xy.'},
- 'value': '0',
- 'unit': 'kgm^2',
- 'lower_boundary': '-inf',
- 'upper_boundary': 'inf'},
- 'j_xz': {
- 'attributes': {
- 'description': 'Inertia of all tanks in xz.'},
- 'value': '0',
- 'unit': 'kgm^2',
- 'lower_boundary': '-inf',
- 'upper_boundary': 'inf'},
- 'j_yx': {
- 'attributes': {
- 'description': 'Inertia of all tanks in yx.'},
- 'value': '0',
- 'unit': 'kgm^2',
- 'lower_boundary': '-inf',
- 'upper_boundary': 'inf'},
- 'j_yz': {
- 'attributes': {
- 'description': 'Inertia of all tanks in yz.'},
- 'value': '0',
- 'unit': 'kgm^2',
- 'lower_boundary': '-inf',
- 'upper_boundary': 'inf'},
- 'j_zx': {
- 'attributes': {
- 'description': 'Inertia of all tanks in zx.'},
- 'value': '0',
- 'unit': 'kgm^2',
- 'lower_boundary': '-inf',
- 'upper_boundary': 'inf'},
- 'j_zy': {
- 'attributes': {
- 'description': 'Inertia of all tanks in zy.'},
- 'value': '0',
- 'unit': 'kgm^2',
- 'lower_boundary': '-inf',
- 'upper_boundary': 'inf'},
- },
- 'center_of_gravity': {
- 'attributes': {
- 'description': 'Center of gravity of all tanks.'},
- 'x': {
- 'attributes': {
- 'description': 'Center of gravity in x-direction with regard to the global reference '
- 'point.'},
- 'value': '0',
- 'unit': 'm',
- 'lower_boundary': '-80',
- 'upper_boundary': '80'},
- 'y': {
- 'attributes': {
- 'description': 'Center of gravity in y-direction with regard to the global reference '
- 'point.'},
- 'value': '0',
- 'unit': 'm',
- 'lower_boundary': '-40',
- 'upper_boundary': '40'},
- 'z': {
- 'attributes': {
- 'description': 'Center of gravity in z-direction with regard to the global reference '
- 'point.'},
- 'value': '0',
- 'unit': 'm',
- 'lower_boundary': '-5',
- 'upper_boundary': '5'}
- }
- },
- 'specific': {
- 'attributes': {
- 'description': 'Tank design specific output parameter.'},
- 'tank': {
- 'attributes': {
- 'ID': '0',
- 'description': 'Description of one tank.'},
- 'name': {
- 'attributes': {
- 'description': 'Name of the tank.'},
- 'value': 'tank_0'},
- 'designator': {
- 'attributes': {
- 'description': 'Designator of the tank.'},
- 'value': 'placeholder_designator'},
- 'position': {
- 'attributes': {
- 'description': 'Local reference point, position of one tank wrt. the tank reference point.'},
- 'x': {
- 'attributes': {
- 'description': 'Distance between the foremost tank end of one tank and the tank '
- 'reference point in x-direction.'},
- 'value': '0',
- 'unit': 'm',
- 'lower_boundary': '-80',
- 'upper_boundary': '80'},
- 'y': {
- 'attributes': {
- 'description': 'Distance between the foremost tank end of one tank and the tank '
- 'reference point in y-direction.'},
- 'value': '0',
- 'unit': 'm',
- 'lower_boundary': '-40',
- 'upper_boundary': '40'},
- 'z': {
- 'attributes': {
- 'description': 'Distance between the foremost tank end of one tank and the tank '
- 'reference point in z-direction.'},
- 'value': '0',
- 'unit': 'm',
- 'lower_boundary': '-5',
- 'upper_boundary': '5'}
- },
- 'direction': {
- 'attributes': {
- 'description': 'Unit vector according to global coordinate system for direction '
- 'applied at position.'},
- 'x': {
- 'attributes': {
- 'description': 'X component of the unit vector.'},
- 'value': '0',
- 'unit': 'm',
- 'lower_boundary': '0',
- 'upper_boundary': '1'},
- 'y': {
- 'attributes': {
- 'description': 'Y component of the unit vector.'},
- 'value': '0',
- 'unit': 'm',
- 'lower_boundary': '0',
- 'upper_boundary': '1'},
- 'z': {
- 'attributes': {
- 'description': 'Z component of the unit vector.'},
- 'value': '0',
- 'unit': 'm',
- 'lower_boundary': '0',
- 'upper_boundary': '1'}
- },
- 'mass_properties': {
- 'attributes': {
- 'description': 'Mass properties of one tank.'},
- 'mass': {
- 'attributes': {'description': 'Total dry mass of one tank.'},
- 'value': '0',
- 'unit': 'kg',
- 'lower_boundary': '0',
- 'upper_boundary': 'inf'},
- 'inertia': {
- 'attributes': {
- 'description': 'Inertia of one tank with regard to its center of gravity.'},
- 'j_xx': {
- 'attributes': {
- 'description': 'Inertia of the of one tank in x.'},
- 'value': '0',
- 'unit': 'kgm^2',
- 'lower_boundary': '-inf',
- 'upper_boundary': 'inf'},
- 'j_yy': {
- 'attributes': {
- 'description': 'Inertia of the of one tank in y.'},
- 'value': '0',
- 'unit': 'kgm^2',
- 'lower_boundary': '-inf',
- 'upper_boundary': 'inf'},
- 'j_zz': {
- 'attributes': {
- 'description': 'Inertia of the of one tank in z.'},
- 'value': '0',
- 'unit': 'kgm^2',
- 'lower_boundary': '-inf',
- 'upper_boundary': 'inf'},
- 'j_xy': {
- 'attributes': {
- 'description': 'Inertia of one tank in xy.'},
- 'value': '0',
- 'unit': 'kgm^2',
- 'lower_boundary': '-inf',
- 'upper_boundary': 'inf'},
- 'j_xz': {
- 'attributes': {
- 'description': 'Inertia of one tank in xz.'},
- 'value': '0',
- 'unit': 'kgm^2',
- 'lower_boundary': '-inf',
- 'upper_boundary': 'inf'},
- 'j_yx': {
- 'attributes': {
- 'description': 'Inertia of one tank in yx.'},
- 'value': '0',
- 'unit': 'kgm^2',
- 'lower_boundary': '-inf',
- 'upper_boundary': 'inf'},
- 'j_yz': {
- 'attributes': {
- 'description': 'Inertia of one tank in yz.'},
- 'value': '0',
- 'unit': 'kgm^2',
- 'lower_boundary': '-inf',
- 'upper_boundary': 'inf'},
- 'j_zx': {
- 'attributes': {
- 'description': 'Inertia of one tank in zx.'},
- 'value': '0',
- 'unit': 'kgm^2',
- 'lower_boundary': '-inf',
- 'upper_boundary': 'inf'},
- 'j_zy': {
- 'attributes': {
- 'description': 'Inertia of one tank in zy.'},
- 'value': '0',
- 'unit': 'kgm^2',
- 'lower_boundary': '-inf',
- 'upper_boundary': 'inf'}},
- 'center_of_gravity': {
- 'attributes': {'description': 'Center of gravity of one tank.'},
- 'x': {
- 'attributes': {
- 'description': 'Center of gravity in x-direction with regard to the global '
- 'reference point.'},
- 'value': '0',
- 'unit': 'm',
- 'lower_boundary': '-80',
- 'upper_boundary': '80'},
- 'y': {
- 'attributes': {
- 'description': 'Center of gravity in y-direction with regard to the global '
- 'reference point.'},
- 'value': '0',
- 'unit': 'm',
- 'lower_boundary': '-40',
- 'upper_boundary': '40'},
- 'z': {
- 'attributes': {
- 'description': 'Center of gravity in z-direction with regard to the global '
- 'reference point.'},
- 'value': '0',
- 'unit': 'm',
- 'lower_boundary': '-5',
- 'upper_boundary': '5'}
- },
- 'centroid': {
- 'attributes': {'description': 'Centroid of one tank.'},
- 'x': {
- 'attributes': {
- 'description': 'Centroid in x-direction with regard to the local '
- 'reference point.'},
- 'value': '0',
- 'unit': 'm',
- 'lower_boundary': '-80',
- 'upper_boundary': '80'},
- 'y': {
- 'attributes': {
- 'description': 'Centroid in y-direction with regard to the local '
- 'reference point.'},
- 'value': '0',
- 'unit': 'm',
- 'lower_boundary': '-40',
- 'upper_boundary': '40'},
- 'z': {
- 'attributes': {
- 'description': 'Centroid in z-direction with regard to the local '
- 'reference point.'},
- 'value': '0',
- 'unit': 'm',
- 'lower_boundary': '-5',
- 'upper_boundary': '5'}
- }
- },
- 'maximum_energy_capacity': {
- 'attributes': {'description': 'Maximum energy capacity of one tank.'},
- 'value': '0',
- 'unit': 'J',
- 'lower_boundary': '0',
- 'upper_boundary': 'inf'},
- 'geometry': {
- 'attributes': {'description': 'Geometrical description of one tank.'},
- 'cross_section': {
- 'attributes': {
- 'ID': '0',
- 'description': 'Geometrical description of one tank cross section.'},
- 'name': {
- 'attributes': {
- 'description': 'Name of tank cross section.'},
- 'value': 'tank_section_0'},
- 'position': {
- 'attributes': {
- 'description': 'Position of tank cross section with regard to the local '
- 'reference point.'},
- 'x': {
- 'attributes': {
- 'description': 'Distance between the tank cross section and the local '
- 'reference point in x-direction.'},
- 'value': '0',
- 'unit': 'm',
- 'lower_boundary': '-80',
- 'upper_boundary': '80'},
- 'y': {
- 'attributes': {
- 'description': 'Distance between the tank cross section and the local '
- 'reference point in y-direction.'},
- 'value': '0',
- 'unit': 'm',
- 'lower_boundary': '-40',
- 'upper_boundary': '40'},
- 'z': {
- 'attributes': {
- 'description': 'Distance between the tank cross section and the local '
- 'reference point in z-direction.'},
- 'value': '0',
- 'unit': 'm',
- 'lower_boundary': '-5',
- 'upper_boundary': '5'}},
- 'shape': {
- 'attributes': {
- 'description': 'Description of the shape of the cross section (circular, '
- 'rectangular, elliptical).'},
- 'value': 'misc'},
- 'height': {
- 'attributes': {
- 'description': 'Height of the cross section.'},
- 'value': '0',
- 'unit': 'm',
- 'lower_boundary': '0',
- 'upper_boundary': 'inf'},
- 'width': {
- 'attributes': {
- 'description': 'Width of the cross section.'},
- 'value': '0',
- 'unit': 'm',
- 'lower_boundary': '0',
- 'upper_boundary': 'inf'},
- 'length': {
- 'attributes': {
- 'description': 'Length of the cross section (if length greater than 0: curved '
- 'cross section, e.g., dashed tank end cap).'},
- 'value': '0',
- 'unit': 'm',
- 'lower_boundary': '0',
- 'upper_boundary': 'inf'}
- }
- }
- },
- 'additional_fuselage_length': {
- 'attributes': {
- 'description': 'Additional fuselage length (if smaller than 0: shrink '
- 'fuselage, if greater than 0: stretch fuselage).'},
- 'value': '0',
- 'unit': 'm',
- 'lower_boundary': '0',
- 'upper_boundary': 'inf'
- }
- }
- }
- }
- }
-
- paths_and_names = prepare_element_tree_for_module_key_parameter(paths_and_names, module_key_parameters_dict)
-
- # Run 'user_method_data_output_preparation' from 'usermethoddatapreparation.py'.
- key_output_dict, method_specific_output_dict = routing_dict['func_user_method_data_output_preparation'](data_dict)
- # Extract tool level from routing dictionary.
- tool_level = routing_dict['tool_level']
-
- """Write data to aircraft exchange file."""
- # Extract root and path to aircraft exchange file.
- root_of_aircraft_exchange_tree = paths_and_names['root_of_aircraft_exchange_tree']
- path_to_aircraft_exchange_file = paths_and_names['path_to_aircraft_exchange_file']
- # Write key data to aircraft exchange file.
- write_key_data_to_aircraft_exchange_file(root_of_aircraft_exchange_tree, path_to_aircraft_exchange_file,
- paths_to_key_parameters_list, key_output_dict, tool_level, runtime_output)
-
- """Method-specific postprocessing."""
- # Run 'method_data_postprocessing' from 'datapostprocessingmodule'.
- data_dict['module_key_parameters_dict'] = module_key_parameters_dict
- data_dict['paths_to_key_parameters_list'] = paths_to_key_parameters_list
- method_data_postprocessing(paths_and_names, routing_dict, data_dict,
- method_specific_output_dict, runtime_output)
+"""Module providing functions for data postprocessing."""
+# Import standard modules.
+
+# Import own modules.
+from datapostprocessingmodule import method_data_postprocessing
+from datapostprocessingmodule import write_key_data_to_aircraft_exchange_file
+from datapostprocessingmodule import prepare_element_tree_for_module_key_parameter
+
+
+def data_postprocessing(paths_and_names, routing_dict, data_dict, runtime_output):
+ """Perform data postprocessing and write data to an aircraft exchange file.
+
+ This function is responsible for data postprocessing that involves the following steps:
+ (1) Data preparation: The module manager prepares a list containing all paths to the key parameters that must
+ be written to the aircraft exchange file.
+ (2) Write data to the aircraft exchange file: The results of the module execution are passed on to the function
+ responsible for properly writing the data to the aircraft exchange file.
+ (3) Method-specific data postprocessing: User-defined method-specific postprocessing is conducted as needed.
+
+ :param dict paths_and_names: Dictionary containing system paths and ElementTrees
+ :param dict routing_dict: Dictionary containing routing parameters
+ :param dict data_dict: Dictionary containing the result of the module execution (direct operating cost estimation)
+ :param logging.Logger runtime_output: Logging object used for capturing log messages in the module
+ :return: None
+ """
+
+ """Data preparation."""
+ # Changes to this list are the sole responsibility of the module manager!
+ paths_to_key_parameters_list = [
+ './component_design/tank/position/x',
+ './component_design/tank/position/y',
+ './component_design/tank/position/z',
+ './component_design/tank/mass_properties/mass',
+ './component_design/tank/mass_properties/inertia/j_xx',
+ './component_design/tank/mass_properties/inertia/j_yy',
+ './component_design/tank/mass_properties/inertia/j_zz',
+ './component_design/tank/mass_properties/inertia/j_xy',
+ './component_design/tank/mass_properties/inertia/j_xz',
+ './component_design/tank/mass_properties/inertia/j_yx',
+ './component_design/tank/mass_properties/inertia/j_yz',
+ './component_design/tank/mass_properties/inertia/j_zx',
+ './component_design/tank/mass_properties/inertia/j_zy',
+ './component_design/tank/mass_properties/center_of_gravity/x',
+ './component_design/tank/mass_properties/center_of_gravity/y',
+ './component_design/tank/mass_properties/center_of_gravity/z',
+ './component_design/tank/specific/additional_fuselage_length',
+ './component_design/tank/specific/tank[@ID="0"]/name',
+ './component_design/tank/specific/tank[@ID="0"]/designator',
+ './component_design/tank/specific/tank[@ID="0"]/position/x',
+ './component_design/tank/specific/tank[@ID="0"]/position/y',
+ './component_design/tank/specific/tank[@ID="0"]/position/z',
+ './component_design/tank/specific/tank[@ID="0"]/direction/x',
+ './component_design/tank/specific/tank[@ID="0"]/direction/y',
+ './component_design/tank/specific/tank[@ID="0"]/direction/z',
+ './component_design/tank/specific/tank[@ID="0"]/mass_properties/mass',
+ './component_design/tank/specific/tank[@ID="0"]/mass_properties/inertia/j_xx',
+ './component_design/tank/specific/tank[@ID="0"]/mass_properties/inertia/j_yy',
+ './component_design/tank/specific/tank[@ID="0"]/mass_properties/inertia/j_zz',
+ './component_design/tank/specific/tank[@ID="0"]/mass_properties/inertia/j_xy',
+ './component_design/tank/specific/tank[@ID="0"]/mass_properties/inertia/j_xz',
+ './component_design/tank/specific/tank[@ID="0"]/mass_properties/inertia/j_yx',
+ './component_design/tank/specific/tank[@ID="0"]/mass_properties/inertia/j_yz',
+ './component_design/tank/specific/tank[@ID="0"]/mass_properties/inertia/j_zx',
+ './component_design/tank/specific/tank[@ID="0"]/mass_properties/inertia/j_zy',
+ './component_design/tank/specific/tank[@ID="0"]/mass_properties/center_of_gravity/x',
+ './component_design/tank/specific/tank[@ID="0"]/mass_properties/center_of_gravity/y',
+ './component_design/tank/specific/tank[@ID="0"]/mass_properties/center_of_gravity/z',
+ './component_design/tank/specific/tank[@ID="0"]/maximum_energy_capacity',
+ './component_design/tank/specific/tank[@ID="0"]/energy_capacity_required_for_mission',
+ './component_design/tank/specific/tank[@ID="0"]/mass_properties/centroid/x',
+ './component_design/tank/specific/tank[@ID="0"]/mass_properties/centroid/y',
+ './component_design/tank/specific/tank[@ID="0"]/mass_properties/centroid/z',
+ './component_design/tank/specific/tank[@ID="0"]/geometry/cross_section[@ID="0"]/name',
+ './component_design/tank/specific/tank[@ID="0"]/geometry/cross_section[@ID="0"]/position/x',
+ './component_design/tank/specific/tank[@ID="0"]/geometry/cross_section[@ID="0"]/position/y',
+ './component_design/tank/specific/tank[@ID="0"]/geometry/cross_section[@ID="0"]/position/z',
+ './component_design/tank/specific/tank[@ID="0"]/geometry/cross_section[@ID="0"]/shape',
+ './component_design/tank/specific/tank[@ID="0"]/geometry/cross_section[@ID="0"]/height',
+ './component_design/tank/specific/tank[@ID="0"]/geometry/cross_section[@ID="0"]/width',
+ './component_design/tank/specific/tank[@ID="0"]/geometry/cross_section[@ID="0"]/length'
+ ]
+ module_key_parameters_dict = {
+ 'component_design': {
+ 'tank': {
+ 'attributes': {
+ 'description': 'Description of aircraft tanks.',
+ 'tool_level': '0'},
+ 'position': {
+ 'attributes': {'description':
+ 'Tank reference point, position of the tanks with regard to the global reference '
+ 'point.'},
+ 'x': {
+ 'attributes': {'description': 'Distance between the foremost tank end and the global '
+ 'reference point in x-direction.'},
+ 'value': '0',
+ 'unit': 'm',
+ 'lower_boundary': '-80',
+ 'upper_boundary': '80'},
+ 'y': {
+ 'attributes': {'description': 'Distance between the foremost tank end and the global '
+ 'reference point in y-direction.'},
+ 'value': '0',
+ 'unit': 'm',
+ 'lower_boundary': '-40',
+ 'upper_boundary': '40'},
+ 'z': {
+ 'attributes': {'description': 'Distance between the foremost middle tank end and the global '
+ 'reference point in z-direction.'},
+ 'value': '0',
+ 'unit': 'm',
+ 'lower_boundary': '-5',
+ 'upper_boundary': '5'},
+ },
+ 'mass_properties': {
+ 'attributes': {
+ 'description': 'Mass properties of all tanks.'},
+ 'mass': {
+ 'attributes': {'description': 'Total tank mass.'},
+ 'value': '0',
+ 'unit': 'kg',
+ 'lower_boundary': '0',
+ 'upper_boundary': 'inf'},
+ 'inertia': {
+ 'attributes': {
+ 'description': 'Inertia of all tanks with regard to the total center of gravity.'},
+ 'j_xx': {
+ 'attributes': {
+ 'description': 'Inertia of all tanks in x.'},
+ 'value': '0',
+ 'unit': 'kgm^2',
+ 'lower_boundary': '-inf',
+ 'upper_boundary': 'inf'},
+ 'j_yy': {
+ 'attributes': {
+ 'description': 'Inertia of all tanks in y.'},
+ 'value': '0',
+ 'unit': 'kgm^2',
+ 'lower_boundary': '-inf',
+ 'upper_boundary': 'inf'},
+ 'j_zz': {
+ 'attributes': {
+ 'description': 'Inertia of all tanks in z.'},
+ 'value': '0',
+ 'unit': 'kgm^2',
+ 'lower_boundary': '-inf',
+ 'upper_boundary': 'inf'},
+ 'j_xy': {
+ 'attributes': {
+ 'description': 'Inertia of all tanks in xy.'},
+ 'value': '0',
+ 'unit': 'kgm^2',
+ 'lower_boundary': '-inf',
+ 'upper_boundary': 'inf'},
+ 'j_xz': {
+ 'attributes': {
+ 'description': 'Inertia of all tanks in xz.'},
+ 'value': '0',
+ 'unit': 'kgm^2',
+ 'lower_boundary': '-inf',
+ 'upper_boundary': 'inf'},
+ 'j_yx': {
+ 'attributes': {
+ 'description': 'Inertia of all tanks in yx.'},
+ 'value': '0',
+ 'unit': 'kgm^2',
+ 'lower_boundary': '-inf',
+ 'upper_boundary': 'inf'},
+ 'j_yz': {
+ 'attributes': {
+ 'description': 'Inertia of all tanks in yz.'},
+ 'value': '0',
+ 'unit': 'kgm^2',
+ 'lower_boundary': '-inf',
+ 'upper_boundary': 'inf'},
+ 'j_zx': {
+ 'attributes': {
+ 'description': 'Inertia of all tanks in zx.'},
+ 'value': '0',
+ 'unit': 'kgm^2',
+ 'lower_boundary': '-inf',
+ 'upper_boundary': 'inf'},
+ 'j_zy': {
+ 'attributes': {
+ 'description': 'Inertia of all tanks in zy.'},
+ 'value': '0',
+ 'unit': 'kgm^2',
+ 'lower_boundary': '-inf',
+ 'upper_boundary': 'inf'},
+ },
+ 'center_of_gravity': {
+ 'attributes': {
+ 'description': 'Center of gravity of all tanks.'},
+ 'x': {
+ 'attributes': {
+ 'description': 'Center of gravity in x-direction with regard to the global reference '
+ 'point.'},
+ 'value': '0',
+ 'unit': 'm',
+ 'lower_boundary': '-80',
+ 'upper_boundary': '80'},
+ 'y': {
+ 'attributes': {
+ 'description': 'Center of gravity in y-direction with regard to the global reference '
+ 'point.'},
+ 'value': '0',
+ 'unit': 'm',
+ 'lower_boundary': '-40',
+ 'upper_boundary': '40'},
+ 'z': {
+ 'attributes': {
+ 'description': 'Center of gravity in z-direction with regard to the global reference '
+ 'point.'},
+ 'value': '0',
+ 'unit': 'm',
+ 'lower_boundary': '-5',
+ 'upper_boundary': '5'}
+ }
+ },
+ 'specific': {
+ 'attributes': {
+ 'description': 'Tank design specific output parameter.'},
+ 'tank': {
+ 'attributes': {
+ 'ID': '0',
+ 'description': 'Description of one tank.'},
+ 'name': {
+ 'attributes': {
+ 'description': 'Name of the tank.'},
+ 'value': 'tank_0'},
+ 'designator': {
+ 'attributes': {
+ 'description': 'Designator of the tank.'},
+ 'value': 'placeholder_designator'},
+ 'position': {
+ 'attributes': {
+ 'description': 'Local reference point, position of one tank wrt. the tank reference point.'},
+ 'x': {
+ 'attributes': {
+ 'description': 'Distance between the foremost tank end of one tank and the tank '
+ 'reference point in x-direction.'},
+ 'value': '0',
+ 'unit': 'm',
+ 'lower_boundary': '-80',
+ 'upper_boundary': '80'},
+ 'y': {
+ 'attributes': {
+ 'description': 'Distance between the foremost tank end of one tank and the tank '
+ 'reference point in y-direction.'},
+ 'value': '0',
+ 'unit': 'm',
+ 'lower_boundary': '-40',
+ 'upper_boundary': '40'},
+ 'z': {
+ 'attributes': {
+ 'description': 'Distance between the foremost tank end of one tank and the tank '
+ 'reference point in z-direction.'},
+ 'value': '0',
+ 'unit': 'm',
+ 'lower_boundary': '-5',
+ 'upper_boundary': '5'}
+ },
+ 'direction': {
+ 'attributes': {
+ 'description': 'Unit vector according to global coordinate system for direction '
+ 'applied at position.'},
+ 'x': {
+ 'attributes': {
+ 'description': 'X component of the unit vector.'},
+ 'value': '0',
+ 'unit': 'm',
+ 'lower_boundary': '0',
+ 'upper_boundary': '1'},
+ 'y': {
+ 'attributes': {
+ 'description': 'Y component of the unit vector.'},
+ 'value': '0',
+ 'unit': 'm',
+ 'lower_boundary': '0',
+ 'upper_boundary': '1'},
+ 'z': {
+ 'attributes': {
+ 'description': 'Z component of the unit vector.'},
+ 'value': '0',
+ 'unit': 'm',
+ 'lower_boundary': '0',
+ 'upper_boundary': '1'}
+ },
+ 'mass_properties': {
+ 'attributes': {
+ 'description': 'Mass properties of one tank.'},
+ 'mass': {
+ 'attributes': {'description': 'Total dry mass of one tank.'},
+ 'value': '0',
+ 'unit': 'kg',
+ 'lower_boundary': '0',
+ 'upper_boundary': 'inf'},
+ 'inertia': {
+ 'attributes': {
+ 'description': 'Inertia of one tank with regard to its center of gravity.'},
+ 'j_xx': {
+ 'attributes': {
+ 'description': 'Inertia of the of one tank in x.'},
+ 'value': '0',
+ 'unit': 'kgm^2',
+ 'lower_boundary': '-inf',
+ 'upper_boundary': 'inf'},
+ 'j_yy': {
+ 'attributes': {
+ 'description': 'Inertia of the of one tank in y.'},
+ 'value': '0',
+ 'unit': 'kgm^2',
+ 'lower_boundary': '-inf',
+ 'upper_boundary': 'inf'},
+ 'j_zz': {
+ 'attributes': {
+ 'description': 'Inertia of the of one tank in z.'},
+ 'value': '0',
+ 'unit': 'kgm^2',
+ 'lower_boundary': '-inf',
+ 'upper_boundary': 'inf'},
+ 'j_xy': {
+ 'attributes': {
+ 'description': 'Inertia of one tank in xy.'},
+ 'value': '0',
+ 'unit': 'kgm^2',
+ 'lower_boundary': '-inf',
+ 'upper_boundary': 'inf'},
+ 'j_xz': {
+ 'attributes': {
+ 'description': 'Inertia of one tank in xz.'},
+ 'value': '0',
+ 'unit': 'kgm^2',
+ 'lower_boundary': '-inf',
+ 'upper_boundary': 'inf'},
+ 'j_yx': {
+ 'attributes': {
+ 'description': 'Inertia of one tank in yx.'},
+ 'value': '0',
+ 'unit': 'kgm^2',
+ 'lower_boundary': '-inf',
+ 'upper_boundary': 'inf'},
+ 'j_yz': {
+ 'attributes': {
+ 'description': 'Inertia of one tank in yz.'},
+ 'value': '0',
+ 'unit': 'kgm^2',
+ 'lower_boundary': '-inf',
+ 'upper_boundary': 'inf'},
+ 'j_zx': {
+ 'attributes': {
+ 'description': 'Inertia of one tank in zx.'},
+ 'value': '0',
+ 'unit': 'kgm^2',
+ 'lower_boundary': '-inf',
+ 'upper_boundary': 'inf'},
+ 'j_zy': {
+ 'attributes': {
+ 'description': 'Inertia of one tank in zy.'},
+ 'value': '0',
+ 'unit': 'kgm^2',
+ 'lower_boundary': '-inf',
+ 'upper_boundary': 'inf'}},
+ 'center_of_gravity': {
+ 'attributes': {'description': 'Center of gravity of one tank.'},
+ 'x': {
+ 'attributes': {
+ 'description': 'Center of gravity in x-direction with regard to the global '
+ 'reference point.'},
+ 'value': '0',
+ 'unit': 'm',
+ 'lower_boundary': '-80',
+ 'upper_boundary': '80'},
+ 'y': {
+ 'attributes': {
+ 'description': 'Center of gravity in y-direction with regard to the global '
+ 'reference point.'},
+ 'value': '0',
+ 'unit': 'm',
+ 'lower_boundary': '-40',
+ 'upper_boundary': '40'},
+ 'z': {
+ 'attributes': {
+ 'description': 'Center of gravity in z-direction with regard to the global '
+ 'reference point.'},
+ 'value': '0',
+ 'unit': 'm',
+ 'lower_boundary': '-5',
+ 'upper_boundary': '5'}
+ },
+ 'centroid': {
+ 'attributes': {'description': 'Centroid of one tank.'},
+ 'x': {
+ 'attributes': {
+ 'description': 'Centroid in x-direction with regard to the local '
+ 'reference point.'},
+ 'value': '0',
+ 'unit': 'm',
+ 'lower_boundary': '-80',
+ 'upper_boundary': '80'},
+ 'y': {
+ 'attributes': {
+ 'description': 'Centroid in y-direction with regard to the local '
+ 'reference point.'},
+ 'value': '0',
+ 'unit': 'm',
+ 'lower_boundary': '-40',
+ 'upper_boundary': '40'},
+ 'z': {
+ 'attributes': {
+ 'description': 'Centroid in z-direction with regard to the local '
+ 'reference point.'},
+ 'value': '0',
+ 'unit': 'm',
+ 'lower_boundary': '-5',
+ 'upper_boundary': '5'}
+ }
+ },
+ 'maximum_energy_capacity': {
+ 'attributes': {'description': 'Maximum energy capacity of one tank.'},
+ 'value': '0',
+ 'unit': 'J',
+ 'lower_boundary': '0',
+ 'upper_boundary': 'inf'},
+ 'energy_capacity_required_for_mission': {
+ 'attributes': {'description': 'Energy amount required for mission.'},
+ 'value': 'True'},
+ 'geometry': {
+ 'attributes': {'description': 'Geometrical description of one tank.'},
+ 'cross_section': {
+ 'attributes': {
+ 'ID': '0',
+ 'description': 'Geometrical description of one tank cross section.'},
+ 'name': {
+ 'attributes': {
+ 'description': 'Name of tank cross section.'},
+ 'value': 'tank_section_0'},
+ 'position': {
+ 'attributes': {
+ 'description': 'Position of tank cross section with regard to the local '
+ 'reference point.'},
+ 'x': {
+ 'attributes': {
+ 'description': 'Distance between the tank cross section and the local '
+ 'reference point in x-direction.'},
+ 'value': '0',
+ 'unit': 'm',
+ 'lower_boundary': '-80',
+ 'upper_boundary': '80'},
+ 'y': {
+ 'attributes': {
+ 'description': 'Distance between the tank cross section and the local '
+ 'reference point in y-direction.'},
+ 'value': '0',
+ 'unit': 'm',
+ 'lower_boundary': '-40',
+ 'upper_boundary': '40'},
+ 'z': {
+ 'attributes': {
+ 'description': 'Distance between the tank cross section and the local '
+ 'reference point in z-direction.'},
+ 'value': '0',
+ 'unit': 'm',
+ 'lower_boundary': '-5',
+ 'upper_boundary': '5'}},
+ 'shape': {
+ 'attributes': {
+ 'description': 'Description of the shape of the cross section (circular, '
+ 'rectangular, elliptical).'},
+ 'value': 'misc'},
+ 'height': {
+ 'attributes': {
+ 'description': 'Height of the cross section.'},
+ 'value': '0',
+ 'unit': 'm',
+ 'lower_boundary': '0',
+ 'upper_boundary': 'inf'},
+ 'width': {
+ 'attributes': {
+ 'description': 'Width of the cross section.'},
+ 'value': '0',
+ 'unit': 'm',
+ 'lower_boundary': '0',
+ 'upper_boundary': 'inf'},
+ 'length': {
+ 'attributes': {
+ 'description': 'Length of the cross section (if length greater than 0: curved '
+ 'cross section, e.g., dashed tank end cap).'},
+ 'value': '0',
+ 'unit': 'm',
+ 'lower_boundary': '0',
+ 'upper_boundary': 'inf'}
+ }
+ }
+ },
+ 'additional_fuselage_length': {
+ 'attributes': {
+ 'description': 'Additional fuselage length (if smaller than 0: shrink '
+ 'fuselage, if greater than 0: stretch fuselage).'},
+ 'value': '0',
+ 'unit': 'm',
+ 'lower_boundary': '0',
+ 'upper_boundary': 'inf'
+ }
+ }
+ }
+ }
+ }
+
+ paths_and_names = prepare_element_tree_for_module_key_parameter(paths_and_names, module_key_parameters_dict)
+
+ # Run 'user_method_data_output_preparation' from 'usermethoddatapreparation.py'.
+ key_output_dict, method_specific_output_dict = routing_dict['func_user_method_data_output_preparation'](data_dict)
+ # Extract tool level from routing dictionary.
+ tool_level = routing_dict['tool_level']
+
+ """Write data to aircraft exchange file."""
+ # Extract root and path to aircraft exchange file.
+ root_of_aircraft_exchange_tree = paths_and_names['root_of_aircraft_exchange_tree']
+ path_to_aircraft_exchange_file = paths_and_names['path_to_aircraft_exchange_file']
+ # Write key data to aircraft exchange file.
+ write_key_data_to_aircraft_exchange_file(root_of_aircraft_exchange_tree, path_to_aircraft_exchange_file,
+ paths_to_key_parameters_list, key_output_dict, tool_level, runtime_output)
+
+ """Method-specific postprocessing."""
+ # Run 'method_data_postprocessing' from 'datapostprocessingmodule'.
+ data_dict['module_key_parameters_dict'] = module_key_parameters_dict
+ data_dict['paths_to_key_parameters_list'] = paths_to_key_parameters_list
+ method_data_postprocessing(paths_and_names, routing_dict, data_dict,
+ method_specific_output_dict, runtime_output)
diff --git a/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/general/call_functions/_00_readenergycarrierandtankconfiguration.py b/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/general/call_functions/_00_readenergycarrierandtankconfiguration.py
index 4470da73eb0ee5577363a0e5bc083fa75aa9e64c..b4c787bc0980caeb1909d164cdd1b04c0dd9a64e 100644
--- a/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/general/call_functions/_00_readenergycarrierandtankconfiguration.py
+++ b/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/general/call_functions/_00_readenergycarrierandtankconfiguration.py
@@ -2,6 +2,9 @@
# Import standard libraries.
import sys
+# Import own libraries.
+from pyunitconversion import constants
+
def read_energy_carrier_and_tank_configuration(paths_and_names, dict_ac_data, dict_tank_design, runtime_output):
"""Determine energy carrier dependent parameter.
@@ -36,10 +39,6 @@ def read_energy_carrier_and_tank_configuration(paths_and_names, dict_ac_data, di
tank_location = dict_ac_data['tank_location']
tank_position = dict_ac_data['tank_position']
tank_energy_share = dict_ac_data['energy_share']
- gravimetric_energy_densities = {'kerosene': dict_ac_data['kerosene_gravimetric_energy_density'],
- 'liquid_hydrogen': dict_ac_data['liquid_hydrogen_gravimetric_energy_density']}
- volumetric_energy_densities = {'kerosene': dict_ac_data['kerosene_volumetric_energy_density'],
- 'liquid_hydrogen': dict_ac_data['liquid_hydrogen_volumetric_energy_density']}
except KeyError:
runtime_output.critical('Error: Missing data in aircraft exchange file. Energy carrier and tank configuration '
+' preparation not possible. Program aborted.')
@@ -51,6 +50,11 @@ def read_energy_carrier_and_tank_configuration(paths_and_names, dict_ac_data, di
# energy_carrier_lookup = {0: {'energy_carrier': 'kerosene'}, 1: {'energy_carrier': 'liquid_hydrogen'}}
energy_carrier_lookup = {int(key.split('ID')[-1]): {'energy_carrier': value}
for key, value in energy_carrier_name.items()}
+
+ gravimetric_energy_densities = {'kerosene': constants.KEROSENE_GRAVIMETRIC_ENERGY_DENSITY,
+ 'liquid_hydrogen': constants.LIQUID_HYDROGEN_GRAVIMETRIC_ENERGY_DENSITY}
+ volumetric_energy_densities = {'kerosene': constants.KEROSENE_VOLUMETRIC_ENERGY_DENSITY,
+ 'liquid_hydrogen': constants.LIQUID_HYDROGEN_VOLUMETRIC_ENERGY_DENSITY}
# Map mission energy ID to energy carrier ID and update the lookup dictionary.
for key, val in mission_energy_id.items():
diff --git a/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/general/call_functions/_01_checktankconfiguration.py b/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/general/call_functions/_01_checktankconfiguration.py
index f65fc225bb9942dcce9f6db89dc700505366a68c..44617f75b84057a8816596712ade89703a39d3b7 100644
--- a/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/general/call_functions/_01_checktankconfiguration.py
+++ b/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/general/call_functions/_01_checktankconfiguration.py
@@ -86,15 +86,23 @@ def check_tank_configuration(paths_and_names, dict_ac_data, dict_tank_design, ru
if valid_wing_tanks and not (trim_tank or additional_center_tank):
number_of_tanks = 5
tank_configuration = 'wing_all_tanks'
+ # Print.
+ runtime_output.print('Valid tank configuration found in acXML: ' + tank_configuration)
elif valid_wing_with_trim_tank and not additional_center_tank:
number_of_tanks = 6
tank_configuration = 'wing_with_trim_tank'
+ # Print.
+ runtime_output.print('Valid tank configuration found in acXML: ' + tank_configuration)
elif valid_wing_with_additional_center_tank and not trim_tank:
number_of_tanks = 6
tank_configuration = 'wing_with_additional_center_tank'
+ # Print.
+ runtime_output.print('Valid tank configuration found in acXML: ' + tank_configuration)
elif valid_wing_with_additional_center_and_trim_tank:
number_of_tanks = 7
tank_configuration = 'wing_with_additional_center_and_trim_tank'
+ # Print.
+ runtime_output.print('Valid tank configuration found in acXML: ' + tank_configuration)
# Invalid tank configuration.
else:
number_of_tanks = 0
diff --git a/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/general/call_functions/_02_preparegeometricaldata.py b/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/general/call_functions/_02_preparegeometricaldata.py
index f8aa2372f5be564005033ce33c00c94f2ee87546..43246f5a4a27cd718bb94ac2fea083bc601d3e87 100644
--- a/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/general/call_functions/_02_preparegeometricaldata.py
+++ b/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/general/call_functions/_02_preparegeometricaldata.py
@@ -224,26 +224,28 @@ def prepare_wing_tanks(dict_ac_data, dict_tank_design, runtime_output):
}
# Add further values to 'tmp_dict'.
- # TODO: thickness_max from aircraftGeometry2.
for i, section in enumerate(wing_section_list):
# Add span index to section.
tmp_dict['sections'][section]['span_index'] = abs(int(round(
tmp_dict['sections'][section]['position']['y']*100, 0)))
+ # Add thickness_ratio.
+ tmp_dict['sections'][section]['thickness_ratio'] = dict_ac_data['wing_thickness_to_length'][i]
# Add 'thickness_ratio' (derived from the profile name).
- profile_name = tmp_dict['sections'][section]['profile']
- if profile_name.startswith(("naca", "n", "F15")):
- tmp_dict['sections'][section]['thickness_ratio'] = int(profile_name[-2:])/100
- else:
- # Not implemented yet.
- runtime_output.critical('Error: Thickness ratio cannot be extracted! Program aborted.')
- sys.exit('Exit information: Thickness ratio cannot be extracted from profile name!')
+ # profile_name = tmp_dict['sections'][section]['profile']
+ # if profile_name.startswith(("naca", "n", "F15")):
+ # tmp_dict['sections'][section]['thickness_ratio'] = int(profile_name[-2:])/100
+ # else:
+ # # Not implemented yet.
+ # runtime_output.critical('Error: Thickness ratio cannot be extracted! Program aborted.')
+ # sys.exit('Exit information: Thickness ratio cannot be extracted from profile name!')
# Add 'tmp_dict' to 'dict_tank_design'.
dict_tank_design['geometry']['wing'] = tmp_dict
"""Interpolate necessary values."""
# Calculate number of points for value interpolation (one point per mm).
- number_of_points = abs(int(round(dict_tank_design['geometry']['wing']['sections']['wing_tip']['position']['y']*100, 0)))
+ number_of_points = abs(int(round(dict_tank_design['geometry']['wing']['sections']['wing_tip']['position']['y']
+ *100, 0)))
# Write wing section span indexes (equal distances in mm) to list.
section_span_indexes = [tmp_dict['sections'][section]['span_index'] for section in wing_section_list]
@@ -425,27 +427,28 @@ def prepare_trim_tank(dict_ac_data, dict_tank_design, runtime_output):
}
# Add further values to 'tmp_dict'.
- # TODO: thickness_max from aircraftGeometry2.
for i, section in enumerate(section_list):
# Add span index to section.
tmp_dict['sections'][section]['span_index'] = abs(int(round(
tmp_dict['sections'][section]['position']['y']*100, 0)))
- # Add 'thickness_ratio' (derived from the profile name).
- profile_name = tmp_dict['sections'][section]['profile']
- if profile_name.startswith(("naca", "n", "F15")):
- tmp_dict['sections'][section]['thickness_ratio'] = int(profile_name[-2:])/100
- else:
- # Not implemented yet.
- runtime_output.critical('Error: Thickness ratio cannot be extracted! Program aborted.')
- sys.exit('Exit information: Thickness ratio cannot be extracted from profile name!')
+ # Add thickness_ratio.
+ tmp_dict['sections'][section]['thickness_ratio'] = dict_ac_data['horizontal_stabilizer_thickness_to_length'][i]
+ # # Add 'thickness_ratio' (derived from the profile name).
+ # profile_name = tmp_dict['sections'][section]['profile']
+ # if profile_name.startswith(("naca", "n", "F15")):
+ # tmp_dict['sections'][section]['thickness_ratio'] = int(profile_name[-2:])/100
+ # else:
+ # # Not implemented yet.
+ # runtime_output.critical('Error: Thickness ratio cannot be extracted! Program aborted.')
+ # sys.exit('Exit information: Thickness ratio cannot be extracted from profile name!')
# Add 'tmp_dict' to 'dict_tank_design'.
dict_tank_design['geometry']['horizontal_stabilizer'] = tmp_dict
"""Interpolate necessary values."""
# Calculate number of points for value interpolation (one point per mm).
- number_of_points = int(round(
- dict_tank_design['geometry']['horizontal_stabilizer']['sections']['tip']['position']['y']*100, 0))
+ number_of_points = abs(int(round(
+ dict_tank_design['geometry']['horizontal_stabilizer']['sections']['tip']['position']['y']*100, 0)))
# Write wing section span indexes (equal distances in mm) to list.
section_span_indexes = [tmp_dict['sections'][section]['span_index']
for section in section_list]
diff --git a/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/general/tankdesigntuberlin.py b/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/general/tankdesigntuberlin.py
index ff978858dad1cb3777dfedea1faa2c3d81368411..9ed9201281e6fbe07c32708bf7018dfc05198954 100644
--- a/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/general/tankdesigntuberlin.py
+++ b/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/general/tankdesigntuberlin.py
@@ -1,167 +1,196 @@
-"""Module providing calculating functions for the tank design of tube-and-wing aircraft according to TU Berlin."""
-# Import standard libraries.
-import importlib
-import os
-import sys
-import pycoordinatesystemconversion as py11csc
-
-def tank_design_tu_berlin(paths_and_names, routing_dict, dict_ac_data, runtime_output):
- """Tank design method for tube-and-wing aircraft.
-
- The first step is to check whether the tank design is feasible. This applies if there is only one wing and one
- fuselage. If this is true, the tank design method calls general (independent on energy carrier) functions for the
- tank design of tube-and-wing aircraft.
- The output dictionary 'dict_tank_design' contains the results of the tank design preparation. The output dictionary
- is structured according to the following scheme:
- dict_tank_design = {
- 'tank_0': {...},
- 'tank_1': {...},
- ...
- 'number_of_tanks': (int, number of tanks available),
- 'tank_configuration': (str, name of tank configuration),
- 'valid_tank_definition': (bool, information if tank configuration is valid),
- 'geometry':{...}
- }
- The detailed structure of the sub dictionaries depends on the energy carrier and can be found in the docStrings of
- the '_00_readenergycarrierandtankconfiguration.py' and '_01_preparegeometricaldata.py' files.
-
- :param dict paths_and_names: Dictionary containing system paths and ElementTrees
- :param dict routing_dict: Dictionary containing routing parameters
- :param dict dict_ac_data: Dictionary containing data from aircraft exchange and module configuration file
- :param logging.Logger runtime_output: Logging object used for capturing log messages in the module
- :raises ModuleNotFoundError: Raised if calculation module not found
- :return dict dict_tank_design: Dictionary containing tank design parameter
- """
- """Convert coordinates from CGAL to aircraft coordinate system."""
- # List of parameters to be considered for CGAL to aircraft coordinate system conversion.
- param_list = ["fuselage_position", "wing_position", "empennage_position", "fuselage_entity_position", "fuselage_section_origin", "fuselage_payload_deck_origin",
- "wing_section_chord_origin", "empennage_entity_position", "empennage_section_chord_origin"]
-
- # for param in param_list:
- # if dict_ac_data[param + "_x"] is not None:
- # if type(dict_ac_data[param + "_x"]) != float:
- # for key in dict_ac_data[param + "_x"].keys():
- # index = key.split("_").index("x") + 1
- # if dict_ac_data[param + "_x"][param + "_x_" + key.split("_", index)[-1]] is not None:
- # element3D = py11csc.Element3D(dict_ac_data[param + "_x"][param + "_x_" + key.split("_", index)[-1]],
- # dict_ac_data[param + "_y"][param + "_y_" + key.split("_", index)[-1]],
- # dict_ac_data[param + "_z"][param + "_z_" + key.split("_", index)[-1]])
- # element3D.CGAL2AC()
- # dict_ac_data[param + "_x"][param + "_x_" + key.split("_", index)[-1]] = element3D.x()
- # dict_ac_data[param + "_y"][param + "_y_" + key.split("_", index)[-1]] = element3D.y()
- # dict_ac_data[param + "_z"][param + "_z_" + key.split("_", index)[-1]] = element3D.z()
- # else:
- # runtime_output.warning("WARNING: The parameter " + param + "_x is missing in the aircraft exchange file. No need to convert the coordinates.")
- # else:
- # element3D = py11csc.Element3D(dict_ac_data[param + "_x"],
- # dict_ac_data[param + "_y"],
- # dict_ac_data[param + "_z"])
- # element3D.CGAL2AC()
- # dict_ac_data[param + "_x"] = element3D.x()
- # dict_ac_data[param + "_y"] = element3D.y()
- # dict_ac_data[param + "_z"] = element3D.z()
- # else:
- # runtime_output.warning("WARNING: The parameter " + param + "_x is missing in the aircraft exchange file. No need to convert the coordinates.")
-
- # Transform fuselage cgal coordinates to aircraft coordinates.
- # Store the current values of each sub-dict in temporary variables
- temp_x_values = dict_ac_data['fuselage_section_origin_x'].values()
- temp_y_values = dict_ac_data['fuselage_section_origin_y'].values()
- temp_z_values = dict_ac_data['fuselage_section_origin_z'].values()
- # Update each dictionary's values by iterating over keys
- # Swap values: z -> x, y -> z, x -> y
- dict_ac_data['fuselage_section_origin_x'] = dict(zip(dict_ac_data['fuselage_section_origin_x'].keys(), temp_z_values))
- dict_ac_data['fuselage_section_origin_y'] = dict(zip(dict_ac_data['fuselage_section_origin_y'].keys(), temp_x_values))
- dict_ac_data['fuselage_section_origin_z'] = dict(zip(dict_ac_data['fuselage_section_origin_z'].keys(), temp_y_values))
-
- # Transform wing cgal coordinates to aircraft coordinates.
- # Store the current values of each sub-dict in temporary variables
- temp_y_values = dict_ac_data['wing_section_chord_origin_y'].values()
- temp_z_values = dict_ac_data['wing_section_chord_origin_z'].values()
- # Update each dictionary's values by iterating over keys
- # Swap values: z -> y, y -> z
- dict_ac_data['wing_section_chord_origin_y'] = dict(zip(dict_ac_data['wing_section_chord_origin_y'].keys(), temp_z_values))
- dict_ac_data['wing_section_chord_origin_z'] = dict(zip(dict_ac_data['wing_section_chord_origin_z'].keys(), temp_y_values))
-
- # Transform empennage cgal coordinates to aircraft coordinates.
- # Store the current values of each sub-dict in temporary variables
- temp_y_values = dict_ac_data['empennage_section_chord_origin_y'].values()
- temp_z_values = dict_ac_data['empennage_section_chord_origin_z'].values()
- # Update each dictionary's values by iterating over keys
- # Swap values: z -> y, y -> z
- dict_ac_data['empennage_section_chord_origin_y'] = dict(zip(dict_ac_data['empennage_section_chord_origin_y'].keys(), temp_z_values))
- dict_ac_data['empennage_section_chord_origin_z'] = dict(zip(dict_ac_data['empennage_section_chord_origin_z'].keys(), temp_y_values))
-
- """Check if tank design is feasible."""
- number_of_fuselages = len(dict_ac_data['fuselage_entity_position_x'].keys())
- if number_of_fuselages < 1:
- # If no fuselage is available, the tank design is impossible and the program aborted.
- runtime_output.critical('Error: Tank design not possible without fuselage! Program aborted.')
- sys.exit('Exit information: Tank design not possible without fuselage definition!')
- elif number_of_fuselages > 1:
- # If more than one fuselage is available, the tank design is impossible and the program aborted.
- runtime_output.critical('Error: Tank design not possible for more than one fuselage! Program aborted.')
- sys.exit('Exit information: Tank design not possible for more than one fuselage!')
-
- number_of_wings = len(dict_ac_data['wing_name'].keys())
- if number_of_wings < 1:
- # If no fuselage is available, the tank design is impossible and the program aborted.
- runtime_output.critical('Error: Tank design not possible without wing! Program aborted.')
- sys.exit('Exit information: Tank design not possible without wing definition!')
- elif number_of_wings > 1:
- # If more than one fuselage is available, the tank design is impossible and the program aborted.
- runtime_output.critical('Error: Tank design not possible for more than one wing! Program aborted.')
- sys.exit('Exit information: Tank design not possible for more than one wing!')
-
- """Run tank design preparation functions."""
- # Initialize local parameter.
- dict_tank_design = {}
- # Define function names and remove underscores.
- function_names = ['read_energy_carrier_and_tank_configuration', 'check_tank_configuration',
- 'prepare_geometrical_data']
- cleaned_function_names = [name.replace('_', '') for name in function_names]
-
- # If the script is compiled, sys._MEIPASS gives the temp directory for PyInstaller.
- if getattr(sys, 'frozen', False):
- # Read all python files from 'call_functions' directory, delete cache folder, and sort 'call_function_list'.
- call_function_list = os.listdir(sys._MEIPASS + '/'
- + routing_dict['module_import_name'].replace('.', '/') + '/general/call_functions')
- # If running as a regular Python script, use the current directory.
- else:
- # Read all python files from 'call_functions' directory, delete cache folder, and sort 'call_function_list'.
- call_function_list = os.listdir(paths_and_names['working_directory'] + '/'
- + routing_dict['module_import_name'].replace('.', '/') + '/general/call_functions')
-
- if '__pycache__' in call_function_list:
- call_function_list.remove('__pycache__')
- if '.DS_Store' in call_function_list:
- call_function_list.remove('.DS_Store')
- call_function_list = sorted(call_function_list, key=lambda x: (int(x.split('_')[1]), x))
-
- # Loop across all *.py files from 'call_functions' directory and find matching entries in 'function_names'.
- for call_function in call_function_list:
- try:
- # Generate function import string.
- import_call_function = (routing_dict['module_import_name']
- + '.general.call_functions.' + os.path.splitext(call_function)[0])
- # Extract function name from 'function_names' list.
- for idx, cleaned_name in enumerate(cleaned_function_names):
- # Check if the cleaned name is present in the 'call_function' string.
- if cleaned_name in call_function:
- function_name = function_names[idx]
- break
- # Import calculation module.
- module = importlib.import_module(import_call_function)
- dict_tank_design = getattr(module, function_name)(paths_and_names, dict_ac_data, dict_tank_design,
- runtime_output)
-
- # Exception handling for module import error.
- except ModuleNotFoundError as module_import_error:
- runtime_output.critical('Error: ' + str(module_import_error) + ' found in ' + routing_dict['module_name']
- + '. Program aborted.')
- sys.exit('Exit information: The own python module to be imported could not be found!')
-
- """Debug print."""
- runtime_output.debug('Debug: The "tank_design_tu_berlin" function was successfully executed.')
-
- return dict_tank_design
+"""Module providing calculating functions for the tank design of tube-and-wing aircraft according to TU Berlin."""
+# Import standard libraries.
+import importlib
+import os
+import sys
+import pycoordinatesystemconversion as py11csc
+import pyaixml as aixml
+import pyaircraftgeometry2 as geom2
+
+def tank_design_tu_berlin(paths_and_names, routing_dict, dict_ac_data, runtime_output):
+ """Tank design method for tube-and-wing aircraft.
+
+ The first step is to check whether the tank design is feasible. This applies if there is only one wing and one
+ fuselage. If this is true, the tank design method calls general (independent on energy carrier) functions for the
+ tank design of tube-and-wing aircraft.
+ The output dictionary 'dict_tank_design' contains the results of the tank design preparation. The output dictionary
+ is structured according to the following scheme:
+ dict_tank_design = {
+ 'tank_0': {...},
+ 'tank_1': {...},
+ ...
+ 'number_of_tanks': (int, number of tanks available),
+ 'tank_configuration': (str, name of tank configuration),
+ 'valid_tank_definition': (bool, information if tank configuration is valid),
+ 'geometry':{...}
+ }
+ The detailed structure of the sub dictionaries depends on the energy carrier and can be found in the docStrings of
+ the '_00_readenergycarrierandtankconfiguration.py' and '_01_preparegeometricaldata.py' files.
+
+ :param dict paths_and_names: Dictionary containing system paths and ElementTrees
+ :param dict routing_dict: Dictionary containing routing parameters
+ :param dict dict_ac_data: Dictionary containing data from aircraft exchange and module configuration file
+ :param logging.Logger runtime_output: Logging object used for capturing log messages in the module
+ :raises ModuleNotFoundError: Raised if calculation module not found
+ :return dict dict_tank_design: Dictionary containing tank design parameter
+ """
+ """ Extract aerodynamic surfaces values using the aircraftGeometry2 library."""
+ # Create the factory
+ airfoil_data_dir = f'{paths_and_names["project_directory"]}/geometryData/airfoilData'
+ aircraft_exchange_file = aixml.openDocument(paths_and_names['path_to_aircraft_exchange_file'])
+ factory = geom2.factory.WingFactory(aircraft_exchange_file, airfoil_data_dir)
+ # Create the surface
+ wing = factory.create("wing/specific/geometry/aerodynamic_surface@0")
+ horizontal_stabilizer = factory.create("empennage/specific/geometry/aerodynamic_surface@1")
+ # Extract wing y coordinates and thickness-to-length ratio.
+ thickness_to_length = []
+ for i in range(len(wing.sections)):
+ z = wing.sections[i].origin.z()
+ chord = geom2.measure.chord(wing, z)
+ thickness = geom2.measure.thickness_max(wing.sections[i])
+ thickness_to_length.append(thickness/chord)
+ dict_ac_data['wing_thickness_to_length'] = thickness_to_length
+
+ # Extract horizontal stabilizer y coordinates and thickness-to-length ratio.
+ thickness_to_length = []
+ for i in range(len(horizontal_stabilizer.sections)):
+ z = horizontal_stabilizer.sections[i].origin.z()
+ chord = geom2.measure.chord(horizontal_stabilizer, z)
+ thickness = geom2.measure.thickness_max(horizontal_stabilizer.sections[i])
+ thickness_to_length.append(thickness/chord)
+ dict_ac_data['horizontal_stabilizer_thickness_to_length'] = thickness_to_length
+
+ """Convert coordinates from CGAL to aircraft coordinate system."""
+ # List of parameters to be considered for CGAL to aircraft coordinate system conversion.
+ param_list = ["fuselage_position", "wing_position", "empennage_position", "fuselage_entity_position",
+ "fuselage_section_origin", "fuselage_payload_deck_origin", "wing_section_chord_origin",
+ "empennage_entity_position", "empennage_section_chord_origin"]
+
+ # for param in param_list:
+ # if dict_ac_data[param + "_x"] is not None:
+ # if type(dict_ac_data[param + "_x"]) != float:
+ # for key in dict_ac_data[param + "_x"].keys():
+ # index = key.split("_").index("x") + 1
+ # if dict_ac_data[param + "_x"][param + "_x_" + key.split("_", index)[-1]] is not None:
+ # element3D = py11csc.Element3D(dict_ac_data[param + "_x"][param + "_x_" + key.split("_", index)[-1]],
+ # dict_ac_data[param + "_y"][param + "_y_" + key.split("_", index)[-1]],
+ # dict_ac_data[param + "_z"][param + "_z_" + key.split("_", index)[-1]])
+ # element3D.CGAL2AC()
+ # dict_ac_data[param + "_x"][param + "_x_" + key.split("_", index)[-1]] = element3D.x()
+ # dict_ac_data[param + "_y"][param + "_y_" + key.split("_", index)[-1]] = element3D.y()
+ # dict_ac_data[param + "_z"][param + "_z_" + key.split("_", index)[-1]] = element3D.z()
+ # else:
+ # runtime_output.warning("WARNING: The parameter " + param + "_x is missing in the aircraft exchange file. No need to convert the coordinates.")
+ # else:
+ # element3D = py11csc.Element3D(dict_ac_data[param + "_x"],
+ # dict_ac_data[param + "_y"],
+ # dict_ac_data[param + "_z"])
+ # element3D.CGAL2AC()
+ # dict_ac_data[param + "_x"] = element3D.x()
+ # dict_ac_data[param + "_y"] = element3D.y()
+ # dict_ac_data[param + "_z"] = element3D.z()
+ # else:
+ # runtime_output.warning("WARNING: The parameter " + param + "_x is missing in the aircraft exchange file. No need to convert the coordinates.")
+
+ # Transform fuselage cgal coordinates to aircraft coordinates.
+ # Store the current values of each sub-dict in temporary variables
+ temp_x_values = dict_ac_data['fuselage_section_origin_x'].values()
+ temp_y_values = dict_ac_data['fuselage_section_origin_y'].values()
+ temp_z_values = dict_ac_data['fuselage_section_origin_z'].values()
+ # Update each dictionary's values by iterating over keys
+ # Swap values: z -> x, y -> z, x -> y
+ dict_ac_data['fuselage_section_origin_x'] = dict(zip(dict_ac_data['fuselage_section_origin_x'].keys(), temp_z_values))
+ dict_ac_data['fuselage_section_origin_y'] = dict(zip(dict_ac_data['fuselage_section_origin_y'].keys(), temp_x_values))
+ dict_ac_data['fuselage_section_origin_z'] = dict(zip(dict_ac_data['fuselage_section_origin_z'].keys(), temp_y_values))
+
+ # Transform wing cgal coordinates to aircraft coordinates.
+ # Store the current values of each sub-dict in temporary variables
+ temp_y_values = dict_ac_data['wing_section_chord_origin_y'].values()
+ temp_z_values = dict_ac_data['wing_section_chord_origin_z'].values()
+ # Update each dictionary's values by iterating over keys
+ # Swap values: z -> y, y -> z
+ dict_ac_data['wing_section_chord_origin_y'] = dict(zip(dict_ac_data['wing_section_chord_origin_y'].keys(), temp_z_values))
+ dict_ac_data['wing_section_chord_origin_z'] = dict(zip(dict_ac_data['wing_section_chord_origin_z'].keys(), temp_y_values))
+
+ # Transform empennage cgal coordinates to aircraft coordinates.
+ # Store the current values of each sub-dict in temporary variables
+ temp_y_values = dict_ac_data['empennage_section_chord_origin_y'].values()
+ temp_z_values = dict_ac_data['empennage_section_chord_origin_z'].values()
+ # Update each dictionary's values by iterating over keys
+ # Swap values: z -> y, y -> z
+ dict_ac_data['empennage_section_chord_origin_y'] = dict(zip(dict_ac_data['empennage_section_chord_origin_y'].keys(), temp_z_values))
+ dict_ac_data['empennage_section_chord_origin_z'] = dict(zip(dict_ac_data['empennage_section_chord_origin_z'].keys(), temp_y_values))
+
+ """Check if tank design is feasible."""
+ number_of_fuselages = len(dict_ac_data['fuselage_entity_position_x'].keys())
+ if number_of_fuselages < 1:
+ # If no fuselage is available, the tank design is impossible and the program aborted.
+ runtime_output.critical('Error: Tank design not possible without fuselage! Program aborted.')
+ sys.exit('Exit information: Tank design not possible without fuselage definition!')
+ elif number_of_fuselages > 1:
+ # If more than one fuselage is available, the tank design is impossible and the program aborted.
+ runtime_output.critical('Error: Tank design not possible for more than one fuselage! Program aborted.')
+ sys.exit('Exit information: Tank design not possible for more than one fuselage!')
+
+ number_of_wings = len(dict_ac_data['wing_name'].keys())
+ if number_of_wings < 1:
+ # If no wing is available, the tank design is impossible and the program aborted.
+ runtime_output.critical('Error: Tank design not possible without wing! Program aborted.')
+ sys.exit('Exit information: Tank design not possible without wing definition!')
+ elif number_of_wings > 1:
+ # If more than one wing is available, the tank design is impossible and the program aborted.
+ runtime_output.critical('Error: Tank design not possible for more than one wing! Program aborted.')
+ sys.exit('Exit information: Tank design not possible for more than one wing!')
+
+ """Run tank design preparation functions."""
+ # Initialize local parameter.
+ dict_tank_design = {}
+ # Define function names and remove underscores.
+ function_names = ['read_energy_carrier_and_tank_configuration', 'check_tank_configuration',
+ 'prepare_geometrical_data']
+ cleaned_function_names = [name.replace('_', '') for name in function_names]
+
+ # If the script is compiled, sys._MEIPASS gives the temp directory for PyInstaller.
+ if getattr(sys, 'frozen', False):
+ # Read all python files from 'call_functions' directory, delete cache folder, and sort 'call_function_list'.
+ call_function_list = os.listdir(sys._MEIPASS + '/'
+ + routing_dict['module_import_name'].replace('.', '/') + '/general/call_functions')
+ # If running as a regular Python script, use the current directory.
+ else:
+ # Read all python files from 'call_functions' directory, delete cache folder, and sort 'call_function_list'.
+ call_function_list = os.listdir(paths_and_names['working_directory'] + '/'
+ + routing_dict['module_import_name'].replace('.', '/') + '/general/call_functions')
+
+ if '__pycache__' in call_function_list:
+ call_function_list.remove('__pycache__')
+ if '.DS_Store' in call_function_list:
+ call_function_list.remove('.DS_Store')
+ call_function_list = sorted(call_function_list, key=lambda x: (int(x.split('_')[1]), x))
+
+ # Loop across all *.py files from 'call_functions' directory and find matching entries in 'function_names'.
+ for call_function in call_function_list:
+ try:
+ # Generate function import string.
+ import_call_function = (routing_dict['module_import_name']
+ + '.general.call_functions.' + os.path.splitext(call_function)[0])
+ # Extract function name from 'function_names' list.
+ for idx, cleaned_name in enumerate(cleaned_function_names):
+ # Check if the cleaned name is present in the 'call_function' string.
+ if cleaned_name in call_function:
+ function_name = function_names[idx]
+ break
+ # Import calculation module.
+ module = importlib.import_module(import_call_function)
+ dict_tank_design = getattr(module, function_name)(paths_and_names, dict_ac_data, dict_tank_design,
+ runtime_output)
+
+ # Exception handling for module import error.
+ except ModuleNotFoundError as module_import_error:
+ runtime_output.critical('Error: ' + str(module_import_error) + ' found in ' + routing_dict['module_name']
+ + '. Program aborted.')
+ sys.exit('Exit information: The own python module to be imported could not be found!')
+
+ """Debug print."""
+ runtime_output.debug('Debug: The "tank_design_tu_berlin" function was successfully executed.')
+
+ return dict_tank_design
diff --git a/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/kerosene/calculatetanks.py b/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/kerosene/calculatetanks.py
index b2e2e982096c4d65fc65da00d989ab68b267f95a..b95bba00108caf1d1f4a6dd438b5df4541c35e66 100644
--- a/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/kerosene/calculatetanks.py
+++ b/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/kerosene/calculatetanks.py
@@ -1,1010 +1,1475 @@
-""" Module containing functions for kerosene tank calculation. """
-# Import standard libraries.
-import sys
-import math
-import numpy as np
-
-
-def calculate_tank_span(span_index_inner_surface, span_index_outer_surface):
- """Tank span in m.
-
- Span index equals position in mm.
-
- :param int span_index_inner_surface: Index of span position of inner surface
- :param int span_index_outer_surface: Index of span position of outer surface
- :return float: Tank span in m
- """
- tank_span = (span_index_outer_surface - span_index_inner_surface)/100
-
- return tank_span
-
-
-def calculate_obelisk_volume(method, dict_wing_geometry, inner_surface_str, outer_surface_str):
- """Calculate geometrical volume of obelisk.
-
- This function calculates the obelisk volume according to the selected method (Torenbeek [1] or Simpson).
-
- [1] E. Torenbeek "Synthesis of Subsonic Airplane Design" (1982), Fig. B-4 [1]
-
- :param str method: Calculation method name
- :param dict dict_wing_geometry: Dictionary containing wing geometry parameters
- :param str inner_surface_str: Name of inner obelisk surface
- :param str outer_surface_str: Name of outer obelisk surface
- :return float: Volume of obelisk in m^3
- """
- interpolated_values = dict_wing_geometry['interpolated_values']
-
- inner_span_index = abs(dict_wing_geometry['sections'][inner_surface_str]['span_index'])
- outer_span_index = abs(dict_wing_geometry['sections'][outer_surface_str]['span_index'])
- tank_span = (outer_span_index - inner_span_index)/100
- maximum_tank_height_inner = interpolated_values['tank_heights'][inner_span_index]
- maximum_tank_height_outer = interpolated_values['tank_heights'][outer_span_index]
- maximum_tank_length_inner = interpolated_values['tank_lengths'][inner_span_index]
- maximum_tank_length_outer = interpolated_values['tank_lengths'][outer_span_index]
- area_inner = maximum_tank_height_inner*maximum_tank_length_inner
- area_outer = maximum_tank_height_outer*maximum_tank_length_outer
-
- match method:
- case 'Torenbeek':
- # Calculate volume of obelisk according to Torenbeek.
- obelisk_volume = (tank_span/3*(area_inner + area_outer
- + ((maximum_tank_height_inner*maximum_tank_length_outer)
- + (maximum_tank_length_inner*maximum_tank_height_outer))/2))
- case 'Simpson':
- # Calculate volume of obelisk according to Simpson's rule.
- middle_area = (area_inner + area_outer)/2
- obelisk_volume = tank_span / 6.0 * (area_inner + 4.0 * middle_area + area_outer)
-
- return obelisk_volume
-
-
-def calculate_kerosene_tanks(dict_ac_data, dict_tank_design, runtime_output):
- """Calculate kerosene tanks of tube-and-wing aircraft.
-
- This function adds the following sub dictionaries to the 'dict_tank_design' dictionary:
- ...
-
- :param dict dict_ac_data: Dictionary containing data from aircraft exchange and module configuration file
- :param dict dict_tank_design: Dictionary containing tank design parameter
- :param logging.Logger runtime_output: Logging object used for capturing log messages in the module
- :return dict dict_tank_design: Dictionary containing tank design parameter
- """
- # Extract data and initialize variables.
- total_tank_energy = 0
- additional_tank_energy = 0
- wing_tank_energy_without_wing_center_tank = 0
-
- """Check if initial sizing loop and estimate energy demand if necessary."""
- initial_sizing_loop = all(value is None for value in dict_ac_data['mission_energy_amount'].values())
- if initial_sizing_loop:
- runtime_output.print('Initial sizing loop! Energy demand is estimated (3.5 liters per PAX per 100 km).')
- energy_demand = 3.35 # in liter per passenger
- mission_fuel_amount = dict_ac_data['number_of_passengers']*dict_ac_data['range']/1000*energy_demand/100
- mission_energy_amount = (mission_fuel_amount/1000*
- dict_ac_data['kerosene_volumetric_energy_density'])
- else:
- mission_energy_amount = dict_ac_data['mission_energy_amount']['mission_energy_amount_ID0']
-
- """ Calculate wing tank volume. """
- # Wing tank volume must be calculated for all possible tank configurations.
- dict_tank_design = calculate_wing_tanks(dict_ac_data, dict_tank_design, runtime_output, mission_energy_amount)
- total_tank_energy += dict_tank_design['tmp_energies']['wing_tank_with_center_tank']
- wing_tank_energy_without_wing_center_tank += dict_tank_design['tmp_energies']['wing_tank_without_center_tank']
- # Check if wing tanks can store mission energy amount.
- if wing_tank_energy_without_wing_center_tank >= mission_energy_amount:
- runtime_output.print('Wing center tank created but unnecessary and remains empty.')
- energy_demand_covered = True
- elif total_tank_energy >= mission_energy_amount:
- runtime_output.print('Wing center tank necessary.')
- energy_demand_covered = True
- else:
- energy_demand_covered = False
-
- """ Print information or calculate other fuel tanks. """
- if energy_demand_covered:
- # Energy amount that can be stored in wing tanks already covers mission energy amount. All other tanks are
- # generated but remain empty ('volume_available' and 'energy_available' are 0).
- match dict_tank_design['tank_configuration']:
- case 'wing_with_trim_tank':
- runtime_output.print('Trim tank is generated but unnecessary and remains empty.')
- case 'wing_with_additional_center_tank':
- runtime_output.print('Additional center tank is generated but unnecessary and remains empty.')
- case 'wing_with_additional_center_and_trim_tank':
- runtime_output.print('Trim and additional center tanks are generated but unnecessary and '
- + 'remain empty.')
- else:
- # If energy amount not covered by wing tanks: Calculate other fuel tanks (depending on tank configuration).
- # Calculate additional tank volumes according to defined tank configuration.
- match dict_tank_design['tank_configuration']:
- case 'wing_with_trim_tank':
- dict_tank_design = calculate_trim_tank(dict_ac_data, dict_tank_design, runtime_output)
- total_tank_energy += dict_tank_design['tmp_energies']['trim_tank']
- if total_tank_energy >= mission_energy_amount:
- energy_demand_covered = True
- case 'wing_with_additional_center_tank':
- dict_tank_design = calculate_additional_center_tank(dict_ac_data, dict_tank_design, runtime_output)
- total_tank_energy += (
- dict_tank_design['tmp_energies']['additional_center_tank'])
- if total_tank_energy >= mission_energy_amount:
- energy_demand_covered = True
- case 'wing_with_additional_center_and_trim_tank':
- dict_tank_design = calculate_trim_tank(dict_ac_data, dict_tank_design, runtime_output)
- total_tank_energy += dict_tank_design['tmp_energies']['trim_tank']
- if total_tank_energy >= mission_energy_amount:
- energy_demand_covered = True
- runtime_output.print('Additional center tank is generated but unnecessary and remains empty.')
- else:
- dict_tank_design = calculate_additional_center_tank(dict_ac_data, dict_tank_design, runtime_output)
- additional_tank_energy += dict_tank_design['tmp_energies']['additional_center_tank']
- total_tank_energy += additional_tank_energy
- if total_tank_energy >= mission_energy_amount:
- energy_demand_covered = True
-
- # Final check if tanks can store mission energy amount.
- if energy_demand_covered:
- runtime_output.print('Tank design successful.')
- else:
- energy_missing = mission_energy_amount - total_tank_energy
- volume_missing = energy_missing/dict_ac_data['kerosene_volumetric_energy_density']
- runtime_output.print('Attention: Necessary amount of fuel cannot be stored in selected tanks! '
- + str(int(round(energy_missing,0))) + 'J (' + str(round(volume_missing,2)) +
- 'L) missing.')
-
- """ Calculate total tank parameters. """
- dict_tank_design['total_tank_parameters'] = {}
- # Tank mass (integral tank -> equals zero).
- dict_tank_design['total_tank_parameters']['mass'] = 0.0
- # Tank position.
- dict_tank_design['total_tank_parameters']['position'] = {}
- dict_tank_design['total_tank_parameters']['position']['x'] = (
- dict_tank_design['geometry']['wing']['position']['x'])
- dict_tank_design['total_tank_parameters']['position']['y'] = (
- dict_tank_design['geometry']['wing']['position']['y'])
- dict_tank_design['total_tank_parameters']['position']['z'] = (
- dict_tank_design['geometry']['wing']['position']['z'])
- # Inertia (are set to zero).
- inertia_list = ['j_xx', 'j_yy', 'j_zz', 'j_xy', 'j_xz', 'j_yx', 'j_yz', 'j_zx', 'j_zy']
- dict_tank_design['total_tank_parameters']['inertia'] = {}
- for inertia in inertia_list:
- dict_tank_design['total_tank_parameters']['inertia'][inertia] = 0.0
- # Center of gravity (equals zero since integral tank has no mass).
- dict_tank_design['total_tank_parameters']['center_of_gravity'] = {}
- dict_tank_design['total_tank_parameters']['center_of_gravity']['x'] = 0.0
- dict_tank_design['total_tank_parameters']['center_of_gravity']['y'] = 0.0
- dict_tank_design['total_tank_parameters']['center_of_gravity']['z'] = 0.0
-
- # Additional fuselage length equals zero for kerosene driven aircraft.
- dict_tank_design['total_tank_parameters']['additional_fuselage_length'] = 0.0
-
- # Prints.
- runtime_output.debug('Debug: The "calculate_tanks" function was successfully executed.')
-
- return dict_tank_design
-
-
-def calculate_wing_tanks(dict_ac_data, dict_tank_design, runtime_output, mission_energy_amount):
- """Calculate energy contained in wing tanks.
-
- In the first step, the volume of the obelisks (according to Torenbeek or Simpson) is calculated for every given
- tank entity. Afterwards, the actual tank volume is calculated, considering volume loss due to internal structure
- of integral tanks and buffer for temperature-dependent expansion of fuel. All the volumes are summed up
- ('volume_obelisks_without_center_tank'), except for the center tank volume that is saved in a separate parameter
- ('volume_obelisk_center_tank'). The energy contained in the tank can than be calculated by multiplying the actual
- volume with the volumetric energy density of kerosene.
- Finally it is checked if the wing center tank is necessary. If the left and right inner and outer wing tanks are
- big enough to store the energy required, the wing center tank values are set to zero.
-
- :param dict dict_design: Dictionary containing data from aircraft exchange and module configuration file
- :param dict dict_tank_design: Dictionary containing tank design parameter
- :param logging.Logger runtime_output: Logging object used for capturing log messages in the module
- :param float mission_energy_amount: Mission energy amount in Joule
- :return dict dict_tank_design: Dictionary containing tank design parameter
- """
- # Extract necessary data from 'dict_ac_data'.
- factor_volume_usable = dict_ac_data['factor_volume_usable']
- # Since a vent tank is considered, no temperature expansion allowance has to be considered for wing tanks.
- temperature_expansion_allowance = 1.0
-
- wing_geometry_dict = dict_tank_design['geometry']['wing']
- wing_section_dict = dict_tank_design['geometry']['wing']['sections']
- wing_symmetry = dict_tank_design['geometry']['wing']['information']['wing_symmetry']
-
- # Get all tank entities that are located at the wing.
- wing_tank_entity_list = [k for k, v in dict_tank_design.items()
- if k.startswith('tank_') and k[5:].isdigit() and v['tank_location'] == 'wing']
- wing_center_tank_entity = [k for k in wing_tank_entity_list
- if dict_tank_design[k]['tank_position'].endswith('center')][0]
- # Calculate distance from wing root to wing tip.
- distance_wing_root_to_tip = (wing_section_dict['wing_tip']['position']['y']
- - wing_section_dict['wing_root']['position']['y'])
- # Calculate span offset for tank sections.
- center_tank_span_offset = -(wing_section_dict['wing_root']['position']['y']*
- dict_ac_data['buffer_center_tank_segment'])
- inner_wing_tank_span_offset = distance_wing_root_to_tip*dict_ac_data['buffer_inner_tank_segment']
- kink_section_span_offset = 0.0
- outer_vent_tank_span_offset = -(distance_wing_root_to_tip*dict_ac_data['buffer_outer_tank_segment'])
-
- # Set tank sections according to number of wing sections.
- number_of_wing_sections = len(wing_section_dict)
- if number_of_wing_sections < 3:
- runtime_output.critical('Error: Not enough wing sections given. '
- + 'Program aborted.')
- sys.exit(1)
- elif number_of_wing_sections == 3:
- sections = {'outer_center_tank_section': 'wing_root',
- 'section_0': 'wing_root',
- 'section_1': 'wing_tip',
- 'outer_vent_tank_section': 'wing_tip'}
- vent_tank_inner_surface = 'section_1'
- # Span offsets for 'center_tank', 'section_0', 'section_1', and 'outer_vent_tank_section'.
- span_offset_list = [center_tank_span_offset, inner_wing_tank_span_offset, kink_section_span_offset,
- outer_vent_tank_span_offset]
- elif number_of_wing_sections == 4:
- sections = {'outer_center_tank_section': 'wing_root',
- 'section_0': 'wing_root',
- 'section_1': 'kink',
- 'section_2': 'wing_tip',
- 'outer_vent_tank_section': 'wing_tip'}
- vent_tank_inner_surface = 'section_2'
- # Span offsets for 'center_tank', 'section_0', 'section_1', 'section_2', and 'outer_vent_tank_section'.
- span_offset_list = [center_tank_span_offset, inner_wing_tank_span_offset, kink_section_span_offset,
- outer_vent_tank_span_offset, outer_vent_tank_span_offset]
- else:
- runtime_output.critical('Error: Too many wing sections given. '
- + 'Program aborted.')
- sys.exit(1)
-
- # Prepare tank sections.
- i = 0
- for sec, template in sections.items():
- wing_section_dict[sec] = {}
- wing_section_dict[sec]['position'] = {}
- wing_section_dict[sec]['position']['y'] = (
- wing_section_dict[template]['position']['y'] + span_offset_list[i])
- wing_section_dict[sec]['span_index'] = abs(int(round(
- wing_section_dict[sec]['position']['y']*100, 0)))
- wing_section_dict[sec]['position']['x'] = (
- wing_geometry_dict['interpolated_values']['x_coordinate_leading_edge']
- [wing_section_dict[sec]['span_index']])
- wing_section_dict[sec]['position']['z'] = (
- #wing_section_dict[template]['position']['z'])
- wing_geometry_dict['interpolated_values']['z_coordinate_leading_edge']
- [wing_section_dict[sec]['span_index']])
- # span_index = wing_section_dict[sec]['span_index']
- i += 1
-
- """Calculate vent tank."""
- # Add vent tank to tank design dict.
- dict_tank_design['vent_tank'] = {}
- dict_tank_design['vent_tank']['tank_location'] = 'wing'
- dict_tank_design['vent_tank']['tank_position'] = 'vent'
- # CS 25.969: Vent tank capacity must at least be equal to 2 percent of tank capacity (1 percent per side).
- dict_tank_design['vent_tank']['energy_required'] = 0.01*mission_energy_amount
- vent_tank_outer_surface = 'outer_vent_tank_section'
-
- # Calculate energy contained in vent tank iteratively. Position of inner surface is adjusted in 1 mm steps.
- vent_tank_energy = 0
- while vent_tank_energy < dict_tank_design['vent_tank']['energy_required']:
- vent_tank_volume = calculate_obelisk_volume(dict_ac_data['obelisk_volume_calculation_method'],
- wing_geometry_dict,
- vent_tank_inner_surface, vent_tank_outer_surface)
- vent_tank_volume_actual = factor_volume_usable*temperature_expansion_allowance*vent_tank_volume
- vent_tank_energy = vent_tank_volume_actual*dict_ac_data['kerosene_volumetric_energy_density']
- wing_section_dict[vent_tank_inner_surface]['span_index'] -= 1
-
- # Update x position of 'section_2' aka. 'vent_tank_inner_surface'.
- span_idx = wing_section_dict[vent_tank_inner_surface]['span_index']
- wing_section_dict[vent_tank_inner_surface]['position']['x'] = (
- wing_geometry_dict['interpolated_values']['x_coordinate_leading_edge'][span_idx])
- wing_section_dict[vent_tank_inner_surface]['position']['y'] = span_idx/100
-
- # TODO: Eventuell löschen, wenn plot nicht mehr benötigt.
- dict_tank_design['vent_tank']['geometry'] = {}
- dict_tank_design['vent_tank']['geometry']['total'] = {}
- dict_tank_design['vent_tank']['geometry']['total']['position'] = {}
- dict_tank_design['vent_tank']['geometry']['total']['position']['x'] = (
- wing_geometry_dict['interpolated_values']['x_coordinate_front_spar'][span_idx])
- dict_tank_design['vent_tank']['geometry']['total']['position']['y'] = (
- wing_section_dict[vent_tank_inner_surface]['position']['y'])
- dict_tank_design['vent_tank']['geometry']['inner_surface'] = {}
- dict_tank_design['vent_tank']['geometry']['inner_surface']['width'] = (
- wing_geometry_dict['interpolated_values']['tank_lengths'][span_idx])
- dict_tank_design['vent_tank']['volume_available'] = vent_tank_volume_actual
- dict_tank_design['vent_tank']['energy_available'] = vent_tank_energy
-
- """Calculate tank volumes (wing geometry does not change from here)."""
- # Initialize parameter.
- actual_volume_center_tank = 0
- actual_volume_without_center_tank = 0
-
- # Iterate through tank entities.
- wing_tank_entity_list = [key for key, value in dict_tank_design.items() if key.startswith('tank_')
- and key[5:].isdigit() and value['tank_location'] == 'wing']
- for wing_tank_entity in wing_tank_entity_list:
- # Initialize empty dictionary and lists.
- dict_tank_design[wing_tank_entity]['geometry'] = {}
- dict_tank_design[wing_tank_entity]['geometry']['inner_surface'] = {}
- dict_tank_design[wing_tank_entity]['geometry']['outer_surface'] = {}
- inner_surface_str = str()
- outer_surface_str = str()
-
- if wing_symmetry:
- if number_of_wing_sections == 4:
- # Set sections depending on tank position.
- match dict_tank_design[wing_tank_entity]['tank_position']:
- case 'inner_left' | 'inner_right':
- inner_surface_str = 'section_0'
- outer_surface_str = 'section_1'
- case 'outer_left' | 'outer_right':
- inner_surface_str = 'section_1'
- outer_surface_str = 'section_2'
- case 'center':
- inner_surface_str = 'fuselage_center_line'
- outer_surface_str = 'outer_center_tank_section'
- else:
- runtime_output.critical('Error: Wing without kink not implemented yet! Program aborted.')
- sys.exit(1)
- else:
- runtime_output.critical('Error: Wing not symmetric! '
- + 'Program aborted.')
- sys.exit(1)
-
- # Calculate obelisk volume.
- obelisk_volume = calculate_obelisk_volume(dict_ac_data['obelisk_volume_calculation_method'],
- wing_geometry_dict, inner_surface_str, outer_surface_str)
- # Calculate actual tank volume (considering volume loss due to internal structure of integral tanks and buffer
- # for temperature-dependent expansion of fuel).
- if dict_tank_design[wing_tank_entity]['tank_position'] == 'center':
- obelisk_volume *= 2
- actual_volume = factor_volume_usable*temperature_expansion_allowance*obelisk_volume
- # Sum up volume of all tanks except wing center tank.
- if dict_tank_design[wing_tank_entity]['tank_position'] != 'center':
- actual_volume_without_center_tank += actual_volume
- # Set volume of wing center tank.
- else:
- actual_volume_center_tank = actual_volume
-
- # Write data to 'dict_tank_design'.
- dict_tank_design[wing_tank_entity]['volume_available'] = actual_volume
- dict_tank_design[wing_tank_entity]['energy_available'] = (
- actual_volume*dict_ac_data['kerosene_volumetric_energy_density'])
-
- # # Add required output data: x, y, and z position, shape, height, width, and length.
- # for surface_str, surface_name in zip([inner_surface_str, outer_surface_str],
- # ['inner_surface', 'outer_surface']):
- # surface_data = wing_section_dict[surface_str]
- # span_idx = surface_data['span_index']
-
- # # Extract x and z coordinates.
- # x_coordinate = wing_geometry_dict['interpolated_values']['x_coordinate_front_spar'][span_idx]
- # z_coordinate = surface_data['position']['z']
-
- # # Adjust y coordinate for left hand tanks.
- # y_coordinate = surface_data['position']['y']
- # if 'left' in dict_tank_design[wing_tank_entity]['tank_position']:
- # y_coordinate = -(surface_data['position']['y'])
-
- # dict_tank_design[wing_tank_entity]['geometry'][surface_name] = {
- # 'section_name': surface_str,
- # 'position': {
- # 'x': x_coordinate,
- # 'y': y_coordinate,
- # 'z': z_coordinate,
- # },
- # 'shape': 'rectangular',
- # 'height': wing_geometry_dict['interpolated_values']['tank_heights'][span_idx],
- # 'width': wing_geometry_dict['interpolated_values']['tank_lengths'][span_idx],
- # 'length': 0.0
- # }
-
- # # Correct wing center tank information.
- # if 'center' in dict_tank_design[wing_tank_entity]['tank_position']:
- # dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['position']['y'] = (
- # dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['position']['y']
- # )
- # dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['position']['y'] = -(
- # dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['position']['y']
- # )
-
- # Calculate tank mass (equals zero due to integral tank).
- dict_tank_design[wing_tank_entity]['geometry']['total'] = {}
- dict_tank_design[wing_tank_entity]['geometry']['total']['mass'] = 0.0
- # Set inertia to zero.
- inertia_list = ['j_xx', 'j_yy', 'j_zz', 'j_xy', 'j_xz', 'j_yx', 'j_yz', 'j_zx', 'j_zy']
- dict_tank_design[wing_tank_entity]['geometry']['total']['inertia'] = {}
- for inertia in inertia_list:
- dict_tank_design[wing_tank_entity]['geometry']['total']['inertia'][inertia] = 0.0
- # Center of gravity equals zero since integral tank has no mass.
- dict_tank_design[wing_tank_entity]['geometry']['total']['center_of_gravity'] = {}
- dict_tank_design[wing_tank_entity]['geometry']['total']['center_of_gravity']['x'] = 0.0
- dict_tank_design[wing_tank_entity]['geometry']['total']['center_of_gravity']['y'] = 0.0
- dict_tank_design[wing_tank_entity]['geometry']['total']['center_of_gravity']['z'] = 0.0
-
- # Calculate position of tank entity (foremost point of tank).
- dict_tank_design[wing_tank_entity]['geometry']['total']['position'] = {}
- dict_tank_design[wing_tank_entity]['geometry']['total']['position']['x'] = (
- wing_geometry_dict['interpolated_values']['x_coordinate_front_spar'][
- wing_section_dict[inner_surface_str]['span_index']
- ])
- if (dict_tank_design[wing_tank_entity]['tank_position'] == 'inner_left') or (
- dict_tank_design[wing_tank_entity]['tank_position'] == 'outer_left'):
- dict_tank_design[wing_tank_entity]['geometry']['total']['position']['y'] = -abs(
- wing_section_dict[inner_surface_str]['position']['y'])
- else:
- dict_tank_design[wing_tank_entity]['geometry']['total']['position']['y'] = abs(
- wing_section_dict[inner_surface_str]['position']['y'])
- dict_tank_design[wing_tank_entity]['geometry']['total']['position']['z'] = (
- wing_section_dict[inner_surface_str]['position']['z'])
- # Direction.
- dict_tank_design[wing_tank_entity]['geometry']['total']['direction'] = {}
- dict_tank_design[wing_tank_entity]['geometry']['total']['direction']['x'] = 0
- dict_tank_design[wing_tank_entity]['geometry']['total']['direction']['y'] = 1
- dict_tank_design[wing_tank_entity]['geometry']['total']['direction']['z'] = 0
-
- # Add required output data: x, y, and z position, shape, height, width, and length.
- for surface_str, surface_name in zip([inner_surface_str, outer_surface_str],
- ['inner_surface', 'outer_surface']):
- surface_data = wing_section_dict[surface_str]
- span_idx = surface_data['span_index']
- # Inner surface equals tank entity position.
- if surface_name == 'inner_surface':
- x_coordinate = 0.0
- y_coordinate = 0.0
- z_coordinate = 0.0
- else:
- # Adjust y coordinate for left hand tanks.
- y_coordinate_entity = dict_tank_design[wing_tank_entity]['geometry']['total']['position']['y']
- if 'left' in dict_tank_design[wing_tank_entity]['tank_position']:
- y_coordinate_section = -surface_data['position']['y']
- else:
- y_coordinate_section = surface_data['position']['y']
- y_coordinate = y_coordinate_section - y_coordinate_entity
- # if 'left' in dict_tank_design[wing_tank_entity]['tank_position']:
- # y_coordinate = y_coordinate*(-1)
- # x coordinate.
- x_coordinate_entity = dict_tank_design[wing_tank_entity]['geometry']['total']['position']['x']
- x_coordinate_section = wing_geometry_dict['interpolated_values']['x_coordinate_front_spar'][span_idx]
- if x_coordinate_entity < 0 and x_coordinate_section > 0 and x_coordinate_section > x_coordinate_entity:
- delta_x = x_coordinate_entity - x_coordinate_section
- else:
- delta_x = x_coordinate_section - x_coordinate_entity
- # if x_coordinate_section < 0 and x_coordinate_section < x_coordinate_entity:
- # delta_x = x_coordinate_section - x_coordinate_entity
- # elif x_coordinate_section > 0 and x_coordinate_section < x_coordinate_entity:
- # delta_x = x_coordinate_entity - x_coordinate_section
- # elif x_coordinate_section > 0 and x_coordinate_entity == 0:
- # delta_x = x_coordinate_section - x_coordinate_entity
- # elif x_coordinate_section > x_coordinate_entity:
- # delta_x = x_coordinate_entity - x_coordinate_section
- # else:
- # delta_x = 0
- x_coordinate = delta_x
- # z coordinate.
- z_coordinate_entity = dict_tank_design[wing_tank_entity]['geometry']['total']['position']['z']
- z_coordinate_section = surface_data['position']['z']
- # if z_coordinate_section < 0 and z_coordinate_section < z_coordinate_entity:
- # delta_z = z_coordinate_section - z_coordinate_entity
- # elif z_coordinate_section > 0 and z_coordinate_section < z_coordinate_entity:
- # delta_z = z_coordinate_entity - z_coordinate_section
- # elif z_coordinate_section > 0 and z_coordinate_entity == 0:
- # delta_z = z_coordinate_section - z_coordinate_entity
- # elif z_coordinate_section > z_coordinate_entity:
- # delta_z = z_coordinate_entity - z_coordinate_section
- # else:
- # delta_z = 0
- z_coordinate = z_coordinate_section - z_coordinate_entity
-
- dict_tank_design[wing_tank_entity]['geometry'][surface_name] = {
- 'section_name': surface_str,
- 'position': {
- 'x': x_coordinate,
- 'y': y_coordinate,
- 'z': z_coordinate,
- },
- 'shape': 'rectangular',
- 'height': wing_geometry_dict['interpolated_values']['tank_heights'][span_idx],
- 'width': wing_geometry_dict['interpolated_values']['tank_lengths'][span_idx],
- 'length': 0.0
- }
-
- # Correct wing center tank information.
- if 'center' in dict_tank_design[wing_tank_entity]['tank_position']:
- dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['position']['y'] = (
- dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['position']['y']/2
- )
- dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['position']['y'] = -(
- dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['position']['y']
- )
-
- # Extract x and z coordinates.
- # x_coordinate = wing_geometry_dict['interpolated_values']['x_coordinate_front_spar'][span_idx]
- # z_coordinate = surface_data['position']['z']
-
- # # Adjust y coordinate for left hand tanks.
- # y_coordinate = surface_data['position']['y']
- # if 'left' in dict_tank_design[wing_tank_entity]['tank_position']:
- # y_coordinate = -(surface_data['position']['y'])
-
- # dict_tank_design[wing_tank_entity]['geometry'][surface_name] = {
- # 'section_name': surface_str,
- # 'position': {
- # 'x': x_coordinate,
- # 'y': y_coordinate,
- # 'z': z_coordinate,
- # },
- # 'shape': 'rectangular',
- # 'height': wing_geometry_dict['interpolated_values']['tank_heights'][span_idx],
- # 'width': wing_geometry_dict['interpolated_values']['tank_lengths'][span_idx],
- # 'length': 0.0
- # }
-
- # Centroid.
- # Assumption: inner surface area always greater than outer surface area.
- inner_surface_area = (dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['height']
- *dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['width'])
- outer_surface_area = (dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['height']
- *dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['width'])
- y_position_outer_surface = dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['position']['y']
- y_position_inner_surface = dict_tank_design[wing_tank_entity]['geometry']['total']['position']['y']
- tank_span = y_position_outer_surface - y_position_inner_surface
- y_position_center_of_mass = y_position_inner_surface + (tank_span/4*((inner_surface_area
- + 2*math.sqrt(inner_surface_area*outer_surface_area)
- + outer_surface_area)/(inner_surface_area + outer_surface_area)))
- centroid_y = y_position_inner_surface + ((tank_span
- *((dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['height']
- *dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['width'])
- +(dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['height']
- *dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['width'])
- +(dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['height']
- *dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['width'])
- +(3*dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['height']
- *dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['width'])))
- /(2
- *(2*dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['height']
- *dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['width'])
- + (dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['height']
- *dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['width'])
- + (dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['height']
- *dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['width'])
- + (2*dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['height']
- *dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['width'])))
- x_position_cog_inner_surface = dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['width']/2
- x_position_cog_outer_surface = dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['width']/2
- z_position_cog_inner_surface = dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['height']/2
- z_position_cog_outer_surface = dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['height']/2
- x_position_center_of_mass = ((inner_surface_area*x_position_cog_inner_surface
- + outer_surface_area*x_position_cog_outer_surface)
- /(inner_surface_area + outer_surface_area))
- z_position_center_of_mass = ((inner_surface_area*z_position_cog_inner_surface
- + outer_surface_area*z_position_cog_outer_surface)
- /(inner_surface_area + outer_surface_area))
-
- dict_tank_design[wing_tank_entity]['geometry']['total']['centroid'] = {}
- if wing_tank_entity == wing_center_tank_entity:
- dict_tank_design[wing_tank_entity]['geometry']['total']['centroid']['x'] = x_position_center_of_mass
- # dict_tank_design[wing_tank_entity]['geometry']['total']['centroid']['x'] = (
- # dict_tank_design['tank_4']['geometry']['inner_surface']['position']['x']
- # + dict_tank_design['tank_4']['geometry']['inner_surface']['width']/2
- # )
- dict_tank_design[wing_tank_entity]['geometry']['total']['centroid']['y'] = 0
- dict_tank_design[wing_tank_entity]['geometry']['total']['centroid']['z'] = 0
- else:
- dict_tank_design[wing_tank_entity]['geometry']['total']['centroid']['x'] = x_position_center_of_mass
- dict_tank_design[wing_tank_entity]['geometry']['total']['centroid']['y'] = y_position_center_of_mass
- dict_tank_design[wing_tank_entity]['geometry']['total']['centroid']['z'] = z_position_center_of_mass
-
- # Sum up.
- volume_wing_tank_without_center_tank = actual_volume_without_center_tank
- volume_wing_tank_with_center_tank = actual_volume_without_center_tank + actual_volume_center_tank
-
- """Calculate fuel mass and energy."""
- # Convert wing fuel volume to energy.
- energy_wing_tank_without_center_tank = (volume_wing_tank_without_center_tank
- *dict_ac_data['kerosene_volumetric_energy_density'])
- energy_wing_tank_with_center_tank = (volume_wing_tank_with_center_tank
- *dict_ac_data['kerosene_volumetric_energy_density'])
-
- """Check if tanks can store required energy."""
- # If left and right inner and outer wing tanks are big enough to store required amount of energy, wing center tank
- # remains empty.
- if energy_wing_tank_without_center_tank >= mission_energy_amount:
- dict_tank_design[wing_center_tank_entity]['volume_available'] = 0
- dict_tank_design[wing_center_tank_entity]['energy_available'] = 0
-
- # Debug print.
- runtime_output.debug('Debug: The "calculate_wing_tanks" function was successfully executed.')
-
- # Prepare data output.
- dict_tank_design['tmp_energies'] = {}
- dict_tank_design['tmp_energies']['wing_tank_without_center_tank'] = float(energy_wing_tank_without_center_tank)
- dict_tank_design['tmp_energies']['wing_tank_with_center_tank'] = float(energy_wing_tank_with_center_tank)
-
- return dict_tank_design
-
-
-def calculate_additional_center_tank(dict_ac_data, dict_tank_design, runtime_output):
- """Calculate energy contained in additional center tank.
-
- This code enables the installation of an additional center tank as LD3-45 container. Therefore, it is checked
- initially whether the existing cargo compartment provides sufficient height. If this is not the case, all export
- values are set to zero. Otherwise, the LD3-45 container is installed 10 cm behind the end of the landing gear bay.
- It is assumed that this is approximately in line with the trailing edge of the wing. The volume and dimensions of
- the container are taken from [1].
-
- Attention: Please note that it is not possible to calculate more than one additional center tank at the moment!
-
- [1] https://www.lufthansa-cargo.com/de/fleet-ulds/ulds/containers
-
- :param dict dict_design: Dictionary containing data from aircraft exchange and module configuration file
- :param dict dict_tank_design: Dictionary containing tank design parameter
- :param logging.Logger runtime_output: Logging object used for capturing log messages in the module
- :return dict dict_tank_design: Dictionary containing tank design parameter
- """
- # Extract necessary data from 'dict_ac_data'.
- factor_volume_usable = dict_ac_data['factor_volume_usable']
- temperature_expansion_allowance = dict_ac_data['temperature_expansion_allowance']
-
- # Get all tank entities that are located at the fuselage (additional center tanks).
- additional_center_tank_entity_list = [k for k, v in dict_tank_design.items() if k.startswith('tank_')
- and k[5:].isdigit() and v['tank_location'] == 'fuselage']
- number_of_additional_center_tanks = len(additional_center_tank_entity_list)
- if number_of_additional_center_tanks > 1:
- runtime_output.critical('Error: Tank design not possible for more than one additional center tank! '
- + 'Program aborted.')
- sys.exit('Exit information: Tank design not possible for more than one additional center tank!')
- # Extract identifier of center tank.
- center_tank_entity = additional_center_tank_entity_list[0]
-
- """Prepare data of LD3-45 container."""
- # Assumption: Angle at base equals 45 degree and usable volume of container taken from [1] (not calculated).
- height_container = 1.15
- width_base_container = 1.53
- width_top_container = 2.44
- length_container = 1.56
- height_base_part_container = (width_top_container - width_base_container)*0.5
- height_top_part_container = height_container - height_base_part_container
- volume_container = 3.4
- # Calculate areas and volumes for later use.
- area_base_part = width_base_container*length_container
- area_top_part = width_top_container*length_container
- volume_base_part = (
- (height_base_part_container*width_top_container*length_container)
- - height_base_part_container*height_base_part_container*length_container)
- volume_top_part = width_top_container*length_container*height_top_part_container
-
- # Check, if cargo compartment height sufficient to store LD3-45 container.
- if dict_tank_design['geometry']['fuselage']['cargo_compartment_height'] < height_container:
- additional_center_tank_design_possible = False
- runtime_output.warning('Warning: Cargo compartment height too small. Storage of LD3-45 container not '
- + 'possible. All values are set to 0.')
- else:
- additional_center_tank_design_possible = True
-
- """Calculate additional center tank."""
- # Calculate usable volume and convert to energy.
- center_tank_volume = volume_container*factor_volume_usable*temperature_expansion_allowance
- energy_kerosene_available = center_tank_volume*dict_ac_data['kerosene_volumetric_energy_density']
-
- # Calculate ACT and necessary values if possible.
- if additional_center_tank_design_possible:
- # Write data to 'dict_tank_design'.
- dict_tank_design[center_tank_entity]['volume_available'] = center_tank_volume
- dict_tank_design[center_tank_entity]['energy_available'] = energy_kerosene_available
-
- # Prepare geometrical data for additional center tank.
- # Assumption: Landing gear bay ends at wing trailing edge position.
- # x_coordinate_wing_leading_edge = dict_ac_data['wing_position_x']
- chord_length_at_fuselage_center_line = (
- dict_tank_design['geometry']['wing']['sections']['fuselage_center_line']['chord_length'])
- # x_coordinate_wing_trailing_edge = x_coordinate_wing_leading_edge + chord_length_at_fuselage_center_line
- buffer = 0.1
- x_coordinate = chord_length_at_fuselage_center_line + buffer
- y_coordinate = [width_top_container*0.5, width_base_container*0.5, 0.0,
- -width_base_container*0.5, -width_top_container*0.5]
- cargo_floor_below_wing = (dict_tank_design['geometry']['fuselage']['z_coordinate_cargo_floor']
- < dict_tank_design['geometry']['wing']['position']['z'])
- z_offset_wing_to_cargo_floor = abs(dict_tank_design['geometry']['wing']['position']['z']
- - dict_tank_design['geometry']['fuselage']['z_coordinate_cargo_floor'])
- if cargo_floor_below_wing:
- relative_z_position_cargo_floor_to_wing = -z_offset_wing_to_cargo_floor
- else:
- relative_z_position_cargo_floor_to_wing = z_offset_wing_to_cargo_floor
- z_coordinate = relative_z_position_cargo_floor_to_wing + np.array([
- # plane_0
- height_base_part_container + height_top_part_container*0.5,
- # plane_1, plane_2, plane_3
- height_container*0.5, height_container*0.5, height_container*0.5,
- # plane_4
- height_base_part_container + height_top_part_container*0.5])
- heights = [height_top_part_container, height_container, height_container,
- height_container, height_top_part_container]
- plane_names = ['cross_section_0', 'cross_section_1', 'cross_section_2', 'cross_section_3', 'cross_section_4']
-
- # Create the dictionary for center tank geometry.
- dict_tank_design[center_tank_entity]['geometry'] = {
- plane: {
- 'section_name': plane,
- 'position': {
- 'x': x_coordinate,
- 'y': y_coordinate[i],
- 'z': z_coordinate[i]
- },
- 'shape': 'rectangular',
- 'height': heights[i],
- 'width': length_container,
- 'length': 0.0
- }
- for i, plane in enumerate(plane_names)
- }
-
- # Define total tank geometry values.
- # Calculate tank mass (equals zero due to integral tank).
- dict_tank_design[center_tank_entity]['geometry']['total'] = {}
- dict_tank_design[center_tank_entity]['geometry']['total']['mass'] = 300
- # Set inertia to zero.
- inertia_list = ['j_xx', 'j_yy', 'j_zz', 'j_xy', 'j_xz', 'j_yx', 'j_yz', 'j_zx', 'j_zy']
- dict_tank_design[center_tank_entity]['geometry']['total']['inertia'] = {}
- for inertia in inertia_list:
- dict_tank_design[center_tank_entity]['geometry']['total']['inertia'][inertia] = 0.0
- # Center of gravity.
- # Prepare data for z coordinate calculation.
- h = height_base_part_container
- a_1 = area_top_part
- a_2 = area_base_part
- y_0 = ((h*(a_1 + 2*math.sqrt(a_1*a_2) + 3*a_2))
- /(4*(a_1 + math.sqrt(a_1*a_2)) + a_2))
- z_coordinate_cog_base_part = (dict_tank_design['geometry']['fuselage']['z_coordinate_cargo_floor']
- + (h - y_0))
- z_coordinate_cog_top_part = (dict_tank_design['geometry']['fuselage']['z_coordinate_cargo_floor']
- + height_base_part_container + height_top_part_container*0.5)
- z_cog = ((z_coordinate_cog_base_part*volume_base_part + z_coordinate_cog_top_part*volume_top_part)
- /(volume_base_part + volume_top_part))
-
- dict_tank_design[center_tank_entity]['geometry']['total']['center_of_gravity'] = {}
- dict_tank_design[center_tank_entity]['geometry']['total']['center_of_gravity']['x'] = (
- x_coordinate + length_container*0.5)
- dict_tank_design[center_tank_entity]['geometry']['total']['center_of_gravity']['y'] = 0.0
- dict_tank_design[center_tank_entity]['geometry']['total']['center_of_gravity']['z'] = z_cog
-
- # Calculate position of tank entity (foremost point of tank).
- dict_tank_design[center_tank_entity]['geometry']['total']['position'] = {}
- dict_tank_design[center_tank_entity]['geometry']['total']['position']['x'] = x_coordinate
- dict_tank_design[center_tank_entity]['geometry']['total']['position']['y'] = 0.0
- dict_tank_design[center_tank_entity]['geometry']['total']['position']['z'] = z_coordinate[2]
- # Direction.
- dict_tank_design[center_tank_entity]['geometry']['total']['direction'] = {}
- dict_tank_design[center_tank_entity]['geometry']['total']['direction']['x'] = 0
- dict_tank_design[center_tank_entity]['geometry']['total']['direction']['y'] = 1
- dict_tank_design[center_tank_entity]['geometry']['total']['direction']['z'] = 0
-
- else:
- # Set all export values to 0 if tank design not possible.
- dict_tank_design[center_tank_entity]['geometry'] = {
- 'cross_section_0': {
- 'section_name': 'cross_section_0',
- 'position': {
- 'x': 0.0,
- 'y': 0.0,
- 'z': 0.0
- },
- 'shape': None,
- 'height': 0.0,
- 'width': 0.0,
- 'length': 0.0
- }
- }
- # Tank mass.
- dict_tank_design[center_tank_entity]['geometry']['total'] = {}
- dict_tank_design[center_tank_entity]['geometry']['total']['mass'] = 0.0
- # Inertia.
- inertia_list = ['j_xx', 'j_yy', 'j_zz', 'j_xy', 'j_xz', 'j_yx', 'j_yz', 'j_zx', 'j_zy']
- dict_tank_design[center_tank_entity]['geometry']['total']['inertia'] = {}
- for inertia in inertia_list:
- dict_tank_design[center_tank_entity]['geometry']['total']['inertia'][inertia] = 0.0
- # Center of gravity.
- dict_tank_design[center_tank_entity]['geometry']['total']['center_of_gravity'] = {}
- dict_tank_design[center_tank_entity]['geometry']['total']['center_of_gravity']['x'] = 0.0
- dict_tank_design[center_tank_entity]['geometry']['total']['center_of_gravity']['y'] = 0.0
- dict_tank_design[center_tank_entity]['geometry']['total']['center_of_gravity']['z'] = 0.0
- # Position of tank entity (foremost point of tank).
- dict_tank_design[center_tank_entity]['geometry']['total']['position'] = {}
- dict_tank_design[center_tank_entity]['geometry']['total']['position']['x'] = 0.0
- dict_tank_design[center_tank_entity]['geometry']['total']['position']['y'] = 0.0
- dict_tank_design[center_tank_entity]['geometry']['total']['position']['z'] = 0.0
- # Direction.
- dict_tank_design[center_tank_entity]['geometry']['total']['direction'] = {}
- dict_tank_design[center_tank_entity]['geometry']['total']['direction']['x'] = 0
- dict_tank_design[center_tank_entity]['geometry']['total']['direction']['y'] = 1
- dict_tank_design[center_tank_entity]['geometry']['total']['direction']['z'] = 0
-
- # Debug print.
- runtime_output.debug('Debug: The "calculate_additional_center_tank" function was successfully executed.')
-
- # Prepare data output.
- dict_tank_design['tmp_energies'] = {}
- dict_tank_design['tmp_energies']['additional_center_tank'] = float(energy_kerosene_available)
-
- return dict_tank_design
-
-
-def calculate_trim_tank(dict_ac_data, dict_tank_design, runtime_output):
- """Calculate energy contained in trim tank.
-
- [Add some more information here...]
-
- :param dict dict_design: Dictionary containing data from aircraft exchange and module configuration file
- :param dict dict_tank_design: Dictionary containing tank design parameter
- :param logging.Logger runtime_output: Logging object used for capturing log messages in the module
- :return dict dict_tank_design: Dictionary containing tank design parameter
- """
- # Extract values from 'dict_ac_data'.
- factor_volume_usable = dict_ac_data['factor_volume_usable']
- temperature_expansion_allowance = dict_ac_data['temperature_expansion_allowance']
-
- geometry_dict = dict_tank_design['geometry']['horizontal_stabilizer']
- section_dict = dict_tank_design['geometry']['horizontal_stabilizer']['sections']
- symmetry = dict_tank_design['geometry']['horizontal_stabilizer']['information']['symmetry']
-
- # Get all tank entities that are located at the horizontal stabilizer (trim tank).
- tank_entity = [k for k, v in dict_tank_design.items() if k.startswith('tank_') and k[5:].isdigit()
- and v['tank_location'] == 'horizontal_stabilizer'][0]
-
- # Calculate distance from wing root to wing tip.
- span = section_dict['tip']['position']['y'] - section_dict['fuselage_center_line']['position']['y']
- # Calculate span offset for tank.
- outer_tank_span_offset = -(span*dict_ac_data['buffer_outer_tank_segment'])
-
- # Set tank sections according to number of wing sections.
- number_of_sections = len(section_dict)
- if number_of_sections < 2:
- runtime_output.critical('Error: Not enough horizontal stabilizer sections given. Program aborted.')
- sys.exit(1)
- elif number_of_sections ==2:
- sections = {'section_0': 'fuselage_center_line',
- 'section_1': 'tip'}
- # Span offsets for 'section_0' and 'section_1'.
- span_offset_list = [0.0, outer_tank_span_offset]
- elif number_of_sections == 3:
- sections = {'section_0': 'fuselage_center_line',
- 'section_1': 'tip'}
- # Span offsets for 'section_0' and 'section_1'.
- span_offset_list = [0.0, outer_tank_span_offset]
- else:
- runtime_output.critical('Error: Too many horizontal stabilizer sections given. '
- + 'Program aborted.')
- sys.exit(1)
-
- # Prepare tank sections.
- i = 0
- for sec, template in sections.items():
- section_dict[sec] = {}
- section_dict[sec]['position'] = {}
- section_dict[sec]['position']['y'] = section_dict[template]['position']['y'] + span_offset_list[i]
- section_dict[sec]['span_index'] = int(round(section_dict[sec]['position']['y']*100, 0))
- section_dict[sec]['position']['x'] = (
- geometry_dict['interpolated_values']['x_coordinate_leading_edge'][section_dict[sec]['span_index']])
- section_dict[sec]['position']['z'] = (
- geometry_dict['interpolated_values']['z_coordinate_leading_edge'][section_dict[sec]['span_index']])
- i += 1
-
- """Calculate tank volumes (geometry does not change from here)."""
- # Initialize empty dictionary and lists.
- dict_tank_design[tank_entity]['geometry'] = {}
- dict_tank_design[tank_entity]['geometry']['inner_surface'] = {}
- dict_tank_design[tank_entity]['geometry']['outer_surface'] = {}
- inner_surface_str = str()
- outer_surface_str = str()
-
- if symmetry:
- if number_of_sections == 2:
- inner_surface_str = 'section_0'
- outer_surface_str = 'section_1'
- elif number_of_sections == 3:
- inner_surface_str = 'section_0'
- outer_surface_str = 'section_1'
- else:
- runtime_output.critical('Error: Horizontal stabilizer not symmetric! Program aborted.')
- sys.exit(1)
-
- # Calculate obelisk volume.
- obelisk_volume = calculate_obelisk_volume(dict_ac_data['obelisk_volume_calculation_method'],
- geometry_dict, inner_surface_str, outer_surface_str)
- obelisk_volume *= 2
-
- # Calculate actual tank volume (considering volume loss due to internal structure of integral tanks and buffer for
- # temperature-dependent expansion of fuel).
- volume_trim_tank = factor_volume_usable*temperature_expansion_allowance*obelisk_volume
-
- # Calculate energy and write data to 'dict_tank_design'.
- dict_tank_design[tank_entity]['volume_available'] = volume_trim_tank
- dict_tank_design[tank_entity]['energy_available'] = (
- volume_trim_tank*dict_ac_data['kerosene_volumetric_energy_density'])
-
- # Add required output data: x, y, and z position, shape, height, width, and length.
- for surface_str, surface_name in zip([inner_surface_str, outer_surface_str], ['inner_surface', 'outer_surface']):
- surface_data = section_dict[surface_str]
- span_idx = surface_data['span_index']
-
- # Extract x and z coordinates.
- x_coordinate = geometry_dict['interpolated_values']['x_coordinate_front_spar'][span_idx]
- y_coordinate = surface_data['position']['y']
- z_coordinate = surface_data['position']['z']
-
- dict_tank_design[tank_entity]['geometry'][surface_name] = {
- 'section_name': surface_str,
- 'position': {
- 'x': x_coordinate,
- 'y': y_coordinate,
- 'z': z_coordinate,
- },
- 'shape': 'rectangular',
- 'height': geometry_dict['interpolated_values']['tank_heights'][span_idx],
- 'width': geometry_dict['interpolated_values']['tank_lengths'][span_idx],
- 'length': 0.0
- }
- # Rename and restructure dict.
- dict_tank_design[tank_entity]['geometry']['cross_section_1'] = dict_tank_design[tank_entity]['geometry'].pop(
- 'inner_surface')
- dict_tank_design[tank_entity]['geometry']['cross_section_2'] = dict_tank_design[tank_entity]['geometry'].pop(
- 'outer_surface')
-
- def deep_copy_dict(d):
- if isinstance(d, dict):
- return {key: deep_copy_dict(value) for key, value in d.items()}
- elif isinstance(d, list):
- return [deep_copy_dict(item) for item in d]
- else:
- return d
-
- independent_copy = deep_copy_dict(dict_tank_design[tank_entity]['geometry']['cross_section_2'])
- independent_copy['position']['y'] *= -1
- dict_tank_design[tank_entity]['geometry']['cross_section_0'] = independent_copy
-
- """Set or calculate total tank parameters."""
- # Set tank mass to zero (integral tank).
- dict_tank_design[tank_entity]['geometry']['total'] = {}
- dict_tank_design[tank_entity]['geometry']['total']['mass'] = 0.0
- # Set inertia to zero.
- inertia_list = ['j_xx', 'j_yy', 'j_zz', 'j_xy', 'j_xz', 'j_yx', 'j_yz', 'j_zx', 'j_zy']
- dict_tank_design[tank_entity]['geometry']['total']['inertia'] = {}
- for inertia in inertia_list:
- dict_tank_design[tank_entity]['geometry']['total']['inertia'][inertia] = 0.0
- # Center of gravity equals zero since integral tank has no mass.
- dict_tank_design[tank_entity]['geometry']['total']['center_of_gravity'] = {}
- dict_tank_design[tank_entity]['geometry']['total']['center_of_gravity']['x'] = 0.0
- dict_tank_design[tank_entity]['geometry']['total']['center_of_gravity']['y'] = 0.0
- dict_tank_design[tank_entity]['geometry']['total']['center_of_gravity']['z'] = 0.0
- # Calculate position of tank entity (foremost point of tank).
- distance_wing_to_horizontal_stabilizer = (dict_tank_design['geometry']['horizontal_stabilizer']['position']['x']
- - dict_tank_design['geometry']['wing']['position']['x'])
- wing_lower_than_horizontal_stabilizer = (dict_tank_design['geometry']['wing']['position']['z']
- < dict_tank_design['geometry']['horizontal_stabilizer']['position']['z'])
- z_offset_wing_to_horizontal_stabilizer = abs(dict_tank_design['geometry']['horizontal_stabilizer']['position']['z']
- - dict_tank_design['geometry']['wing']['position']['z'])
- if wing_lower_than_horizontal_stabilizer:
- relative_z_position_horizontal_stabilizer_to_wing = z_offset_wing_to_horizontal_stabilizer
- else:
- relative_z_position_horizontal_stabilizer_to_wing = -z_offset_wing_to_horizontal_stabilizer
- dict_tank_design[tank_entity]['geometry']['total']['position'] = {}
- dict_tank_design[tank_entity]['geometry']['total']['position']['x'] = (
- distance_wing_to_horizontal_stabilizer
- + geometry_dict['interpolated_values']['x_coordinate_front_spar'][section_dict[inner_surface_str]
- ['span_index']])
- dict_tank_design[tank_entity]['geometry']['total']['position']['y'] = (
- section_dict[inner_surface_str]['position']['y'])
- dict_tank_design[tank_entity]['geometry']['total']['position']['z'] = (
- relative_z_position_horizontal_stabilizer_to_wing)
- # Direction.
- dict_tank_design[tank_entity]['geometry']['total']['direction'] = {}
- dict_tank_design[tank_entity]['geometry']['total']['direction']['x'] = 0
- dict_tank_design[tank_entity]['geometry']['total']['direction']['y'] = 1
- dict_tank_design[tank_entity]['geometry']['total']['direction']['z'] = 0
-
- # Debug print.
- runtime_output.debug('Debug: The "calculate_trim_tank" function was successfully executed.')
-
- # Prepare data output.
- dict_tank_design['tmp_energies'] = {}
- dict_tank_design['tmp_energies']['trim_tank'] = float(dict_tank_design[tank_entity]['energy_available'])
-
- return dict_tank_design
+""" Module containing functions for kerosene tank calculation. """
+# Import standard libraries.
+import sys
+import math
+import numpy as np
+
+# Import own libraries.
+from pyunitconversion import constants
+
+
+def calculate_tank_span(span_index_inner_surface, span_index_outer_surface):
+ """Tank span in m.
+
+ Span index equals position in mm.
+
+ :param int span_index_inner_surface: Index of span position of inner surface
+ :param int span_index_outer_surface: Index of span position of outer surface
+ :return float: Tank span in m
+ """
+ tank_span = (span_index_outer_surface - span_index_inner_surface)/100
+
+ return tank_span
+
+
+def calculate_obelisk_volume(method, dict_wing_geometry, inner_surface_str, outer_surface_str):
+ """Calculate geometrical volume of obelisk.
+
+ This function calculates the obelisk volume according to the selected method (Torenbeek [1] or Simpson).
+
+ [1] E. Torenbeek "Synthesis of Subsonic Airplane Design" (1982), Fig. B-4 [1]
+
+ :param str method: Calculation method name
+ :param dict dict_wing_geometry: Dictionary containing wing geometry parameters
+ :param str inner_surface_str: Name of inner obelisk surface
+ :param str outer_surface_str: Name of outer obelisk surface
+ :return float: Volume of obelisk in m^3
+ """
+ interpolated_values = dict_wing_geometry['interpolated_values']
+
+ inner_span_index = abs(dict_wing_geometry['sections'][inner_surface_str]['span_index'])
+ outer_span_index = abs(dict_wing_geometry['sections'][outer_surface_str]['span_index'])
+ tank_span = (outer_span_index - inner_span_index)/100
+ maximum_tank_height_inner = interpolated_values['tank_heights'][inner_span_index]
+ maximum_tank_height_outer = interpolated_values['tank_heights'][outer_span_index]
+ maximum_tank_length_inner = interpolated_values['tank_lengths'][inner_span_index]
+ maximum_tank_length_outer = interpolated_values['tank_lengths'][outer_span_index]
+ area_inner = maximum_tank_height_inner*maximum_tank_length_inner
+ area_outer = maximum_tank_height_outer*maximum_tank_length_outer
+
+ match method:
+ case 'Torenbeek':
+ # Calculate volume of obelisk according to Torenbeek.
+ obelisk_volume = (tank_span/3*(area_inner + area_outer
+ + ((maximum_tank_height_inner*maximum_tank_length_outer)
+ + (maximum_tank_length_inner*maximum_tank_height_outer))/2))
+ case 'Simpson':
+ # Calculate volume of obelisk according to Simpson's rule.
+ middle_area = (area_inner + area_outer)/2
+ obelisk_volume = tank_span / 6.0 * (area_inner + 4.0 * middle_area + area_outer)
+
+ return obelisk_volume
+
+
+def calculate_kerosene_tanks(dict_ac_data, dict_tank_design, runtime_output):
+ """Calculate kerosene tanks of tube-and-wing aircraft.
+
+ This function adds the following sub dictionaries to the 'dict_tank_design' dictionary:
+ ...
+
+ :param dict dict_ac_data: Dictionary containing data from aircraft exchange and module configuration file
+ :param dict dict_tank_design: Dictionary containing tank design parameter
+ :param logging.Logger runtime_output: Logging object used for capturing log messages in the module
+ :return dict dict_tank_design: Dictionary containing tank design parameter
+ """
+ # Extract data and initialize variables.
+ total_tank_energy = 0
+ wing_tank_energy_without_wing_center_tank = 0
+ kerosene_volumetric_energy_density = constants.KEROSENE_VOLUMETRIC_ENERGY_DENSITY
+
+ """Check if initial sizing loop and estimate energy demand if necessary."""
+ initial_sizing_loop = all(value is None for value in dict_ac_data['mission_energy_amount'].values())
+ if initial_sizing_loop:
+ runtime_output.print('Initial sizing loop! Energy demand is estimated (3.35 liters per PAX per 100 km).')
+ energy_demand = 3.35 # in liter per passenger
+ mission_fuel_amount = dict_ac_data['number_of_passengers']*dict_ac_data['range']/1000*energy_demand/100
+ mission_energy_amount = (mission_fuel_amount/1000*kerosene_volumetric_energy_density)
+ else:
+ mission_energy_amount = dict_ac_data['mission_energy_amount']['mission_energy_amount_ID0']
+
+ """ Calculate wing tank volume. """
+ # Wing tank volume must be calculated for all possible tank configurations.
+ dict_tank_design = calculate_wing_tanks(dict_ac_data, dict_tank_design, runtime_output, mission_energy_amount)
+ total_tank_energy += dict_tank_design['tmp_energies']['wing_tank_with_center_tank']
+ wing_tank_energy_without_wing_center_tank += dict_tank_design['tmp_energies']['wing_tank_without_center_tank']
+ # Check if wing tanks can store mission energy amount.
+ if wing_tank_energy_without_wing_center_tank >= mission_energy_amount:
+ runtime_output.print('Energy check: Wing center tank created but unnecessary to store required energy '
+ + 'amount.')
+ runtime_output.print('Energy check: Energy demand covered.')
+ # Set 'energy_required' to 0.
+ wing_tank_entity_list = [k for k, v in dict_tank_design.items()
+ if k.startswith('tank_') and k[5:].isdigit() and v['tank_location'] == 'wing']
+ wing_center_tank_entity = [k for k in wing_tank_entity_list
+ if dict_tank_design[k]['tank_position'].endswith('center')][0]
+ dict_tank_design[wing_center_tank_entity]['energy_required_for_mission'] = False
+ # Set energy demand flag.
+ energy_demand_covered = True
+ elif total_tank_energy >= mission_energy_amount:
+ runtime_output.print('Energy check: Wing center tank necessary to store required energy amount.')
+ runtime_output.print('Energy check: Energy demand covered.')
+ energy_demand_covered = True
+ else:
+ energy_demand_covered = False
+
+ # TEST
+ # If energy amount not covered by wing tanks: Calculate other fuel tanks (depending on tank configuration).
+ # Calculate additional tank volumes according to defined tank configuration.
+ match dict_tank_design['tank_configuration']:
+ case 'wing_with_trim_tank':
+ if not energy_demand_covered:
+ runtime_output.print('Energy check: Demand not covered yet. Continue with design of trim tank.')
+ dict_tank_design = calculate_trim_tank(dict_ac_data, dict_tank_design, runtime_output,
+ energy_demand_covered)
+ total_tank_energy += dict_tank_design['tmp_energies']['trim_tank']
+ if energy_demand_covered:
+ runtime_output.print('Trim tank is generated but unnecessary to store required energy amount.')
+ else:
+ if total_tank_energy >= mission_energy_amount:
+ energy_demand_covered = True
+ runtime_output.print('Energy check: Energy demand covered.')
+ case 'wing_with_additional_center_tank':
+ if not energy_demand_covered:
+ runtime_output.print('Energy check: Demand not covered yet. Continue with design of additional '
+ + 'center tank.')
+ dict_tank_design = calculate_additional_center_tank(dict_ac_data, dict_tank_design, runtime_output,
+ energy_demand_covered)
+ total_tank_energy += (dict_tank_design['tmp_energies']['additional_center_tank'])
+ if energy_demand_covered:
+ runtime_output.print('Additional center tank is generated but unnecessary to store required energy '
+ + 'amount.')
+ else:
+ if total_tank_energy >= mission_energy_amount:
+ energy_demand_covered = True
+ runtime_output.print('Energy check: Energy demand covered.')
+
+ case 'wing_with_additional_center_and_trim_tank':
+ first_act_then_trim = (dict_tank_design['tank_5']['tank_location'] == 'fuselage')
+ first_trim_then_act = (dict_tank_design['tank_5']['tank_location'] == 'horizontal_stabilizer')
+ if first_act_then_trim and not first_trim_then_act:
+ if not energy_demand_covered:
+ runtime_output.print('Energy check: Demand not covered yet. Continue with design of additional '
+ + 'center tank.')
+ dict_tank_design = calculate_additional_center_tank(dict_ac_data, dict_tank_design, runtime_output,
+ energy_demand_covered)
+ total_tank_energy += dict_tank_design['tmp_energies']['additional_center_tank']
+ if energy_demand_covered:
+ runtime_output.print('Additional center tank is generated but unnecessary to store required energy'
+ + ' amount.')
+ else:
+ if total_tank_energy >= mission_energy_amount:
+ energy_demand_covered = True
+ runtime_output.print('Energy check: Energy demand covered.')
+ else:
+ runtime_output.print('Energy check: Demand not covered yet. Continue with design of trim '
+ + 'tank.')
+ dict_tank_design = calculate_trim_tank(dict_ac_data, dict_tank_design, runtime_output,
+ energy_demand_covered)
+ total_tank_energy += dict_tank_design['tmp_energies']['trim_tank']
+ if energy_demand_covered:
+ runtime_output.print('Trim tank is generated but unnecessary to store required energy '
+ + 'amount.')
+ else:
+ if total_tank_energy >= mission_energy_amount:
+ energy_demand_covered = True
+ runtime_output.print('Energy check: Energy demand covered.')
+ if first_trim_then_act and not first_act_then_trim:
+ if not energy_demand_covered:
+ runtime_output.print('Energy check: Demand not covered yet. Continue with design of trim tank.')
+ dict_tank_design = calculate_trim_tank(dict_ac_data, dict_tank_design, runtime_output,
+ energy_demand_covered)
+ total_tank_energy += dict_tank_design['tmp_energies']['trim_tank']
+ if energy_demand_covered:
+ runtime_output.print('Trim tank is generated but unnecessary to store required energy '
+ + 'amount.')
+ else:
+ if total_tank_energy >= mission_energy_amount:
+ energy_demand_covered = True
+ runtime_output.print('Energy check: Energy demand covered.')
+ else:
+ runtime_output.print('Energy check: Demand not covered yet. Continue with design of '
+ + 'additional center tank.')
+ dict_tank_design = calculate_additional_center_tank(dict_ac_data, dict_tank_design, runtime_output,
+ energy_demand_covered)
+ total_tank_energy += dict_tank_design['tmp_energies']['additional_center_tank']
+ if energy_demand_covered:
+ runtime_output.print('Additional center tank is generated but unnecessary to store required energy '
+ + 'amount.')
+ else:
+ if total_tank_energy >= mission_energy_amount:
+ energy_demand_covered = True
+ runtime_output.print('Energy check: Energy demand covered.')
+
+ # Final check if tanks can store mission energy amount.
+ if energy_demand_covered:
+ runtime_output.print('Tank design successful.')
+ else:
+ energy_missing = mission_energy_amount - total_tank_energy
+ volume_missing = energy_missing/kerosene_volumetric_energy_density
+ runtime_output.print('Attention: Necessary amount of fuel cannot be stored in selected tanks! '
+ + str(int(round(energy_missing,0))) + 'J (' + str(round(volume_missing,2)) +
+ 'L) missing.')
+
+ # TEST END
+
+ # """ Print information or calculate other fuel tanks. """
+ # if energy_demand_covered:
+ # # Energy amount that can be stored in wing tanks already covers mission energy amount. All other tanks are
+ # # generated but remain empty ('volume_available' and 'energy_available' are 0.0).
+ # match dict_tank_design['tank_configuration']:
+ # case 'wing_with_trim_tank':
+ # runtime_output.print('Trim tank is generated but unnecessary and remains empty.')
+ # case 'wing_with_additional_center_tank':
+ # runtime_output.print('Additional center tank is generated but unnecessary and remains empty.')
+ # case 'wing_with_additional_center_and_trim_tank':
+ # runtime_output.print('Trim and additional center tank are generated but unnecessary and '
+ # + 'remain empty.')
+ # else:
+ # # If energy amount not covered by wing tanks: Calculate other fuel tanks (depending on tank configuration).
+ # # Calculate additional tank volumes according to defined tank configuration.
+ # match dict_tank_design['tank_configuration']:
+ # case 'wing_with_trim_tank':
+ # dict_tank_design = calculate_trim_tank(dict_ac_data, dict_tank_design, runtime_output)
+ # total_tank_energy += dict_tank_design['tmp_energies']['trim_tank']
+ # if total_tank_energy >= mission_energy_amount:
+ # energy_demand_covered = True
+ # case 'wing_with_additional_center_tank':
+ # dict_tank_design = calculate_additional_center_tank(dict_ac_data, dict_tank_design, runtime_output)
+ # total_tank_energy += (
+ # dict_tank_design['tmp_energies']['additional_center_tank'])
+ # if total_tank_energy >= mission_energy_amount:
+ # energy_demand_covered = True
+ # case 'wing_with_additional_center_and_trim_tank':
+ # first_act_then_trim = (dict_tank_design['tank_5']['tank_location'] == 'fuselage')
+ # first_trim_then_act = (dict_tank_design['tank_5']['tank_location'] == 'horizontal_stabilizer')
+ # if first_act_then_trim and not first_trim_then_act:
+ # dict_tank_design = calculate_additional_center_tank(dict_ac_data, dict_tank_design, runtime_output)
+ # total_tank_energy += dict_tank_design['tmp_energies']['additional_center_tank']
+ # if total_tank_energy >= mission_energy_amount:
+ # energy_demand_covered = True
+ # runtime_output.print('Energy check: Energy demand covered.')
+ # runtime_output.print('Trim tank is generated but unnecessary and remains empty.')
+ # else:
+ # runtime_output.print('Energy check: Demand not covered yet. Continue with design of trim '
+ # + 'tank.')
+ # dict_tank_design = calculate_trim_tank(dict_ac_data, dict_tank_design, runtime_output)
+ # additional_tank_energy += dict_tank_design['tmp_energies']['trim_tank']
+ # total_tank_energy += additional_tank_energy
+ # if total_tank_energy >= mission_energy_amount:
+ # energy_demand_covered = True
+ # if first_trim_then_act and not first_act_then_trim:
+ # dict_tank_design = calculate_trim_tank(dict_ac_data, dict_tank_design, runtime_output)
+ # total_tank_energy += dict_tank_design['tmp_energies']['trim_tank']
+ # if total_tank_energy >= mission_energy_amount:
+ # energy_demand_covered = True
+ # runtime_output.print('Energy check: Energy demand covered.')
+ # runtime_output.print('Additional center tank is generated but unnecessary and remains empty.')
+ # else:
+ # runtime_output.print('Energy check: Demand not covered yet. Continue with design of '
+ # + 'additional center tank.')
+ # dict_tank_design = calculate_additional_center_tank(dict_ac_data, dict_tank_design,
+ # runtime_output)
+ # additional_tank_energy += dict_tank_design['tmp_energies']['additional_center_tank']
+ # total_tank_energy += additional_tank_energy
+ # if total_tank_energy >= mission_energy_amount:
+ # energy_demand_covered = True
+
+ # # Final check if tanks can store mission energy amount.
+ # if energy_demand_covered:
+ # runtime_output.print('Tank design successful.')
+ # else:
+ # energy_missing = mission_energy_amount - total_tank_energy
+ # volume_missing = energy_missing/kerosene_volumetric_energy_density
+ # runtime_output.print('Attention: Necessary amount of fuel cannot be stored in selected tanks! '
+ # + str(int(round(energy_missing,0))) + 'J (' + str(round(volume_missing,2)) +
+ # 'L) missing.')
+
+ """ Calculate total tank parameters. """
+ dict_tank_design['total_tank_parameters'] = {}
+ # Tank mass (integral tank -> equals zero).
+ dict_tank_design['total_tank_parameters']['mass'] = 0.0
+ # Tank position.
+ dict_tank_design['total_tank_parameters']['position'] = {}
+ dict_tank_design['total_tank_parameters']['position']['x'] = (
+ dict_tank_design['geometry']['wing']['position']['x'])
+ dict_tank_design['total_tank_parameters']['position']['y'] = (
+ dict_tank_design['geometry']['wing']['position']['y'])
+ dict_tank_design['total_tank_parameters']['position']['z'] = (
+ dict_tank_design['geometry']['wing']['position']['z'])
+ # Inertia (are set to zero).
+ inertia_list = ['j_xx', 'j_yy', 'j_zz', 'j_xy', 'j_xz', 'j_yx', 'j_yz', 'j_zx', 'j_zy']
+ dict_tank_design['total_tank_parameters']['inertia'] = {}
+ for inertia in inertia_list:
+ dict_tank_design['total_tank_parameters']['inertia'][inertia] = 0.0
+ # Center of gravity (equals zero since integral tank has no mass).
+ dict_tank_design['total_tank_parameters']['center_of_gravity'] = {}
+ dict_tank_design['total_tank_parameters']['center_of_gravity']['x'] = 0.0
+ dict_tank_design['total_tank_parameters']['center_of_gravity']['y'] = 0.0
+ dict_tank_design['total_tank_parameters']['center_of_gravity']['z'] = 0.0
+
+ # Additional fuselage length equals zero for kerosene driven aircraft.
+ dict_tank_design['total_tank_parameters']['additional_fuselage_length'] = 0.0
+
+ # Prints.
+ runtime_output.print('Debug: The "calculate_tanks" function was successfully executed.')
+
+ return dict_tank_design
+
+
+def calculate_wing_tanks(dict_ac_data, dict_tank_design, runtime_output, mission_energy_amount):
+ """Calculate energy contained in wing tanks.
+
+ In the first step, the volume of the obelisks (according to Torenbeek or Simpson) is calculated for every given
+ tank entity. Afterwards, the actual tank volume is calculated, considering volume loss due to internal structure
+ of integral tanks and buffer for temperature-dependent expansion of fuel. All the volumes are summed up
+ ('volume_obelisks_without_center_tank'), except for the center tank volume that is saved in a separate parameter
+ ('volume_obelisk_center_tank'). The energy contained in the tank can than be calculated by multiplying the actual
+ volume with the volumetric energy density of kerosene.
+ Finally it is checked if the wing center tank is necessary. If the left and right inner and outer wing tanks are
+ big enough to store the energy required, the wing center tank values are set to zero.
+
+ :param dict dict_design: Dictionary containing data from aircraft exchange and module configuration file
+ :param dict dict_tank_design: Dictionary containing tank design parameter
+ :param logging.Logger runtime_output: Logging object used for capturing log messages in the module
+ :param float mission_energy_amount: Mission energy amount in Joule
+ :return dict dict_tank_design: Dictionary containing tank design parameter
+ """
+ # Extract necessary data from 'dict_ac_data'.
+ factor_volume_usable = dict_ac_data['factor_volume_usable']
+ # Since a vent tank is considered, no temperature expansion allowance has to be considered for wing tanks.
+ temperature_expansion_allowance = 1.0
+ # Extract kerosene energy density from library.
+ kerosene_volumetric_energy_density = constants.KEROSENE_VOLUMETRIC_ENERGY_DENSITY
+
+ # Print.
+ runtime_output.print('Wing tank design started...')
+
+ wing_geometry_dict = dict_tank_design['geometry']['wing']
+ wing_section_dict = dict_tank_design['geometry']['wing']['sections']
+ wing_symmetry = dict_tank_design['geometry']['wing']['information']['wing_symmetry']
+
+ # Get all tank entities that are located at the wing.
+ wing_tank_entity_list = [k for k, v in dict_tank_design.items()
+ if k.startswith('tank_') and k[5:].isdigit() and v['tank_location'] == 'wing']
+ wing_center_tank_entity = [k for k in wing_tank_entity_list
+ if dict_tank_design[k]['tank_position'].endswith('center')][0]
+ # Calculate distance from wing root to wing tip.
+ distance_wing_root_to_tip = (wing_section_dict['wing_tip']['position']['y']
+ - wing_section_dict['wing_root']['position']['y'])
+ # Calculate span offset for tank sections.
+ center_tank_span_offset = -(wing_section_dict['wing_root']['position']['y']*
+ dict_ac_data['buffer_center_tank_segment'])
+ inner_wing_tank_span_offset = distance_wing_root_to_tip*dict_ac_data['buffer_inner_tank_segment']
+ kink_section_span_offset = 0.0
+ outer_vent_tank_span_offset = -(distance_wing_root_to_tip*dict_ac_data['buffer_outer_tank_segment'])
+
+ # Set tank sections according to number of wing sections.
+ number_of_wing_sections = len(wing_section_dict)
+ if number_of_wing_sections < 3:
+ runtime_output.critical('Error: Not enough wing sections given. '
+ + 'Program aborted.')
+ sys.exit(1)
+ elif number_of_wing_sections == 3:
+ sections = {'outer_center_tank_section': 'wing_root',
+ 'section_0': 'wing_root',
+ 'section_1': 'wing_tip',
+ 'outer_vent_tank_section': 'wing_tip'}
+ vent_tank_inner_surface = 'section_1'
+ # Span offsets for 'center_tank', 'section_0', 'section_1', and 'outer_vent_tank_section'.
+ span_offset_list = [center_tank_span_offset, inner_wing_tank_span_offset, kink_section_span_offset,
+ outer_vent_tank_span_offset]
+ elif number_of_wing_sections == 4:
+ sections = {'outer_center_tank_section': 'wing_root',
+ 'section_0': 'wing_root',
+ 'section_1': 'kink',
+ 'section_2': 'wing_tip',
+ 'outer_vent_tank_section': 'wing_tip'}
+ vent_tank_inner_surface = 'section_2'
+ # Span offsets for 'center_tank', 'section_0', 'section_1', 'section_2', and 'outer_vent_tank_section'.
+ span_offset_list = [center_tank_span_offset, inner_wing_tank_span_offset, kink_section_span_offset,
+ outer_vent_tank_span_offset, outer_vent_tank_span_offset]
+ else:
+ runtime_output.critical('Error: Too many wing sections given. '
+ + 'Program aborted.')
+ sys.exit(1)
+
+ # Prepare tank sections.
+ i = 0
+ for sec, template in sections.items():
+ wing_section_dict[sec] = {}
+ wing_section_dict[sec]['position'] = {}
+ wing_section_dict[sec]['position']['y'] = (
+ wing_section_dict[template]['position']['y'] + span_offset_list[i])
+ wing_section_dict[sec]['span_index'] = abs(int(round(
+ wing_section_dict[sec]['position']['y']*100, 0)))
+ wing_section_dict[sec]['position']['x'] = (
+ wing_geometry_dict['interpolated_values']['x_coordinate_leading_edge']
+ [wing_section_dict[sec]['span_index']])
+ wing_section_dict[sec]['position']['z'] = (
+ #wing_section_dict[template]['position']['z'])
+ wing_geometry_dict['interpolated_values']['z_coordinate_leading_edge']
+ [wing_section_dict[sec]['span_index']])
+ # span_index = wing_section_dict[sec]['span_index']
+ i += 1
+
+ # -------------------------- START OF NEW VENT TANK CALCULATION -------------------------
+ def calculate_wing_tanks_volume():
+ """Calculate tank volumes (wing geometry does not change from here)."""
+ # Initialize parameter.
+ actual_volume_center_tank = 0
+ actual_volume_without_center_tank = 0
+
+ # Iterate through tank entities.
+ wing_tank_entity_list = [key for key, value in dict_tank_design.items() if key.startswith('tank_')
+ and key[5:].isdigit() and value['tank_location'] == 'wing']
+ for wing_tank_entity in wing_tank_entity_list:
+ # Initialize empty dictionary and lists.
+ dict_tank_design[wing_tank_entity]['geometry'] = {}
+ dict_tank_design[wing_tank_entity]['geometry']['inner_surface'] = {}
+ dict_tank_design[wing_tank_entity]['geometry']['outer_surface'] = {}
+ inner_surface_str = str()
+ outer_surface_str = str()
+
+ if wing_symmetry:
+ if number_of_wing_sections == 4:
+ # Set sections depending on tank position.
+ match dict_tank_design[wing_tank_entity]['tank_position']:
+ case 'inner_left' | 'inner_right':
+ inner_surface_str = 'section_0'
+ outer_surface_str = 'section_1'
+ case 'outer_left' | 'outer_right':
+ inner_surface_str = 'section_1'
+ outer_surface_str = 'section_2'
+ case 'center':
+ inner_surface_str = 'fuselage_center_line'
+ outer_surface_str = 'outer_center_tank_section'
+ else:
+ runtime_output.critical('Error: Wing without kink not implemented yet! Program aborted.')
+ sys.exit(1)
+ else:
+ runtime_output.critical('Error: Wing not symmetric! '
+ + 'Program aborted.')
+ sys.exit(1)
+
+ # Calculate obelisk volume.
+ obelisk_volume = calculate_obelisk_volume(dict_ac_data['obelisk_volume_calculation_method'],
+ wing_geometry_dict, inner_surface_str, outer_surface_str)
+ # Calculate actual tank volume (considering volume loss due to internal structure of integral tanks and buffer
+ # for temperature-dependent expansion of fuel).
+ if dict_tank_design[wing_tank_entity]['tank_position'] == 'center':
+ obelisk_volume *= 2
+ actual_volume = factor_volume_usable*temperature_expansion_allowance*obelisk_volume
+ # Sum up volume of all tanks except wing center tank.
+ if dict_tank_design[wing_tank_entity]['tank_position'] != 'center':
+ actual_volume_without_center_tank += actual_volume
+ # Set volume of wing center tank.
+ else:
+ actual_volume_center_tank = actual_volume
+
+ # Write data to 'dict_tank_design'.
+ dict_tank_design[wing_tank_entity]['volume_available'] = actual_volume
+ dict_tank_design[wing_tank_entity]['energy_available'] = (
+ actual_volume*kerosene_volumetric_energy_density)
+ # Print.
+ # inner left wing tank (ID="0") calculated. Volume (energy) available: 3.51 l ().
+ # f'{a*1000:,.2f}'
+ # Transform volume to liter for print.
+ actual_volume_l = actual_volume*1e3
+ if dict_tank_design[wing_tank_entity]['tank_position'] == 'center' and print_outputs:
+ runtime_output.print('Wing center tank (' + wing_tank_entity + ') calculated. '
+ + 'Volume (energy) available: ' + f"{actual_volume_l:,.2f}" + ' L ('
+ + f"{dict_tank_design[wing_tank_entity]['energy_available']/1e6:,.2f}" + ' MJ)')
+ else:
+ if print_outputs:
+ print_position = (dict_tank_design[wing_tank_entity]['tank_position'].split('_')[0].capitalize()
+ + ' ' + dict_tank_design[wing_tank_entity]['tank_position'].split('_')[1] + ' ')
+ runtime_output.print(print_position + 'wing tank (' + wing_tank_entity + ') calculated. '
+ + 'Volume (energy) available: ' + f"{actual_volume_l:,.2f}" + ' L ('
+ + f"{dict_tank_design[wing_tank_entity]['energy_available']/1e6:,.2f}"
+ + ' MJ)')
+
+ # Calculate tank mass (equals zero due to integral tank).
+ dict_tank_design[wing_tank_entity]['geometry']['total'] = {}
+ dict_tank_design[wing_tank_entity]['geometry']['total']['mass'] = 0.0
+ # Set inertia to zero.
+ inertia_list = ['j_xx', 'j_yy', 'j_zz', 'j_xy', 'j_xz', 'j_yx', 'j_yz', 'j_zx', 'j_zy']
+ dict_tank_design[wing_tank_entity]['geometry']['total']['inertia'] = {}
+ for inertia in inertia_list:
+ dict_tank_design[wing_tank_entity]['geometry']['total']['inertia'][inertia] = 0.0
+ # Center of gravity equals zero since integral tank has no mass.
+ dict_tank_design[wing_tank_entity]['geometry']['total']['center_of_gravity'] = {}
+ dict_tank_design[wing_tank_entity]['geometry']['total']['center_of_gravity']['x'] = 0.0
+ dict_tank_design[wing_tank_entity]['geometry']['total']['center_of_gravity']['y'] = 0.0
+ dict_tank_design[wing_tank_entity]['geometry']['total']['center_of_gravity']['z'] = 0.0
+
+ # Calculate position of tank entity (foremost point of tank).
+ dict_tank_design[wing_tank_entity]['geometry']['total']['position'] = {}
+ dict_tank_design[wing_tank_entity]['geometry']['total']['position']['x'] = (
+ wing_geometry_dict['interpolated_values']['x_coordinate_front_spar'][
+ wing_section_dict[inner_surface_str]['span_index']
+ ])
+ if (dict_tank_design[wing_tank_entity]['tank_position'] == 'inner_left') or (
+ dict_tank_design[wing_tank_entity]['tank_position'] == 'outer_left'):
+ dict_tank_design[wing_tank_entity]['geometry']['total']['position']['y'] = -abs(
+ wing_section_dict[inner_surface_str]['position']['y'])
+ else:
+ dict_tank_design[wing_tank_entity]['geometry']['total']['position']['y'] = abs(
+ wing_section_dict[inner_surface_str]['position']['y'])
+ dict_tank_design[wing_tank_entity]['geometry']['total']['position']['z'] = (
+ wing_section_dict[inner_surface_str]['position']['z'])
+ # Direction.
+ dict_tank_design[wing_tank_entity]['geometry']['total']['direction'] = {}
+ dict_tank_design[wing_tank_entity]['geometry']['total']['direction']['x'] = 0
+ dict_tank_design[wing_tank_entity]['geometry']['total']['direction']['y'] = 1
+ dict_tank_design[wing_tank_entity]['geometry']['total']['direction']['z'] = 0
+ # Set required energy.
+ dict_tank_design[wing_tank_entity]['energy_required_for_mission'] = True
+
+ # Add required output data: x, y, and z position, shape, height, width, and length.
+ for surface_str, surface_name in zip([inner_surface_str, outer_surface_str],
+ ['inner_surface', 'outer_surface']):
+ surface_data = wing_section_dict[surface_str]
+ span_idx = surface_data['span_index']
+ # Inner surface equals tank entity position.
+ if surface_name == 'inner_surface':
+ x_coordinate = 0.0
+ y_coordinate = 0.0
+ z_coordinate = 0.0
+ else:
+ # Adjust y coordinate for left hand tanks.
+ y_coordinate_entity = dict_tank_design[wing_tank_entity]['geometry']['total']['position']['y']
+ if 'left' in dict_tank_design[wing_tank_entity]['tank_position']:
+ y_coordinate_section = -surface_data['position']['y']
+ y_coordinate = -(abs(y_coordinate_section) - abs(y_coordinate_entity))
+ else:
+ y_coordinate_section = surface_data['position']['y']
+ y_coordinate = (abs(y_coordinate_section) - abs(y_coordinate_entity))
+ # old
+ # y_coordinate = y_coordinate_section - y_coordinate_entity
+ # NEW:
+ # y_coordinate = -(abs(y_coordinate_section) - abs(y_coordinate_entity))
+ # if 'left' in dict_tank_design[wing_tank_entity]['tank_position']:
+ # y_coordinate = y_coordinate*(-1)
+ # x coordinate.
+ x_coordinate_entity = dict_tank_design[wing_tank_entity]['geometry']['total']['position']['x']
+ x_coordinate_section = wing_geometry_dict['interpolated_values']['x_coordinate_front_spar'][span_idx]
+ if x_coordinate_entity < 0 and x_coordinate_section > 0 and x_coordinate_section > x_coordinate_entity:
+ delta_x = x_coordinate_entity - x_coordinate_section
+ else:
+ delta_x = x_coordinate_section - x_coordinate_entity
+ x_coordinate = delta_x
+ # z coordinate.
+ z_coordinate_entity = dict_tank_design[wing_tank_entity]['geometry']['total']['position']['z']
+ z_coordinate_section = surface_data['position']['z']
+ z_coordinate = z_coordinate_section - z_coordinate_entity
+
+ dict_tank_design[wing_tank_entity]['geometry'][surface_name] = {
+ 'section_name': surface_str,
+ 'position': {
+ 'x': x_coordinate,
+ 'y': y_coordinate,
+ 'z': z_coordinate,
+ },
+ 'shape': 'rectangular',
+ 'height': wing_geometry_dict['interpolated_values']['tank_heights'][span_idx],
+ 'width': wing_geometry_dict['interpolated_values']['tank_lengths'][span_idx],
+ 'length': 0.0
+ }
+
+ # Correct wing center tank information.
+ if 'center' in dict_tank_design[wing_tank_entity]['tank_position']:
+ dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['position']['y'] = (
+ dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['position']['y']/2
+ )
+ dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['position']['y'] = -(
+ dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['position']['y']
+ )
+
+ # Centroid.
+ # Assumption: inner surface area always greater than outer surface area.
+ inner_surface_area = (dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['height']
+ *dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['width'])
+ outer_surface_area = (dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['height']
+ *dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['width'])
+ y_position_outer_surface = dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['position']['y']
+ y_position_inner_surface = dict_tank_design[wing_tank_entity]['geometry']['total']['position']['y']
+ tank_span = y_position_outer_surface - y_position_inner_surface
+ y_position_center_of_mass = y_position_inner_surface + (tank_span/4*((inner_surface_area
+ + 2*math.sqrt(inner_surface_area*outer_surface_area)
+ + outer_surface_area)/(inner_surface_area + outer_surface_area)))
+ centroid_y = y_position_inner_surface + ((tank_span
+ *((dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['height']
+ *dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['width'])
+ +(dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['height']
+ *dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['width'])
+ +(dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['height']
+ *dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['width'])
+ +(3*dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['height']
+ *dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['width'])))
+ /(2
+ *(2*dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['height']
+ *dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['width'])
+ + (dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['height']
+ *dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['width'])
+ + (dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['height']
+ *dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['width'])
+ + (2*dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['height']
+ *dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['width'])))
+ x_position_cog_inner_surface = dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['width']/2
+ x_position_cog_outer_surface = dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['width']/2
+ z_position_cog_inner_surface = dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['height']/2
+ z_position_cog_outer_surface = dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['height']/2
+ x_position_center_of_mass = ((inner_surface_area*x_position_cog_inner_surface
+ + outer_surface_area*x_position_cog_outer_surface)
+ /(inner_surface_area + outer_surface_area))
+ z_position_center_of_mass = ((inner_surface_area*z_position_cog_inner_surface
+ + outer_surface_area*z_position_cog_outer_surface)
+ /(inner_surface_area + outer_surface_area))
+
+ dict_tank_design[wing_tank_entity]['geometry']['total']['centroid'] = {}
+ if wing_tank_entity == wing_center_tank_entity:
+ dict_tank_design[wing_tank_entity]['geometry']['total']['centroid']['x'] = x_position_center_of_mass
+ # dict_tank_design[wing_tank_entity]['geometry']['total']['centroid']['x'] = (
+ # dict_tank_design['tank_4']['geometry']['inner_surface']['position']['x']
+ # + dict_tank_design['tank_4']['geometry']['inner_surface']['width']/2
+ # )
+ dict_tank_design[wing_tank_entity]['geometry']['total']['centroid']['y'] = 0
+ dict_tank_design[wing_tank_entity]['geometry']['total']['centroid']['z'] = 0
+ else:
+ dict_tank_design[wing_tank_entity]['geometry']['total']['centroid']['x'] = x_position_center_of_mass
+ dict_tank_design[wing_tank_entity]['geometry']['total']['centroid']['y'] = y_position_center_of_mass
+ dict_tank_design[wing_tank_entity]['geometry']['total']['centroid']['z'] = z_position_center_of_mass
+
+ # Sum up.
+ volume_wing_tank_without_center_tank = actual_volume_without_center_tank
+ volume_wing_tank_with_center_tank = actual_volume_without_center_tank + actual_volume_center_tank
+
+ """Calculate fuel mass and energy."""
+ # Convert wing fuel volume to energy.
+ energy_wing_tank_without_center_tank = (volume_wing_tank_without_center_tank
+ *kerosene_volumetric_energy_density)
+ energy_wing_tank_with_center_tank = (volume_wing_tank_with_center_tank
+ *kerosene_volumetric_energy_density)
+
+ return energy_wing_tank_without_center_tank, energy_wing_tank_with_center_tank
+
+
+ def calculate_vent_tank_volume(wing_tank_energy_amount):
+ """Calculate vent tank."""
+ # § 25.969 Fuel tank expansion space. Each fuel tank must have an expansion space of not less than 2 percent
+ # of the tank capacity. It must be impossible to fill the expansion space inadvertently with the airplane in the
+ # normal ground attitude. For pressure fueling systems, compliance with this section may be shown with the means
+ # provided to comply with §25.979(b).
+ # Add vent tank to tank design dict.
+ dict_tank_design['vent_tank'] = {}
+ dict_tank_design['vent_tank']['tank_location'] = 'wing'
+ dict_tank_design['vent_tank']['tank_position'] = 'vent'
+ # CS 25.969: Vent tank capacity must at least be equal to 2 percent of tank capacity (1 percent per side).
+ dict_tank_design['vent_tank']['energy_required'] = 0.01*wing_tank_energy_amount
+ vent_tank_outer_surface = 'outer_vent_tank_section'
+
+ # Calculate energy contained in vent tank iteratively. Position of inner surface is adjusted in 1 mm steps.
+ vent_tank_energy = 0
+ while vent_tank_energy < dict_tank_design['vent_tank']['energy_required']:
+ vent_tank_volume = calculate_obelisk_volume(dict_ac_data['obelisk_volume_calculation_method'],
+ wing_geometry_dict,
+ vent_tank_inner_surface, vent_tank_outer_surface)
+ vent_tank_volume_actual = factor_volume_usable*temperature_expansion_allowance*vent_tank_volume
+ vent_tank_energy = vent_tank_volume_actual*kerosene_volumetric_energy_density
+ wing_section_dict[vent_tank_inner_surface]['span_index'] -= 1
+
+ # Update x position of 'section_2' aka. 'vent_tank_inner_surface'.
+ span_idx = wing_section_dict[vent_tank_inner_surface]['span_index']
+ wing_section_dict[vent_tank_inner_surface]['position']['x'] = (
+ wing_geometry_dict['interpolated_values']['x_coordinate_leading_edge'][span_idx])
+ wing_section_dict[vent_tank_inner_surface]['position']['y'] = span_idx/100
+
+ # TODO: Eventuell löschen, wenn plot nicht mehr benötigt.
+ dict_tank_design['vent_tank']['geometry'] = {}
+ dict_tank_design['vent_tank']['geometry']['total'] = {}
+ dict_tank_design['vent_tank']['geometry']['total']['position'] = {}
+ dict_tank_design['vent_tank']['geometry']['total']['position']['x'] = (
+ wing_geometry_dict['interpolated_values']['x_coordinate_front_spar'][span_idx])
+ dict_tank_design['vent_tank']['geometry']['total']['position']['y'] = (
+ wing_section_dict[vent_tank_inner_surface]['position']['y'])
+ dict_tank_design['vent_tank']['geometry']['inner_surface'] = {}
+ dict_tank_design['vent_tank']['geometry']['inner_surface']['width'] = (
+ wing_geometry_dict['interpolated_values']['tank_lengths'][span_idx])
+ dict_tank_design['vent_tank']['volume_available'] = vent_tank_volume_actual
+ dict_tank_design['vent_tank']['energy_available'] = vent_tank_energy
+ # Print.
+ runtime_output.print('Vent tank (located near each wing tip) calculated.')
+
+ print_outputs = False
+ energy_wing_tank_without_center_tank, energy_wing_tank_with_center_tank = calculate_wing_tanks_volume()
+ print_outputs = True
+ calculate_vent_tank_volume(energy_wing_tank_with_center_tank)
+ energy_wing_tank_without_center_tank, energy_wing_tank_with_center_tank = calculate_wing_tanks_volume()
+ # calculate_wing_tanks_volume()
+ # output is volume_wing_tank_with_center_tank
+ # this is input for calculate_vent_tank()
+ # then calculate_wing_tanks_volume()
+ # -------------------------- END OF NEW VENT TANK CALCULATION -------------------------
+
+ # -------------------------- START OF OLD VENT TANK CALCULATION -------------------------
+ # """Calculate vent tank."""
+ # # § 25.969 Fuel tank expansion space. Each fuel tank must have an expansion space of not less than 2 percent
+ # # of the tank capacity. It must be impossible to fill the expansion space inadvertently with the airplane in the
+ # # normal ground attitude. For pressure fueling systems, compliance with this section may be shown with the means
+ # # provided to comply with §25.979(b).
+ # # Add vent tank to tank design dict.
+ # dict_tank_design['vent_tank'] = {}
+ # dict_tank_design['vent_tank']['tank_location'] = 'wing'
+ # dict_tank_design['vent_tank']['tank_position'] = 'vent'
+ # # CS 25.969: Vent tank capacity must at least be equal to 2 percent of tank capacity (1 percent per side).
+ # dict_tank_design['vent_tank']['energy_required'] = 0.01*mission_energy_amount
+ # vent_tank_outer_surface = 'outer_vent_tank_section'
+
+ # # Calculate energy contained in vent tank iteratively. Position of inner surface is adjusted in 1 mm steps.
+ # vent_tank_energy = 0
+ # while vent_tank_energy < dict_tank_design['vent_tank']['energy_required']:
+ # vent_tank_volume = calculate_obelisk_volume(dict_ac_data['obelisk_volume_calculation_method'],
+ # wing_geometry_dict,
+ # vent_tank_inner_surface, vent_tank_outer_surface)
+ # vent_tank_volume_actual = factor_volume_usable*temperature_expansion_allowance*vent_tank_volume
+ # vent_tank_energy = vent_tank_volume_actual*kerosene_volumetric_energy_density
+ # wing_section_dict[vent_tank_inner_surface]['span_index'] -= 1
+
+ # # Update x position of 'section_2' aka. 'vent_tank_inner_surface'.
+ # span_idx = wing_section_dict[vent_tank_inner_surface]['span_index']
+ # wing_section_dict[vent_tank_inner_surface]['position']['x'] = (
+ # wing_geometry_dict['interpolated_values']['x_coordinate_leading_edge'][span_idx])
+ # wing_section_dict[vent_tank_inner_surface]['position']['y'] = span_idx/100
+
+ # # TODO: Eventuell löschen, wenn plot nicht mehr benötigt.
+ # dict_tank_design['vent_tank']['geometry'] = {}
+ # dict_tank_design['vent_tank']['geometry']['total'] = {}
+ # dict_tank_design['vent_tank']['geometry']['total']['position'] = {}
+ # dict_tank_design['vent_tank']['geometry']['total']['position']['x'] = (
+ # wing_geometry_dict['interpolated_values']['x_coordinate_front_spar'][span_idx])
+ # dict_tank_design['vent_tank']['geometry']['total']['position']['y'] = (
+ # wing_section_dict[vent_tank_inner_surface]['position']['y'])
+ # dict_tank_design['vent_tank']['geometry']['inner_surface'] = {}
+ # dict_tank_design['vent_tank']['geometry']['inner_surface']['width'] = (
+ # wing_geometry_dict['interpolated_values']['tank_lengths'][span_idx])
+ # dict_tank_design['vent_tank']['volume_available'] = vent_tank_volume_actual
+ # dict_tank_design['vent_tank']['energy_available'] = vent_tank_energy
+ # # Print.
+ # runtime_output.print('Vent tank (located near each wing tip) calculated.')
+
+ # """Calculate tank volumes (wing geometry does not change from here)."""
+ # # Initialize parameter.
+ # actual_volume_center_tank = 0
+ # actual_volume_without_center_tank = 0
+
+ # # Iterate through tank entities.
+ # wing_tank_entity_list = [key for key, value in dict_tank_design.items() if key.startswith('tank_')
+ # and key[5:].isdigit() and value['tank_location'] == 'wing']
+ # for wing_tank_entity in wing_tank_entity_list:
+ # # Initialize empty dictionary and lists.
+ # dict_tank_design[wing_tank_entity]['geometry'] = {}
+ # dict_tank_design[wing_tank_entity]['geometry']['inner_surface'] = {}
+ # dict_tank_design[wing_tank_entity]['geometry']['outer_surface'] = {}
+ # inner_surface_str = str()
+ # outer_surface_str = str()
+
+ # if wing_symmetry:
+ # if number_of_wing_sections == 4:
+ # # Set sections depending on tank position.
+ # match dict_tank_design[wing_tank_entity]['tank_position']:
+ # case 'inner_left' | 'inner_right':
+ # inner_surface_str = 'section_0'
+ # outer_surface_str = 'section_1'
+ # case 'outer_left' | 'outer_right':
+ # inner_surface_str = 'section_1'
+ # outer_surface_str = 'section_2'
+ # case 'center':
+ # inner_surface_str = 'fuselage_center_line'
+ # outer_surface_str = 'outer_center_tank_section'
+ # else:
+ # runtime_output.critical('Error: Wing without kink not implemented yet! Program aborted.')
+ # sys.exit(1)
+ # else:
+ # runtime_output.critical('Error: Wing not symmetric! '
+ # + 'Program aborted.')
+ # sys.exit(1)
+
+ # # Calculate obelisk volume.
+ # obelisk_volume = calculate_obelisk_volume(dict_ac_data['obelisk_volume_calculation_method'],
+ # wing_geometry_dict, inner_surface_str, outer_surface_str)
+ # # Calculate actual tank volume (considering volume loss due to internal structure of integral tanks and buffer
+ # # for temperature-dependent expansion of fuel).
+ # if dict_tank_design[wing_tank_entity]['tank_position'] == 'center':
+ # obelisk_volume *= 2
+ # actual_volume = factor_volume_usable*temperature_expansion_allowance*obelisk_volume
+ # # Sum up volume of all tanks except wing center tank.
+ # if dict_tank_design[wing_tank_entity]['tank_position'] != 'center':
+ # actual_volume_without_center_tank += actual_volume
+ # # Set volume of wing center tank.
+ # else:
+ # actual_volume_center_tank = actual_volume
+
+ # # Write data to 'dict_tank_design'.
+ # dict_tank_design[wing_tank_entity]['volume_available'] = actual_volume
+ # dict_tank_design[wing_tank_entity]['energy_available'] = (
+ # actual_volume*kerosene_volumetric_energy_density)
+ # # Print.
+ # # inner left wing tank (ID="0") calculated. Volume (energy) available: 3.51 l ().
+ # # f'{a*1000:,.2f}'
+ # if dict_tank_design[wing_tank_entity]['tank_position'] == 'center':
+ # runtime_output.print('Wing center tank (' + wing_tank_entity + ') calculated. '
+ # + 'Volume (energy) available: ' + f"{actual_volume:,.2f}" + ' L ('
+ # + f"{dict_tank_design[wing_tank_entity]['energy_available']/1e6:,.2f}" + ' MJ)')
+ # else:
+ # print_position = (dict_tank_design[wing_tank_entity]['tank_position'].split('_')[0].capitalize()
+ # + ' ' + dict_tank_design[wing_tank_entity]['tank_position'].split('_')[1] + ' ')
+ # runtime_output.print(print_position + 'wing tank (' + wing_tank_entity + ') calculated. '
+ # + 'Volume (energy) available: ' + f"{actual_volume:,.2f}" + ' L ('
+ # + f"{dict_tank_design[wing_tank_entity]['energy_available']/1e6:,.2f}" + ' MJ)')
+
+ # # Calculate tank mass (equals zero due to integral tank).
+ # dict_tank_design[wing_tank_entity]['geometry']['total'] = {}
+ # dict_tank_design[wing_tank_entity]['geometry']['total']['mass'] = 0.0
+ # # Set inertia to zero.
+ # inertia_list = ['j_xx', 'j_yy', 'j_zz', 'j_xy', 'j_xz', 'j_yx', 'j_yz', 'j_zx', 'j_zy']
+ # dict_tank_design[wing_tank_entity]['geometry']['total']['inertia'] = {}
+ # for inertia in inertia_list:
+ # dict_tank_design[wing_tank_entity]['geometry']['total']['inertia'][inertia] = 0.0
+ # # Center of gravity equals zero since integral tank has no mass.
+ # dict_tank_design[wing_tank_entity]['geometry']['total']['center_of_gravity'] = {}
+ # dict_tank_design[wing_tank_entity]['geometry']['total']['center_of_gravity']['x'] = 0.0
+ # dict_tank_design[wing_tank_entity]['geometry']['total']['center_of_gravity']['y'] = 0.0
+ # dict_tank_design[wing_tank_entity]['geometry']['total']['center_of_gravity']['z'] = 0.0
+
+ # # Calculate position of tank entity (foremost point of tank).
+ # dict_tank_design[wing_tank_entity]['geometry']['total']['position'] = {}
+ # dict_tank_design[wing_tank_entity]['geometry']['total']['position']['x'] = (
+ # wing_geometry_dict['interpolated_values']['x_coordinate_front_spar'][
+ # wing_section_dict[inner_surface_str]['span_index']
+ # ])
+ # if (dict_tank_design[wing_tank_entity]['tank_position'] == 'inner_left') or (
+ # dict_tank_design[wing_tank_entity]['tank_position'] == 'outer_left'):
+ # dict_tank_design[wing_tank_entity]['geometry']['total']['position']['y'] = -abs(
+ # wing_section_dict[inner_surface_str]['position']['y'])
+ # else:
+ # dict_tank_design[wing_tank_entity]['geometry']['total']['position']['y'] = abs(
+ # wing_section_dict[inner_surface_str]['position']['y'])
+ # dict_tank_design[wing_tank_entity]['geometry']['total']['position']['z'] = (
+ # wing_section_dict[inner_surface_str]['position']['z'])
+ # # Direction.
+ # dict_tank_design[wing_tank_entity]['geometry']['total']['direction'] = {}
+ # dict_tank_design[wing_tank_entity]['geometry']['total']['direction']['x'] = 0
+ # dict_tank_design[wing_tank_entity]['geometry']['total']['direction']['y'] = 1
+ # dict_tank_design[wing_tank_entity]['geometry']['total']['direction']['z'] = 0
+ # # Set required energy.
+ # dict_tank_design[wing_tank_entity]['energy_required_for_mission'] = True
+
+ # # Add required output data: x, y, and z position, shape, height, width, and length.
+ # for surface_str, surface_name in zip([inner_surface_str, outer_surface_str],
+ # ['inner_surface', 'outer_surface']):
+ # surface_data = wing_section_dict[surface_str]
+ # span_idx = surface_data['span_index']
+ # # Inner surface equals tank entity position.
+ # if surface_name == 'inner_surface':
+ # x_coordinate = 0.0
+ # y_coordinate = 0.0
+ # z_coordinate = 0.0
+ # else:
+ # # Adjust y coordinate for left hand tanks.
+ # y_coordinate_entity = dict_tank_design[wing_tank_entity]['geometry']['total']['position']['y']
+ # if 'left' in dict_tank_design[wing_tank_entity]['tank_position']:
+ # y_coordinate_section = -surface_data['position']['y']
+ # y_coordinate = -(abs(y_coordinate_section) - abs(y_coordinate_entity))
+ # else:
+ # y_coordinate_section = surface_data['position']['y']
+ # y_coordinate = (abs(y_coordinate_section) - abs(y_coordinate_entity))
+ # # old
+ # # y_coordinate = y_coordinate_section - y_coordinate_entity
+ # # NEW:
+ # # y_coordinate = -(abs(y_coordinate_section) - abs(y_coordinate_entity))
+ # # if 'left' in dict_tank_design[wing_tank_entity]['tank_position']:
+ # # y_coordinate = y_coordinate*(-1)
+ # # x coordinate.
+ # x_coordinate_entity = dict_tank_design[wing_tank_entity]['geometry']['total']['position']['x']
+ # x_coordinate_section = wing_geometry_dict['interpolated_values']['x_coordinate_front_spar'][span_idx]
+ # if x_coordinate_entity < 0 and x_coordinate_section > 0 and x_coordinate_section > x_coordinate_entity:
+ # delta_x = x_coordinate_entity - x_coordinate_section
+ # else:
+ # delta_x = x_coordinate_section - x_coordinate_entity
+ # x_coordinate = delta_x
+ # # z coordinate.
+ # z_coordinate_entity = dict_tank_design[wing_tank_entity]['geometry']['total']['position']['z']
+ # z_coordinate_section = surface_data['position']['z']
+ # z_coordinate = z_coordinate_section - z_coordinate_entity
+
+ # dict_tank_design[wing_tank_entity]['geometry'][surface_name] = {
+ # 'section_name': surface_str,
+ # 'position': {
+ # 'x': x_coordinate,
+ # 'y': y_coordinate,
+ # 'z': z_coordinate,
+ # },
+ # 'shape': 'rectangular',
+ # 'height': wing_geometry_dict['interpolated_values']['tank_heights'][span_idx],
+ # 'width': wing_geometry_dict['interpolated_values']['tank_lengths'][span_idx],
+ # 'length': 0.0
+ # }
+
+ # # Correct wing center tank information.
+ # if 'center' in dict_tank_design[wing_tank_entity]['tank_position']:
+ # dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['position']['y'] = (
+ # dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['position']['y']/2
+ # )
+ # dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['position']['y'] = -(
+ # dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['position']['y']
+ # )
+
+ # # Centroid.
+ # # Assumption: inner surface area always greater than outer surface area.
+ # inner_surface_area = (dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['height']
+ # *dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['width'])
+ # outer_surface_area = (dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['height']
+ # *dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['width'])
+ # y_position_outer_surface = dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['position']['y']
+ # y_position_inner_surface = dict_tank_design[wing_tank_entity]['geometry']['total']['position']['y']
+ # tank_span = y_position_outer_surface - y_position_inner_surface
+ # y_position_center_of_mass = y_position_inner_surface + (tank_span/4*((inner_surface_area
+ # + 2*math.sqrt(inner_surface_area*outer_surface_area)
+ # + outer_surface_area)/(inner_surface_area + outer_surface_area)))
+ # centroid_y = y_position_inner_surface + ((tank_span
+ # *((dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['height']
+ # *dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['width'])
+ # +(dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['height']
+ # *dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['width'])
+ # +(dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['height']
+ # *dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['width'])
+ # +(3*dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['height']
+ # *dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['width'])))
+ # /(2
+ # *(2*dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['height']
+ # *dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['width'])
+ # + (dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['height']
+ # *dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['width'])
+ # + (dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['height']
+ # *dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['width'])
+ # + (2*dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['height']
+ # *dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['width'])))
+ # x_position_cog_inner_surface = dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['width']/2
+ # x_position_cog_outer_surface = dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['width']/2
+ # z_position_cog_inner_surface = dict_tank_design[wing_tank_entity]['geometry']['inner_surface']['height']/2
+ # z_position_cog_outer_surface = dict_tank_design[wing_tank_entity]['geometry']['outer_surface']['height']/2
+ # x_position_center_of_mass = ((inner_surface_area*x_position_cog_inner_surface
+ # + outer_surface_area*x_position_cog_outer_surface)
+ # /(inner_surface_area + outer_surface_area))
+ # z_position_center_of_mass = ((inner_surface_area*z_position_cog_inner_surface
+ # + outer_surface_area*z_position_cog_outer_surface)
+ # /(inner_surface_area + outer_surface_area))
+
+ # dict_tank_design[wing_tank_entity]['geometry']['total']['centroid'] = {}
+ # if wing_tank_entity == wing_center_tank_entity:
+ # dict_tank_design[wing_tank_entity]['geometry']['total']['centroid']['x'] = x_position_center_of_mass
+ # # dict_tank_design[wing_tank_entity]['geometry']['total']['centroid']['x'] = (
+ # # dict_tank_design['tank_4']['geometry']['inner_surface']['position']['x']
+ # # + dict_tank_design['tank_4']['geometry']['inner_surface']['width']/2
+ # # )
+ # dict_tank_design[wing_tank_entity]['geometry']['total']['centroid']['y'] = 0
+ # dict_tank_design[wing_tank_entity]['geometry']['total']['centroid']['z'] = 0
+ # else:
+ # dict_tank_design[wing_tank_entity]['geometry']['total']['centroid']['x'] = x_position_center_of_mass
+ # dict_tank_design[wing_tank_entity]['geometry']['total']['centroid']['y'] = y_position_center_of_mass
+ # dict_tank_design[wing_tank_entity]['geometry']['total']['centroid']['z'] = z_position_center_of_mass
+
+ # # Sum up.
+ # volume_wing_tank_without_center_tank = actual_volume_without_center_tank
+ # volume_wing_tank_with_center_tank = actual_volume_without_center_tank + actual_volume_center_tank
+
+ # """Calculate fuel mass and energy."""
+ # # Convert wing fuel volume to energy.
+ # energy_wing_tank_without_center_tank = (volume_wing_tank_without_center_tank
+ # *kerosene_volumetric_energy_density)
+ # energy_wing_tank_with_center_tank = (volume_wing_tank_with_center_tank
+ # *kerosene_volumetric_energy_density)
+
+ # -------------------------- END OF OLD VENT TANK CALCULATION -------------------------
+
+ """Check if tanks can store required energy."""
+ # If left and right inner and outer wing tanks are big enough to store required amount of energy, wing center tank
+ # remains empty.
+ if energy_wing_tank_without_center_tank >= mission_energy_amount:
+ dict_tank_design[wing_center_tank_entity]['volume_available'] = 0
+ dict_tank_design[wing_center_tank_entity]['energy_available'] = 0
+
+ # Prints.
+ runtime_output.print('Wing tanks successfully calculated.')
+ runtime_output.debug('Debug: The "calculate_wing_tanks" function was successfully executed.')
+
+ # Prepare data output.
+ dict_tank_design['tmp_energies'] = {}
+ dict_tank_design['tmp_energies']['wing_tank_without_center_tank'] = float(energy_wing_tank_without_center_tank)
+ dict_tank_design['tmp_energies']['wing_tank_with_center_tank'] = float(energy_wing_tank_with_center_tank)
+
+ return dict_tank_design
+
+
+def calculate_additional_center_tank(dict_ac_data, dict_tank_design, runtime_output, energy_demand_covered):
+ """Calculate energy contained in additional center tank.
+
+ This code enables the installation of an additional center tank as LD3-45 container. Therefore, it is checked
+ initially whether the existing cargo compartment provides sufficient height. If this is not the case, all export
+ values are set to zero. Otherwise, the LD3-45 container is installed 10 cm behind the end of the landing gear bay.
+ It is assumed that this is approximately in line with the trailing edge of the wing. The volume and dimensions of
+ the container are taken from [1].
+
+ Attention: Please note that it is not possible to calculate more than one additional center tank at the moment!
+
+ [1] https://www.lufthansa-cargo.com/de/fleet-ulds/ulds/containers
+
+ :param dict dict_design: Dictionary containing data from aircraft exchange and module configuration file
+ :param dict dict_tank_design: Dictionary containing tank design parameter
+ :param logging.Logger runtime_output: Logging object used for capturing log messages in the module
+ :param energy_demand_covered: Information if mission energy demand already covered
+ :return dict dict_tank_design: Dictionary containing tank design parameter
+ """
+ # Extract necessary data from 'dict_ac_data'.
+ factor_volume_usable = dict_ac_data['factor_volume_usable']
+ temperature_expansion_allowance = dict_ac_data['temperature_expansion_allowance']
+
+ # Extract kerosene energy density from library.
+ kerosene_volumetric_energy_density = constants.KEROSENE_VOLUMETRIC_ENERGY_DENSITY
+
+ # Print.
+ runtime_output.print('Additional center tank design started...')
+
+ # Get all tank entities that are located at the fuselage (additional center tanks).
+ additional_center_tank_entity_list = [k for k, v in dict_tank_design.items() if k.startswith('tank_')
+ and k[5:].isdigit() and v['tank_location'] == 'fuselage']
+ number_of_additional_center_tanks = len(additional_center_tank_entity_list)
+ if number_of_additional_center_tanks > 1:
+ runtime_output.critical('Error: Tank design not possible for more than one additional center tank! '
+ + 'Program aborted.')
+ sys.exit('Exit information: Tank design not possible for more than one additional center tank!')
+ # Extract identifier of center tank.
+ center_tank_entity = additional_center_tank_entity_list[0]
+
+ """Prepare data of LD3-45 container."""
+ # Assumption: Angle at base equals 45 degree and usable volume of container taken from [1] (not calculated).
+ height_container = 1.15
+ width_base_container = 1.53
+ width_top_container = 2.44
+ length_container = 1.56
+ height_base_part_container = (width_top_container - width_base_container)*0.5
+ height_top_part_container = height_container - height_base_part_container
+ volume_container = 3.4
+ # Calculate areas and volumes for later use.
+ area_base_part = width_base_container*length_container
+ area_top_part = width_top_container*length_container
+ volume_base_part = (
+ (height_base_part_container*width_top_container*length_container)
+ - height_base_part_container*height_base_part_container*length_container)
+ volume_top_part = width_top_container*length_container*height_top_part_container
+
+ # Check, if cargo compartment height sufficient to store LD3-45 container.
+ if dict_tank_design['geometry']['fuselage']['cargo_compartment_height'] < height_container:
+ additional_center_tank_design_possible = False
+ runtime_output.warning('Warning: Cargo compartment height too small. Storage of LD3-45 container not '
+ + 'possible. All values are set to 0.')
+ else:
+ additional_center_tank_design_possible = True
+
+ """Calculate additional center tank."""
+ # Calculate usable volume and convert to energy.
+ center_tank_volume = volume_container*factor_volume_usable*temperature_expansion_allowance
+ energy_kerosene_available = center_tank_volume*kerosene_volumetric_energy_density
+ center_tank_volume_l = center_tank_volume*1e3
+ # Calculate ACT and necessary values if possible.
+ if additional_center_tank_design_possible:
+ # Write data to 'dict_tank_design'.
+ dict_tank_design[center_tank_entity]['volume_available'] = center_tank_volume
+ dict_tank_design[center_tank_entity]['energy_available'] = energy_kerosene_available
+ if energy_demand_covered:
+ dict_tank_design[center_tank_entity]['energy_required_for_mission'] = False
+ else:
+ dict_tank_design[center_tank_entity]['energy_required_for_mission'] = True
+
+ # Print.
+ runtime_output.print('Additional center tank (' + center_tank_entity + ') calculated. '
+ + 'Volume (energy) available: ' + f"{center_tank_volume_l:,.2f}" + ' L ('
+ + f"{dict_tank_design[center_tank_entity]['energy_available']/1e6:,.2f}" + ' MJ)')
+
+ # Prepare geometrical data for additional center tank.
+ # Assumption: Landing gear bay ends at wing trailing edge position.
+ # x_coordinate_wing_leading_edge = dict_ac_data['wing_position_x']
+ chord_length_at_fuselage_center_line = (
+ dict_tank_design['geometry']['wing']['sections']['fuselage_center_line']['chord_length'])
+ # x_coordinate_wing_trailing_edge = x_coordinate_wing_leading_edge + chord_length_at_fuselage_center_line
+ buffer = 0.1
+ x_coordinate = chord_length_at_fuselage_center_line + buffer
+ y_coordinate = [width_top_container*0.5, width_base_container*0.5, 0.0,
+ -width_base_container*0.5, -width_top_container*0.5]
+ cargo_floor_below_wing = (dict_tank_design['geometry']['fuselage']['z_coordinate_cargo_floor']
+ < dict_tank_design['geometry']['wing']['position']['z'])
+ z_offset_wing_to_cargo_floor = abs(dict_tank_design['geometry']['wing']['position']['z']
+ - dict_tank_design['geometry']['fuselage']['z_coordinate_cargo_floor'])
+ if cargo_floor_below_wing:
+ relative_z_position_cargo_floor_to_wing = -z_offset_wing_to_cargo_floor
+ else:
+ relative_z_position_cargo_floor_to_wing = z_offset_wing_to_cargo_floor
+ z_coordinate = relative_z_position_cargo_floor_to_wing + np.array([
+ # plane_0
+ height_base_part_container + height_top_part_container*0.5,
+ # plane_1, plane_2, plane_3
+ height_container*0.5, height_container*0.5, height_container*0.5,
+ # plane_4
+ height_base_part_container + height_top_part_container*0.5])
+ heights = [height_top_part_container, height_container, height_container,
+ height_container, height_top_part_container]
+ plane_names = ['cross_section_0', 'cross_section_1', 'cross_section_2', 'cross_section_3', 'cross_section_4']
+
+ # Create the dictionary for center tank geometry.
+ dict_tank_design[center_tank_entity]['geometry'] = {
+ plane: {
+ 'section_name': plane,
+ 'position': {
+ 'x': x_coordinate,
+ 'y': y_coordinate[i],
+ 'z': z_coordinate[i]
+ },
+ 'shape': 'rectangular',
+ 'height': heights[i],
+ 'width': length_container,
+ 'length': 0.0
+ }
+ for i, plane in enumerate(plane_names)
+ }
+
+ # Define total tank geometry values.
+ # Calculate tank mass (equals zero due to integral tank).
+ dict_tank_design[center_tank_entity]['geometry']['total'] = {}
+ dict_tank_design[center_tank_entity]['geometry']['total']['mass'] = 300
+ # Set inertia to zero.
+ inertia_list = ['j_xx', 'j_yy', 'j_zz', 'j_xy', 'j_xz', 'j_yx', 'j_yz', 'j_zx', 'j_zy']
+ dict_tank_design[center_tank_entity]['geometry']['total']['inertia'] = {}
+ for inertia in inertia_list:
+ dict_tank_design[center_tank_entity]['geometry']['total']['inertia'][inertia] = 0.0
+ # Center of gravity.
+ # Prepare data for z coordinate calculation.
+ h = height_base_part_container
+ a_1 = area_top_part
+ a_2 = area_base_part
+ y_0 = ((h*(a_1 + 2*math.sqrt(a_1*a_2) + 3*a_2))
+ /(4*(a_1 + math.sqrt(a_1*a_2)) + a_2))
+ z_coordinate_cog_base_part = (dict_tank_design['geometry']['fuselage']['z_coordinate_cargo_floor']
+ + (h - y_0))
+ z_coordinate_cog_top_part = (dict_tank_design['geometry']['fuselage']['z_coordinate_cargo_floor']
+ + height_base_part_container + height_top_part_container*0.5)
+ z_cog = ((z_coordinate_cog_base_part*volume_base_part + z_coordinate_cog_top_part*volume_top_part)
+ /(volume_base_part + volume_top_part))
+
+ dict_tank_design[center_tank_entity]['geometry']['total']['center_of_gravity'] = {}
+ dict_tank_design[center_tank_entity]['geometry']['total']['center_of_gravity']['x'] = (
+ x_coordinate + length_container*0.5)
+ dict_tank_design[center_tank_entity]['geometry']['total']['center_of_gravity']['y'] = 0.0
+ dict_tank_design[center_tank_entity]['geometry']['total']['center_of_gravity']['z'] = z_cog
+
+ # Calculate position of tank entity (foremost point of tank).
+ dict_tank_design[center_tank_entity]['geometry']['total']['position'] = {}
+ dict_tank_design[center_tank_entity]['geometry']['total']['position']['x'] = x_coordinate
+ dict_tank_design[center_tank_entity]['geometry']['total']['position']['y'] = 0.0
+ dict_tank_design[center_tank_entity]['geometry']['total']['position']['z'] = z_coordinate[2]
+ # Direction.
+ dict_tank_design[center_tank_entity]['geometry']['total']['direction'] = {}
+ dict_tank_design[center_tank_entity]['geometry']['total']['direction']['x'] = 0
+ dict_tank_design[center_tank_entity]['geometry']['total']['direction']['y'] = 1
+ dict_tank_design[center_tank_entity]['geometry']['total']['direction']['z'] = 0
+
+ # Centroid.
+ dict_tank_design[center_tank_entity]['geometry']['total']['centroid'] = {}
+ dict_tank_design[center_tank_entity]['geometry']['total']['centroid']['x'] = length_container/2
+ dict_tank_design[center_tank_entity]['geometry']['total']['centroid']['y'] = 0
+ dict_tank_design[center_tank_entity]['geometry']['total']['centroid']['z'] = z_cog
+
+ else:
+ # Set all export values to 0 if tank design not possible.
+ dict_tank_design[center_tank_entity]['geometry'] = {
+ 'cross_section_0': {
+ 'section_name': 'cross_section_0',
+ 'position': {
+ 'x': 0.0,
+ 'y': 0.0,
+ 'z': 0.0
+ },
+ 'shape': None,
+ 'height': 0.0,
+ 'width': 0.0,
+ 'length': 0.0
+ }
+ }
+ # Tank mass.
+ dict_tank_design[center_tank_entity]['geometry']['total'] = {}
+ dict_tank_design[center_tank_entity]['geometry']['total']['mass'] = 0.0
+ # Inertia.
+ inertia_list = ['j_xx', 'j_yy', 'j_zz', 'j_xy', 'j_xz', 'j_yx', 'j_yz', 'j_zx', 'j_zy']
+ dict_tank_design[center_tank_entity]['geometry']['total']['inertia'] = {}
+ for inertia in inertia_list:
+ dict_tank_design[center_tank_entity]['geometry']['total']['inertia'][inertia] = 0.0
+ # Center of gravity.
+ dict_tank_design[center_tank_entity]['geometry']['total']['center_of_gravity'] = {}
+ dict_tank_design[center_tank_entity]['geometry']['total']['center_of_gravity']['x'] = 0.0
+ dict_tank_design[center_tank_entity]['geometry']['total']['center_of_gravity']['y'] = 0.0
+ dict_tank_design[center_tank_entity]['geometry']['total']['center_of_gravity']['z'] = 0.0
+ # Position of tank entity (foremost point of tank).
+ dict_tank_design[center_tank_entity]['geometry']['total']['position'] = {}
+ dict_tank_design[center_tank_entity]['geometry']['total']['position']['x'] = 0.0
+ dict_tank_design[center_tank_entity]['geometry']['total']['position']['y'] = 0.0
+ dict_tank_design[center_tank_entity]['geometry']['total']['position']['z'] = 0.0
+ # Direction.
+ dict_tank_design[center_tank_entity]['geometry']['total']['direction'] = {}
+ dict_tank_design[center_tank_entity]['geometry']['total']['direction']['x'] = 0
+ dict_tank_design[center_tank_entity]['geometry']['total']['direction']['y'] = 1
+ dict_tank_design[center_tank_entity]['geometry']['total']['direction']['z'] = 0
+ # Centroid.
+ dict_tank_design[center_tank_entity]['geometry']['total']['centroid'] = {}
+ dict_tank_design[center_tank_entity]['geometry']['total']['centroid']['x'] = 0
+ dict_tank_design[center_tank_entity]['geometry']['total']['centroid']['y'] = 0
+ dict_tank_design[center_tank_entity]['geometry']['total']['centroid']['z'] = 0
+
+ # Prints.
+ runtime_output.print('Additional center tank design completed.')
+ runtime_output.debug('Debug: The "calculate_additional_center_tank" function was successfully executed.')
+
+ # Prepare data output.
+ dict_tank_design['tmp_energies'] = {}
+ dict_tank_design['tmp_energies']['additional_center_tank'] = float(energy_kerosene_available)
+
+ return dict_tank_design
+
+
+def calculate_trim_tank(dict_ac_data, dict_tank_design, runtime_output, energy_demand_covered):
+ """Calculate energy contained in trim tank.
+
+ [Add some more information here...]
+
+ :param dict dict_design: Dictionary containing data from aircraft exchange and module configuration file
+ :param dict dict_tank_design: Dictionary containing tank design parameter
+ :param logging.Logger runtime_output: Logging object used for capturing log messages in the module
+ :param energy_demand_covered: Information if mission energy demand already covered
+ :return dict dict_tank_design: Dictionary containing tank design parameter
+ """
+ #TODO: Implement vent tank design from wing tank.
+ # Extract values from 'dict_ac_data'.
+ factor_volume_usable = dict_ac_data['factor_volume_usable']
+ temperature_expansion_allowance = dict_ac_data['temperature_expansion_allowance']
+ # Extract kerosene energy density from library.
+ kerosene_volumetric_energy_density = constants.KEROSENE_VOLUMETRIC_ENERGY_DENSITY
+
+ # Print.
+ runtime_output.print('Trim tank design started...')
+
+ geometry_dict = dict_tank_design['geometry']['horizontal_stabilizer']
+ section_dict = dict_tank_design['geometry']['horizontal_stabilizer']['sections']
+ symmetry = dict_tank_design['geometry']['horizontal_stabilizer']['information']['symmetry']
+
+ # Get all tank entities that are located at the horizontal stabilizer (trim tank).
+ tank_entity = [k for k, v in dict_tank_design.items() if k.startswith('tank_') and k[5:].isdigit()
+ and v['tank_location'] == 'horizontal_stabilizer'][0]
+
+ # Calculate distance from wing root to wing tip.
+ span = section_dict['tip']['position']['y'] - section_dict['fuselage_center_line']['position']['y']
+ # Calculate span offset for tank.
+ outer_tank_span_offset = -(span*dict_ac_data['buffer_outer_tank_segment'])
+
+ # Set tank sections according to number of wing sections.
+ number_of_sections = len(section_dict)
+ if number_of_sections < 2:
+ runtime_output.critical('Error: Not enough horizontal stabilizer sections given. Program aborted.')
+ sys.exit(1)
+ elif number_of_sections ==2:
+ sections = {'section_0': 'fuselage_center_line',
+ 'section_1': 'tip'}
+ # Span offsets for 'section_0' and 'section_1'.
+ span_offset_list = [0.0, outer_tank_span_offset]
+ elif number_of_sections == 3:
+ sections = {'section_0': 'fuselage_center_line',
+ 'section_1': 'tip'}
+ # Span offsets for 'section_0' and 'section_1'.
+ span_offset_list = [0.0, outer_tank_span_offset]
+ else:
+ runtime_output.critical('Error: Too many horizontal stabilizer sections given. '
+ + 'Program aborted.')
+ sys.exit(1)
+
+ # Prepare tank sections.
+ i = 0
+ for sec, template in sections.items():
+ section_dict[sec] = {}
+ section_dict[sec]['position'] = {}
+ section_dict[sec]['position']['y'] = section_dict[template]['position']['y'] + span_offset_list[i]
+ section_dict[sec]['span_index'] = int(round(section_dict[sec]['position']['y']*100, 0))
+ section_dict[sec]['position']['x'] = (
+ geometry_dict['interpolated_values']['x_coordinate_leading_edge'][section_dict[sec]['span_index']])
+ section_dict[sec]['position']['z'] = (
+ geometry_dict['interpolated_values']['z_coordinate_leading_edge'][section_dict[sec]['span_index']])
+ i += 1
+
+ """Calculate tank volumes (geometry does not change from here)."""
+ # Initialize empty dictionary and lists.
+ dict_tank_design[tank_entity]['geometry'] = {}
+ dict_tank_design[tank_entity]['geometry']['inner_surface'] = {}
+ dict_tank_design[tank_entity]['geometry']['outer_surface'] = {}
+ inner_surface_str = str()
+ outer_surface_str = str()
+
+ if symmetry:
+ if number_of_sections == 2:
+ inner_surface_str = 'section_0'
+ outer_surface_str = 'section_1'
+ elif number_of_sections == 3:
+ inner_surface_str = 'section_0'
+ outer_surface_str = 'section_1'
+ else:
+ runtime_output.critical('Error: Horizontal stabilizer not symmetric! Program aborted.')
+ sys.exit(1)
+
+ # Calculate obelisk volume.
+ obelisk_volume = calculate_obelisk_volume(dict_ac_data['obelisk_volume_calculation_method'],
+ geometry_dict, inner_surface_str, outer_surface_str)
+ obelisk_volume *= 2
+
+ # Calculate actual tank volume (considering volume loss due to internal structure of integral tanks and buffer for
+ # temperature-dependent expansion of fuel).
+ volume_trim_tank = factor_volume_usable*temperature_expansion_allowance*obelisk_volume
+
+ # Calculate energy and write data to 'dict_tank_design'.
+ dict_tank_design[tank_entity]['volume_available'] = volume_trim_tank
+ dict_tank_design[tank_entity]['energy_available'] = (
+ volume_trim_tank*kerosene_volumetric_energy_density)
+ if energy_demand_covered:
+ dict_tank_design[tank_entity]['energy_required_for_mission'] = False
+ else:
+ dict_tank_design[tank_entity]['energy_required_for_mission'] = True
+
+ # Add required output data: x, y, and z position, shape, height, width, and length.
+ for surface_str, surface_name in zip([inner_surface_str, outer_surface_str], ['inner_surface', 'outer_surface']):
+ surface_data = section_dict[surface_str]
+ span_idx = surface_data['span_index']
+
+ # Extract x and z coordinates.
+ x_coordinate = geometry_dict['interpolated_values']['x_coordinate_front_spar'][span_idx]
+ y_coordinate = surface_data['position']['y']
+ z_coordinate = surface_data['position']['z']
+
+ dict_tank_design[tank_entity]['geometry'][surface_name] = {
+ 'section_name': surface_str,
+ 'position': {
+ 'x': x_coordinate,
+ 'y': y_coordinate,
+ 'z': z_coordinate,
+ },
+ 'shape': 'rectangular',
+ 'height': geometry_dict['interpolated_values']['tank_heights'][span_idx],
+ 'width': geometry_dict['interpolated_values']['tank_lengths'][span_idx],
+ 'length': 0.0
+ }
+ # Rename and restructure dict.
+ dict_tank_design[tank_entity]['geometry']['cross_section_1'] = dict_tank_design[tank_entity]['geometry'].pop(
+ 'inner_surface')
+ dict_tank_design[tank_entity]['geometry']['cross_section_2'] = dict_tank_design[tank_entity]['geometry'].pop(
+ 'outer_surface')
+
+ def deep_copy_dict(d):
+ if isinstance(d, dict):
+ return {key: deep_copy_dict(value) for key, value in d.items()}
+ elif isinstance(d, list):
+ return [deep_copy_dict(item) for item in d]
+ else:
+ return d
+
+ independent_copy = deep_copy_dict(dict_tank_design[tank_entity]['geometry']['cross_section_2'])
+ independent_copy['position']['y'] *= -1
+ dict_tank_design[tank_entity]['geometry']['cross_section_0'] = independent_copy
+
+ """Set or calculate total tank parameters."""
+ # Set tank mass to zero (integral tank).
+ dict_tank_design[tank_entity]['geometry']['total'] = {}
+ dict_tank_design[tank_entity]['geometry']['total']['mass'] = 0.0
+ # Set inertia to zero.
+ inertia_list = ['j_xx', 'j_yy', 'j_zz', 'j_xy', 'j_xz', 'j_yx', 'j_yz', 'j_zx', 'j_zy']
+ dict_tank_design[tank_entity]['geometry']['total']['inertia'] = {}
+ for inertia in inertia_list:
+ dict_tank_design[tank_entity]['geometry']['total']['inertia'][inertia] = 0.0
+ # Center of gravity equals zero since integral tank has no mass.
+ dict_tank_design[tank_entity]['geometry']['total']['center_of_gravity'] = {}
+ dict_tank_design[tank_entity]['geometry']['total']['center_of_gravity']['x'] = 0.0
+ dict_tank_design[tank_entity]['geometry']['total']['center_of_gravity']['y'] = 0.0
+ dict_tank_design[tank_entity]['geometry']['total']['center_of_gravity']['z'] = 0.0
+ # Calculate position of tank entity (foremost point of tank).
+ distance_wing_to_horizontal_stabilizer = (dict_tank_design['geometry']['horizontal_stabilizer']['position']['x']
+ - dict_tank_design['geometry']['wing']['position']['x'])
+ wing_lower_than_horizontal_stabilizer = (dict_tank_design['geometry']['wing']['position']['z']
+ < dict_tank_design['geometry']['horizontal_stabilizer']['position']['z'])
+ z_offset_wing_to_horizontal_stabilizer = abs(dict_tank_design['geometry']['horizontal_stabilizer']['position']['z']
+ - dict_tank_design['geometry']['wing']['position']['z'])
+ if wing_lower_than_horizontal_stabilizer:
+ relative_z_position_horizontal_stabilizer_to_wing = z_offset_wing_to_horizontal_stabilizer
+ else:
+ relative_z_position_horizontal_stabilizer_to_wing = -z_offset_wing_to_horizontal_stabilizer
+ dict_tank_design[tank_entity]['geometry']['total']['position'] = {}
+ dict_tank_design[tank_entity]['geometry']['total']['position']['x'] = (
+ distance_wing_to_horizontal_stabilizer
+ + geometry_dict['interpolated_values']['x_coordinate_front_spar'][section_dict[inner_surface_str]
+ ['span_index']])
+ dict_tank_design[tank_entity]['geometry']['total']['position']['y'] = (
+ section_dict[inner_surface_str]['position']['y'])
+ dict_tank_design[tank_entity]['geometry']['total']['position']['z'] = (
+ relative_z_position_horizontal_stabilizer_to_wing)
+ # Direction.
+ dict_tank_design[tank_entity]['geometry']['total']['direction'] = {}
+ dict_tank_design[tank_entity]['geometry']['total']['direction']['x'] = 0
+ dict_tank_design[tank_entity]['geometry']['total']['direction']['y'] = 1
+ dict_tank_design[tank_entity]['geometry']['total']['direction']['z'] = 0
+
+ # Centroid.
+ # Assumption: inner surface area always greater than outer surface area.
+ inner_surface = dict_tank_design['tank_5']['geometry']['cross_section_1']
+ outer_surface = dict_tank_design['tank_5']['geometry']['cross_section_2']
+ inner_surface_area = (inner_surface['height']
+ *inner_surface['width'])
+ outer_surface_area = (outer_surface['height']
+ *outer_surface['width'])
+ y_position_outer_surface = outer_surface['position']['y']
+ y_position_inner_surface = inner_surface['position']['y']
+ tank_span = y_position_outer_surface - y_position_inner_surface
+ y_position_center_of_mass = 0
+ centroid_y = 0
+ x_position_cog_inner_surface = inner_surface['width']/2
+ x_position_cog_outer_surface = outer_surface['width']/2
+ z_position_cog_inner_surface = inner_surface['height']/2
+ z_position_cog_outer_surface = outer_surface['height']/2
+ x_position_center_of_mass = ((inner_surface_area*x_position_cog_inner_surface
+ + outer_surface_area*x_position_cog_outer_surface)
+ /(inner_surface_area + outer_surface_area))
+ z_position_center_of_mass = ((inner_surface_area*z_position_cog_inner_surface
+ + outer_surface_area*z_position_cog_outer_surface)
+ /(inner_surface_area + outer_surface_area))
+
+ dict_tank_design[tank_entity]['geometry']['total']['centroid'] = {}
+ dict_tank_design[tank_entity]['geometry']['total']['centroid']['x'] = x_position_center_of_mass
+ dict_tank_design[tank_entity]['geometry']['total']['centroid']['y'] = y_position_center_of_mass
+ dict_tank_design[tank_entity]['geometry']['total']['centroid']['z'] = z_position_center_of_mass
+
+ # Transform volume to liter for print.
+ volume_trim_tank_l = volume_trim_tank*1e3
+ # Print.
+ runtime_output.print('Trim tank (' + tank_entity + ') calculated. '
+ + 'Volume (energy) available: ' + f"{volume_trim_tank_l:,.2f}" + ' L ('
+ + f"{dict_tank_design[tank_entity]['energy_available']/1e6:,.2f}" + ' MJ)')
+
+ # Prints.
+ runtime_output.print('Trim tank design completed.')
+ runtime_output.debug('Debug: The "calculate_trim_tank" function was successfully executed.')
+
+ # Prepare data output.
+ dict_tank_design['tmp_energies'] = {}
+ dict_tank_design['tmp_energies']['trim_tank'] = float(dict_tank_design[tank_entity]['energy_available'])
+
+ return dict_tank_design
diff --git a/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/kerosene/methodkerosene.py b/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/kerosene/methodkerosene.py
index 7b7223856943eb44de11c3d25328a448a884e289..63cb3425b48b635435dc0e9ddf133fd10d3f4822 100644
--- a/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/kerosene/methodkerosene.py
+++ b/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/kerosene/methodkerosene.py
@@ -59,6 +59,6 @@ def method_kerosene(paths_and_names, routing_dict, dict_ac_exchange, dict_mod_co
# Debug print.
runtime_output.debug('Debug: The "method_kerosene" function was successfully executed.')
- runtime_output.print('Tank design successfully completed.')
+ runtime_output.print('Tank design completed.')
return kerosene_output_dict
diff --git a/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/usermethoddatapreparation.py b/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/usermethoddatapreparation.py
index df5b8efa8dd1477bbd2ddad9872dd0854f0ddd93..8b8525a535177b507ca76bbe0168be588721e4c4 100644
--- a/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/usermethoddatapreparation.py
+++ b/tank_design/src/tube_and_wing/empirical/tank_design_tu_berlin/usermethoddatapreparation.py
@@ -1,494 +1,499 @@
-"""Module providing functions for the preparation of user data."""
-import pycoordinatesystemconversion as py11csc
-
-
-def user_method_data_input_preparation(routing_dict):
- """Prepare necessary input data for the user method from aircraft exchange and module configuration files.
-
- In this function, the user is responsible for preparing the data needed for the user method. Relevant general data
- are obtained from the aircraft exchange file and calculation specific parameter from the module configuration file.
- The user must submit the data in the following format:
- dict = {'parameter_name': [path to parameter node, expected data type], ...}
-
- :param dict routing_dict: Dictionary containing information on necessary data from module configuration file
- :returns:
- - dict data_to_extract_from_aircraft_exchange_dict: Dictionary containing parameter name, path to parameter,
- and expected data type of parameters to be extracted from aircraft exchange file
- - dict data_to_extract_from_module_configuration_dict: Dictionary containing parameter name, path to parameter,
- and expected data type of parameters to be extracted from module configuration file
- """
-
- """Aircraft exchange file."""
- # Temporary paths for shorter lines.
- tmp_design_specs_path = './requirements_and_specifications/design_specification/'
- tmp_top_level_aircraft_requirements_path = (
- './requirements_and_specifications/requirements/top_level_aircraft_requirements/')
- tmp_fuselage_entity_path = './component_design/fuselage/specific/geometry/fuselage[@ID="0"]/'
- tmp_fuselage_section_path = tmp_fuselage_entity_path + 'sections/section[@ID="0"]/'
- tmp_fuselage_accommodation_path = tmp_fuselage_entity_path + 'fuselage_accommodation/'
- tmp_fuselage_payload_deck_path = (tmp_fuselage_accommodation_path
- + 'payload_tube[@ID="0"]/payload_decks/payload_deck[@ID="0"]/')
- tmp_wing_path = './component_design/wing/specific/geometry/aerodynamic_surface[@ID="0"]/'
- tmp_wing_section_path = tmp_wing_path + 'parameters/sections/section[@ID="0"]/'
- tmp_spar_path = (
- './component_design/wing/specific/geometry/aerodynamic_surface[@ID="0"]/parameters/spars/spar[@ID="0"]/')
- tmp_empennage_path = './component_design/empennage/specific/geometry/aerodynamic_surface[@ID="0"]/'
- tmp_empennage_section_path = tmp_empennage_path + 'parameters/sections/section[@ID="0"]/'
- tmp_empennage_spar_path = (
- './component_design/empennage/specific/geometry/aerodynamic_surface[@ID="0"]/parameters/spars/spar[@ID="0"]/')
-
- # Enter all parameters to be extracted from the aircraft exchange file.
- data_to_extract_from_aircraft_exchange_dict = {
- # Data necessary for initial energy consumption estimation.
- 'number_of_passengers':
- [tmp_design_specs_path + 'transport_task/passenger_definition/total_number_passengers', float],
- 'range':
- [tmp_top_level_aircraft_requirements_path + 'design_mission/range', float],
- # Energy information.
- 'mission_energy_amount':
- ['./analysis/mission/design_mission/mission_energy[@ID="0"]/consumed_energy', float],
- 'mission_energy_ID':
- ['./analysis/mission/design_mission/mission_energy[@ID="0"]/energy_carrier_ID', int],
- 'energy_carrier_name':
- [tmp_design_specs_path + 'energy_carriers/energy_carrier[@ID="0"]/type', str],
- # Tank configuration.
- 'tank_energy_ID':
- [tmp_design_specs_path + 'configuration/tank_definition/tank[@ID="0"]/energy_carrier_ID', int],
- 'tank_location':
- [tmp_design_specs_path + 'configuration/tank_definition/tank[@ID="0"]/location', str],
- 'tank_position':
- [tmp_design_specs_path + 'configuration/tank_definition/tank[@ID="0"]/position', str],
- 'energy_share':
- [tmp_design_specs_path + 'configuration/tank_definition/tank[@ID="0"]/energy_share', float],
- # Fuselage data.
- 'fuselage_position_x': ['./component_design/fuselage/position/x', float],
- 'fuselage_position_y': ['./component_design/fuselage/position/y', float],
- 'fuselage_position_z': ['./component_design/fuselage/position/z', float],
- 'fuselage_entity_position_x': [tmp_fuselage_entity_path + 'position/x', float],
- 'fuselage_entity_position_y': [tmp_fuselage_entity_path + 'position/y', float],
- 'fuselage_entity_position_z': [tmp_fuselage_entity_path + 'position/z', float],
- 'fuselage_section_origin_x': [tmp_fuselage_section_path + 'origin/x', float],
- 'fuselage_section_origin_y': [tmp_fuselage_section_path + 'origin/y', float],
- 'fuselage_section_origin_z': [tmp_fuselage_section_path + 'origin/z', float],
- 'fuselage_section_upper_height': [tmp_fuselage_section_path + 'upper_height', float],
- 'fuselage_section_lower_height': [tmp_fuselage_section_path + 'lower_height', float],
- 'fuselage_section_width': [tmp_fuselage_section_path + 'width', float],
- 'fuselage_payload_deck_origin_x': [tmp_fuselage_payload_deck_path + 'position/x', float],
- 'fuselage_payload_deck_origin_y': [tmp_fuselage_payload_deck_path + 'position/y', float],
- 'fuselage_payload_deck_origin_z': [tmp_fuselage_payload_deck_path + 'position/z', float],
- 'fuselage_payload_deck_structural_floor_thickness': [tmp_fuselage_payload_deck_path +
- 'payload_deck_structural_floor_thickness', float],
- # Wing data.
- 'wing_name': [tmp_wing_path + 'name', str],
- 'wing_position_x': ['./component_design/wing/position/x', float],
- 'wing_position_y': ['./component_design/wing/position/y', float],
- 'wing_position_z': ['./component_design/wing/position/z', float],
- 'wing_symmetry': [tmp_wing_path + 'parameters/symmetric', bool],
- 'wing_section_chord_origin_x': [tmp_wing_section_path + 'chord_origin/x', float],
- 'wing_section_chord_origin_y': [tmp_wing_section_path + 'chord_origin/y', float],
- 'wing_section_chord_origin_z': [tmp_wing_section_path + 'chord_origin/z', float],
- 'wing_section_chord_length': [tmp_wing_section_path + 'chord_length', float],
- 'wing_section_profile': [tmp_wing_section_path + 'profile', str],
- # Wing spar data.
- 'spar_position_inner_spanwise': [tmp_spar_path + 'position/inner_position/spanwise', float],
- 'spar_position_inner_chord': [tmp_spar_path + 'position/inner_position/chord/to', float],
- 'spar_position_outer_spanwise': [tmp_spar_path + 'position/outer_position/spanwise', float],
- 'spar_position_outer_chord': [tmp_spar_path + 'position/outer_position/chord/to', float],
- # Empennage data.
- 'empennage_name': [tmp_empennage_path + 'name', str],
- 'empennage_position_x': ['./component_design/empennage/position/x', float],
- 'empennage_position_y': ['./component_design/empennage/position/y', float],
- 'empennage_position_z': ['./component_design/empennage/position/z', float],
- 'empennage_symmetry': [tmp_empennage_path + 'parameters/symmetric', bool],
- 'empennage_entity_position_x': [tmp_empennage_path + 'position/x', float],
- 'empennage_entity_position_y': [tmp_empennage_path + 'position/y', float],
- 'empennage_entity_position_z': [tmp_empennage_path + 'position/z', float],
- 'empennage_section_chord_origin_x': [tmp_empennage_section_path + 'chord_origin/x', float],
- 'empennage_section_chord_origin_y': [tmp_empennage_section_path + 'chord_origin/y', float],
- 'empennage_section_chord_origin_z': [tmp_empennage_section_path + 'chord_origin/z', float],
- 'empennage_section_chord_length': [tmp_empennage_section_path + 'chord_length', float],
- 'empennage_section_profile': [tmp_empennage_section_path + 'profile', str],
- # Empennage spar data.
- 'empennage_spar_position_inner_spanwise': [tmp_empennage_spar_path +
- 'position/inner_position/spanwise', float],
- 'empennage_spar_position_inner_chord': [tmp_empennage_spar_path + 'position/inner_position/chord/to', float],
- 'empennage_spar_position_outer_spanwise': [tmp_empennage_spar_path +
- 'position/outer_position/spanwise', float],
- 'empennage_spar_position_outer_chord': [tmp_empennage_spar_path + 'position/outer_position/chord/to', float],
- }
-
- """Module configuration file."""
- # Enter all general parameters to be extracted from the module configuration file. 'general parameters' means
- # parameters that do not differ according to the user layer. It should be noted that 'tmp_general' is only used to
- # shorten the path information in the 'general_data_to_extract_from_module_configuration_dict'.
- tmp_general = ('./program_settings/configuration[@ID="tube_and_wing"]/fidelity[@ID="empirical"]/'
- + 'tank_design_tu_berlin/general/')
- general_data_to_extract_from_module_configuration_dict = {
- 'mass_technology_factor': [tmp_general + 'mass_technology_factor', float]
- }
-
- # Enter all specific parameters to be extracted from the module configuration file. 'specific parameters' means
- # parameters that differ according to the user layer. It should be noted that 'tmp_specific' is only used to
- # shorten the path information in the 'specific_data_to_extract_from_module_configuration_dict'.
- tmp_specific = ('./program_settings/configuration[@ID="tube_and_wing"]/fidelity[@ID="empirical"]/'
- + 'tank_design_tu_berlin/specific/')
- specific_data_to_extract_from_module_configuration_dict = {
- 'kerosene_gravimetric_energy_density':
- [tmp_specific + 'kerosene_gravimetric_energy_density', float],
- 'kerosene_volumetric_energy_density':
- [tmp_specific + 'kerosene_volumetric_energy_density', float],
- 'liquid_hydrogen_gravimetric_energy_density':
- [tmp_specific + 'liquid_hydrogen_tank_structure/liquid_hydrogen_gravimetric_energy_density', float],
- 'liquid_hydrogen_volumetric_energy_density':
- [tmp_specific + 'liquid_hydrogen_tank_structure/liquid_hydrogen_volumetric_energy_density', float],
- 'material_wall':
- [tmp_specific + 'liquid_hydrogen_tank_structure/material_wall', str],
- 'density_wall':
- [tmp_specific + 'liquid_hydrogen_tank_structure/density_wall', float],
- 'thickness_wall_calculation_method':
- [tmp_specific + 'liquid_hydrogen_tank_structure/thickness_wall_calculation_method', str],
- 'mass_pumps':
- [tmp_specific + 'liquid_hydrogen_tank_structure/mass_pumps', float],
- 'mass_baffle':
- [tmp_specific + 'liquid_hydrogen_tank_structure/mass_baffle', float],
- 'type_insulation':
- [tmp_specific + 'liquid_hydrogen_tank_insulation/type_insulation', str],
- 'material_insulation':
- [tmp_specific + 'liquid_hydrogen_tank_insulation/material_insulation', str],
- 'thickness_insulation':
- [tmp_specific + 'liquid_hydrogen_tank_insulation/thickness_insulation', float],
- 'density_insulation':
- [tmp_specific + 'liquid_hydrogen_tank_insulation/density_insulation', float],
- 'type_end_cap':
- [tmp_specific + 'liquid_hydrogen_tank_design_parameter/type_end_cap', str],
- 'internal_pressure':
- [tmp_specific + 'liquid_hydrogen_tank_design_parameter/internal_pressure', float],
- 'factor_usable_diameter':
- [tmp_specific + 'miscellaneous/factor_usable_diameter', float],
- 'factor_volume_allowance':
- [tmp_specific + 'miscellaneous/factor_volume_allowance', float],
- 'a_to_d_factor':
- [tmp_specific + 'kerosene_tank_design_parameter/a_to_d_factor', float],
- 'factor_volume_usable':
- [tmp_specific + 'kerosene_tank_design_parameter/factor_volume_usable', float],
- 'temperature_expansion_allowance':
- [tmp_specific + 'kerosene_tank_design_parameter/temperature_expansion_allowance', float],
- # Obelisk calculation method name.
- 'obelisk_volume_calculation_method':
- [tmp_specific + 'kerosene_tank_design_parameter/obelisk_calculation_method', str],
- 'buffer_inner_tank_segment':
- [tmp_specific + 'kerosene_tank_design_parameter/buffer_inner_tank_segment', float],
- 'buffer_outer_tank_segment':
- [tmp_specific + 'kerosene_tank_design_parameter/buffer_outer_tank_segment', float],
- 'buffer_center_tank_segment':
- [tmp_specific + 'kerosene_tank_design_parameter/buffer_center_tank_segment', float]
- }
-
- # Merge module configuration dictionaries.
- data_to_extract_from_module_configuration_dict = (general_data_to_extract_from_module_configuration_dict
- | specific_data_to_extract_from_module_configuration_dict)
-
- return data_to_extract_from_aircraft_exchange_dict, data_to_extract_from_module_configuration_dict
-
-
-def user_method_data_output_preparation(data_dict):
- """Prepare user-specific output data based on the calculation method results.
-
- This function is responsible for preparing the user-specific output data based on the results of the calculation
- method. The 'data_dict' input parameter contains the results of the module execution.
- The data for the key parameters output must be specified in the following format in order to be written correctly
- to the aircraft exchange file by the 'write_key_data_to_aircraft_exchange_file' function in the following step:
- dict = {'parameter_name': [path to parameter node, value, name (if needed)], ...}
- Important notes:
- (1) It should be noted that only key parameters may be written that have been previously defined by the module
- manager.
- (2) Attention must be paid to the proper path specifications, otherwise warnings may be issued or, in the worst
- case, errors may occur subsequently resulting in the write process and consequently the entire program being
- aborted.
- (3) If the path specifications contain IDs, these must start at '0' and be defined in ascending order without
- gaps.
- For the method-specific output, a path list and a dictionary is necessary to properly write the data to the
- method-specific XML file.
- the dictionary must be specified in the following format:
- dict = ...
- Note: If the user wants to export data from the design and study mission, two path lists and dictionaries are
- necessary.
-
- :param dict data_dict: Dictionary containing the results of the module execution
- :returns:
- - dict key_output_dict: Output dictionary containing key parameters that are written to aircraft XML file
- - dict method_specific_output_dict: Dictionary containing specific parameters that are written to
- method-specific output XML
- """
-
- """ Convert coordinates from aircraft coordinate system to CGAL."""
- # Implement function here...
-
- """Key parameters output."""
- total_position_path = './component_design/tank/position/'
- total_mass_path = './component_design/tank/mass_properties/'
- total_inertia_path = './component_design/tank/mass_properties/inertia/'
- total_cog_path = './component_design/tank/mass_properties/center_of_gravity/'
- # data_dict['total_tank_parameters']['position'] = \
- # coordinate_system_conversion(data_dict['total_tank_parameters']['position'])
-
- key_output_dict = {
- # Total tank parameter.
- 'x':
- [total_position_path + 'x',
- data_dict['total_tank_parameters']['position']['x']],
- 'y':
- [total_position_path + 'y',
- data_dict['total_tank_parameters']['position']['y']],
- 'z':
- [total_position_path + 'z',
- data_dict['total_tank_parameters']['position']['z']],
- 'mass':
- [total_mass_path + 'mass',
- data_dict['total_tank_parameters']['mass']],
- 'j_xx':
- [total_inertia_path + 'j_xx',
- data_dict['total_tank_parameters']['inertia']['j_xx']],
- 'j_yy':
- [total_inertia_path + 'j_yy',
- data_dict['total_tank_parameters']['inertia']['j_yy']],
- 'j_zz':
- [total_inertia_path + 'j_zz',
- data_dict['total_tank_parameters']['inertia']['j_zz']],
- 'j_xy':
- [total_inertia_path + 'j_xy',
- data_dict['total_tank_parameters']['inertia']['j_xy']],
- 'j_xz':
- [total_inertia_path + 'j_xz',
- data_dict['total_tank_parameters']['inertia']['j_xz']],
- 'j_yx':
- [total_inertia_path + 'j_yx',
- data_dict['total_tank_parameters']['inertia']['j_yx']],
- 'j_yz':
- [total_inertia_path + 'j_yz',
- data_dict['total_tank_parameters']['inertia']['j_yz']],
- 'j_zx':
- [total_inertia_path + 'j_zx',
- data_dict['total_tank_parameters']['inertia']['j_zx']],
- 'j_zy':
- [total_inertia_path + 'j_zy',
- data_dict['total_tank_parameters']['inertia']['j_zy']],
- 'cog_x':
- [total_cog_path + 'x',
- data_dict['total_tank_parameters']['center_of_gravity']['x']],
- 'cog_y':
- [total_cog_path + 'y',
- data_dict['total_tank_parameters']['center_of_gravity']['y']],
- 'cog_z':
- [total_cog_path + 'z',
- data_dict['total_tank_parameters']['center_of_gravity']['z']]
- }
-
- # Generate dictionary for each tank entity.
- j = 0
- while j < data_dict['number_of_tanks']:
- tank_path_id = './component_design/tank/specific/tank[@ID="' + str(j) + '"]/'
- tank_id = 'tank_' + str(j)
- data_dict[tank_id]['geometry']['total']['position'] = \
- coordinate_system_conversion(data_dict[tank_id]['geometry']['total']['position'])
- tank_output_dict = {
- 'name_id' + str(j):
- [tank_path_id + 'name',
- 'tank_' + str(j)],
- 'designator_id' + str(j):
- [tank_path_id + 'designator',
- data_dict[tank_id]['tank_location'] + '_' + data_dict[tank_id]['tank_position']],
- 'x_id' + str(j):
- [tank_path_id + 'position/x',
- round(data_dict[tank_id]['geometry']['total']['position']['x'], 9)],
- 'y_id' + str(j):
- [tank_path_id + 'position/y',
- round(data_dict[tank_id]['geometry']['total']['position']['y'], 9)],
- 'z_id' + str(j):
- [tank_path_id + 'position/z',
- round(data_dict[tank_id]['geometry']['total']['position']['z'], 9)],
- 'direction_x_id' + str(j):
- [tank_path_id + 'direction/x',
- data_dict[tank_id]['geometry']['total']['direction']['x']],
- 'direction_y_id' + str(j):
- [tank_path_id + 'direction/y',
- data_dict[tank_id]['geometry']['total']['direction']['y']],
- 'direction_z_id' + str(j):
- [tank_path_id + 'direction/z',
- data_dict[tank_id]['geometry']['total']['direction']['z']],
- 'mass_id' + str(j):
- [tank_path_id + 'mass_properties/mass',
- data_dict[tank_id]['geometry']['total']['mass']],
- 'j_xx_id' + str(j):
- [tank_path_id + 'mass_properties/inertia/j_xx',
- data_dict[tank_id]['geometry']['total']['inertia']['j_xx']],
- 'j_yy_id' + str(j):
- [tank_path_id + 'mass_properties/inertia/j_yy',
- data_dict[tank_id]['geometry']['total']['inertia']['j_yy']],
- 'j_zz_id' + str(j):
- [tank_path_id + 'mass_properties/inertia/j_zz',
- data_dict[tank_id]['geometry']['total']['inertia']['j_zz']],
- 'j_xy_id' + str(j):
- [tank_path_id + 'mass_properties/inertia/j_xy',
- data_dict[tank_id]['geometry']['total']['inertia']['j_xy']],
- 'j_xz_id' + str(j):
- [tank_path_id + 'mass_properties/inertia/j_xz',
- data_dict[tank_id]['geometry']['total']['inertia']['j_xz']],
- 'j_yx_id' + str(j):
- [tank_path_id + 'mass_properties/inertia/j_yx',
- data_dict[tank_id]['geometry']['total']['inertia']['j_yx']],
- 'j_yz_id' + str(j):
- [tank_path_id + 'mass_properties/inertia/j_yz',
- data_dict[tank_id]['geometry']['total']['inertia']['j_yz']],
- 'j_zx_id' + str(j):
- [tank_path_id + 'mass_properties/inertia/j_zx',
- data_dict[tank_id]['geometry']['total']['inertia']['j_zx']],
- 'j_zy_id' + str(j):
- [tank_path_id + 'mass_properties/inertia/j_zy',
- data_dict[tank_id]['geometry']['total']['inertia']['j_zy']],
- 'cog_x_id' + str(j):
- [tank_path_id + 'mass_properties/center_of_gravity/x',
- data_dict[tank_id]['geometry']['total']['center_of_gravity']['x']],
- 'cog_y_id' + str(j):
- [tank_path_id + 'mass_properties/center_of_gravity/y',
- data_dict[tank_id]['geometry']['total']['center_of_gravity']['y']],
- 'cog_z_id' + str(j):
- [tank_path_id + 'mass_properties/center_of_gravity/z',
- data_dict[tank_id]['geometry']['total']['center_of_gravity']['z']],
- 'energy_id' + str(j):
- [tank_path_id + 'maximum_energy_capacity',
- data_dict[tank_id]['energy_available']],
- 'centroid_x_id' + str(j):
- [tank_path_id + 'mass_properties/centroid/x',
- round(data_dict[tank_id]['geometry']['total']['centroid']['x'], 9)],
- 'centroid_y_id' + str(j):
- [tank_path_id + 'mass_properties/centroid/y',
- round(data_dict[tank_id]['geometry']['total']['centroid']['y'], 9)],
- 'centroid_z_id' + str(j):
- [tank_path_id + 'mass_properties/centroid/z',
- round(data_dict[tank_id]['geometry']['total']['centroid']['z'], 9)],
- }
-
- # Iterate over tank sections of each tank entity.
- i = 0
- if data_dict[tank_id]['energy_carrier_name'] == 'kerosene':
- number_of_sections = 2
- section_names = ['inner_surface', 'outer_surface']
- if data_dict[tank_id]['tank_location'] == 'fuselage' and data_dict[tank_id]['tank_position'] == 'center':
- number_of_sections = sum(1 for k in data_dict[tank_id]['geometry'].keys()
- if k.startswith('cross_section_'))
- section_names = [k for k in data_dict[tank_id]['geometry'].keys() if k.startswith('cross_section_')]
- section_names = sorted(section_names, key=lambda x: int(x.split('_')[-1]))
- if data_dict[tank_id]['tank_location'] == 'horizontal_stabilizer' and (
- data_dict[tank_id]['tank_position'] == 'total'):
- number_of_sections = sum(1 for k in data_dict[tank_id]['geometry'].keys()
- if k.startswith('cross_section_'))
- section_names = [k for k in data_dict[tank_id]['geometry'].keys() if k.startswith('cross_section_')]
- section_names = sorted(section_names, key=lambda x: int(x.split('_')[-1]))
- else:
- number_of_sections = sum(1 for k in data_dict[tank_id]['geometry'].keys()
- if k.startswith('cross_section_'))
- section_names = [k for k in data_dict[tank_id]['geometry'].keys() if k.startswith('cross_section_')]
- section_names = sorted(section_names, key=lambda x: int(x.split('_')[-1]))
- while i < number_of_sections:
- tank_section_path = tank_path_id + 'geometry/cross_section[@ID="' + str(i) + '"]/'
- tank_section_name = 'tank_section_' + str(i)
- # data_dict[tank_id]['geometry'][section_names[i]]['position'] = \
- # coordinate_system_conversion(data_dict[tank_id]['geometry'][section_names[i]]['position'])
- # Check if the energy carrier of current tank is kerosene
- # -> if true: -> use coordinate transformation for wing tanks.
- if data_dict['tank_' + str(j)]['energy_carrier_name'] == 'kerosene':
- tank_section_output_dict = {
- 'cross_section_name_id' + str(j) + '_id' + str(i):
- [tank_section_path + 'name',
- tank_section_name],
- 'cross_section_x_id' + str(j) + '_id' + str(i):
- [tank_section_path + 'position/x',
- round(data_dict[tank_id]['geometry'][section_names[i]]['position']['x'], 9)],
- 'cross_section_y_id' + str(j) + '_id' + str(i):
- [tank_section_path + 'position/y',
- round(data_dict[tank_id]['geometry'][section_names[i]]['position']['z'], 9)],
- 'cross_section_z_id' + str(j) + '_id' + str(i):
- [tank_section_path + 'position/z',
- round(data_dict[tank_id]['geometry'][section_names[i]]['position']['y'] * -1, 9)],
- 'shape_id' + str(j) + '_id' + str(i):
- [tank_section_path + 'shape',
- data_dict[tank_id]['geometry'][section_names[i]]['shape']],
- 'height_id' + str(j) + '_id' + str(i):
- [tank_section_path + 'height',
- data_dict[tank_id]['geometry'][section_names[i]]['height']],
- 'width_id' + str(j) + '_id' + str(i):
- [tank_section_path + 'width',
- data_dict[tank_id]['geometry'][section_names[i]]['width']],
- 'length_id' + str(j) + '_id' + str(i):
- [tank_section_path + 'length',
- data_dict[tank_id]['geometry'][section_names[i]]['length']]
- }
- # Else condition: The energy carrier of current tank is not kerosene
- # -> use coordinate transformation for fuselage tanks.
- else:
- tank_section_output_dict = {
- 'cross_section_name_id' + str(j) + '_id' + str(i):
- [tank_section_path + 'name',
- tank_section_name],
- 'cross_section_x_id' + str(j) + '_id' + str(i):
- [tank_section_path + 'position/x',
- round(data_dict[tank_id]['geometry'][section_names[i]]['position']['y'] * -1, 9)],
- 'cross_section_y_id' + str(j) + '_id' + str(i):
- [tank_section_path + 'position/y',
- round(data_dict[tank_id]['geometry'][section_names[i]]['position']['z'], 9)],
- 'cross_section_z_id' + str(j) + '_id' + str(i):
- [tank_section_path + 'position/z',
- round(data_dict[tank_id]['geometry'][section_names[i]]['position']['x'], 9)],
- 'shape_id' + str(j) + '_id' + str(i):
- [tank_section_path + 'shape',
- data_dict[tank_id]['geometry'][section_names[i]]['shape']],
- 'height_id' + str(j) + '_id' + str(i):
- [tank_section_path + 'height',
- data_dict[tank_id]['geometry'][section_names[i]]['height']],
- 'width_id' + str(j) + '_id' + str(i):
- [tank_section_path + 'width',
- data_dict[tank_id]['geometry'][section_names[i]]['width']],
- 'length_id' + str(j) + '_id' + str(i):
- [tank_section_path + 'length',
- data_dict[tank_id]['geometry'][section_names[i]]['length']]
- }
- # merge dictionary to one single output dictionary
- tank_output_dict.update(tank_section_output_dict)
- i += 1
-
- key_output_dict.update(tank_output_dict)
- j += 1
-
- # Add additional fuselage length.
- additional_length_dict = {
- 'additional_fuselage_length': ['./component_design/tank/specific/additional_fuselage_length',
- data_dict['total_tank_parameters']['additional_fuselage_length']]
- }
-
- key_output_dict.update(additional_length_dict)
-
- """Method-specific output."""
- method_specific_output_dict = {}
- for key, value in key_output_dict.items():
- if 'mass_properties' not in value[0]:
- method_specific_output_dict[key] = value
-
- return key_output_dict, method_specific_output_dict
-
-
-def coordinate_system_conversion(element):
- if len(element.keys()) > 3:
- element_3d = py11csc.Element3D(element["j_xx"], element["j_xy"], element["j_xz"],
- element["j_yx"], element["j_yy"], element["j_yz"],
- element["j_zx"], element["j_zy"], element["j_zz"])
- element_3d.AC2CGAL()
- for k in element.keys():
- element[k] = getattr(element_3d, k.split("_")[-1])()
- return element
- else:
- element_3d = py11csc.Element3D(element["x"], element["y"], element["z"])
- element_3d.AC2CGAL()
- for k in element.keys():
- element[k] = getattr(element_3d, k)()
- return element
+"""Module providing functions for the preparation of user data."""
+import pycoordinatesystemconversion as py11csc
+
+
+def user_method_data_input_preparation(routing_dict):
+ """Prepare necessary input data for the user method from aircraft exchange and module configuration files.
+
+ In this function, the user is responsible for preparing the data needed for the user method. Relevant general data
+ are obtained from the aircraft exchange file and calculation specific parameter from the module configuration file.
+ The user must submit the data in the following format:
+ dict = {'parameter_name': [path to parameter node, expected data type], ...}
+
+ :param dict routing_dict: Dictionary containing information on necessary data from module configuration file
+ :returns:
+ - dict data_to_extract_from_aircraft_exchange_dict: Dictionary containing parameter name, path to parameter,
+ and expected data type of parameters to be extracted from aircraft exchange file
+ - dict data_to_extract_from_module_configuration_dict: Dictionary containing parameter name, path to parameter,
+ and expected data type of parameters to be extracted from module configuration file
+ """
+
+ """Aircraft exchange file."""
+ # Temporary paths for shorter lines.
+ tmp_design_specs_path = './requirements_and_specifications/design_specification/'
+ tmp_top_level_aircraft_requirements_path = (
+ './requirements_and_specifications/requirements/top_level_aircraft_requirements/')
+ tmp_fuselage_entity_path = './component_design/fuselage/specific/geometry/fuselage[@ID="0"]/'
+ tmp_fuselage_section_path = tmp_fuselage_entity_path + 'sections/section[@ID="0"]/'
+ tmp_fuselage_accommodation_path = tmp_fuselage_entity_path + 'fuselage_accommodation/'
+ tmp_fuselage_payload_deck_path = (tmp_fuselage_accommodation_path
+ + 'payload_tube[@ID="0"]/payload_decks/payload_deck[@ID="0"]/')
+ tmp_wing_path = './component_design/wing/specific/geometry/aerodynamic_surface[@ID="0"]/'
+ tmp_wing_section_path = tmp_wing_path + 'parameters/sections/section[@ID="0"]/'
+ tmp_spar_path = (
+ './component_design/wing/specific/geometry/aerodynamic_surface[@ID="0"]/parameters/spars/spar[@ID="0"]/')
+ tmp_empennage_path = './component_design/empennage/specific/geometry/aerodynamic_surface[@ID="0"]/'
+ tmp_empennage_section_path = tmp_empennage_path + 'parameters/sections/section[@ID="0"]/'
+ tmp_empennage_spar_path = (
+ './component_design/empennage/specific/geometry/aerodynamic_surface[@ID="0"]/parameters/spars/spar[@ID="0"]/')
+ tmp_mission_analysis_path = './analysis/mission/design_mission/'
+
+ # Enter all parameters to be extracted from the aircraft exchange file.
+ data_to_extract_from_aircraft_exchange_dict = {
+ # Data necessary for initial energy consumption estimation.
+ 'number_of_passengers':
+ [tmp_design_specs_path + 'transport_task/passenger_definition/total_number_passengers', float],
+ 'range':
+ [tmp_top_level_aircraft_requirements_path + 'design_mission/range', float],
+ # Energy information.
+ 'mission_energy_amount':
+ [tmp_mission_analysis_path +'loaded_mission_energy/mission_energy[@ID="0"]/consumed_energy', float],
+ 'mission_energy_ID':
+ [tmp_mission_analysis_path +'loaded_mission_energy/mission_energy[@ID="0"]/energy_carrier_ID', int],
+ # TODO here only loaded mission energy is used, but there are also trip, taxi & landing energy
+ 'energy_carrier_name':
+ [tmp_design_specs_path + 'energy_carriers/energy_carrier[@ID="0"]/type', str],
+ # Tank configuration.
+ 'tank_energy_ID':
+ [tmp_design_specs_path + 'configuration/tank_definition/tank[@ID="0"]/energy_carrier_ID', int],
+ 'tank_location':
+ [tmp_design_specs_path + 'configuration/tank_definition/tank[@ID="0"]/location', str],
+ 'tank_position':
+ [tmp_design_specs_path + 'configuration/tank_definition/tank[@ID="0"]/position', str],
+ 'energy_share':
+ [tmp_design_specs_path + 'configuration/tank_definition/tank[@ID="0"]/energy_share', float],
+ # Fuselage data.
+ 'fuselage_position_x': ['./component_design/fuselage/position/x', float],
+ 'fuselage_position_y': ['./component_design/fuselage/position/y', float],
+ 'fuselage_position_z': ['./component_design/fuselage/position/z', float],
+ 'fuselage_entity_position_x': [tmp_fuselage_entity_path + 'position/x', float],
+ 'fuselage_entity_position_y': [tmp_fuselage_entity_path + 'position/y', float],
+ 'fuselage_entity_position_z': [tmp_fuselage_entity_path + 'position/z', float],
+ 'fuselage_section_origin_x': [tmp_fuselage_section_path + 'origin/x', float],
+ 'fuselage_section_origin_y': [tmp_fuselage_section_path + 'origin/y', float],
+ 'fuselage_section_origin_z': [tmp_fuselage_section_path + 'origin/z', float],
+ 'fuselage_section_upper_height': [tmp_fuselage_section_path + 'upper_height', float],
+ 'fuselage_section_lower_height': [tmp_fuselage_section_path + 'lower_height', float],
+ 'fuselage_section_width': [tmp_fuselage_section_path + 'width', float],
+ 'fuselage_payload_deck_origin_x': [tmp_fuselage_payload_deck_path + 'position/x', float],
+ 'fuselage_payload_deck_origin_y': [tmp_fuselage_payload_deck_path + 'position/y', float],
+ 'fuselage_payload_deck_origin_z': [tmp_fuselage_payload_deck_path + 'position/z', float],
+ 'fuselage_payload_deck_structural_floor_thickness': [tmp_fuselage_payload_deck_path +
+ 'payload_deck_structural_floor_thickness', float],
+ # Wing data.
+ 'wing_name': [tmp_wing_path + 'name', str],
+ 'wing_position_x': ['./component_design/wing/position/x', float],
+ 'wing_position_y': ['./component_design/wing/position/y', float],
+ 'wing_position_z': ['./component_design/wing/position/z', float],
+ 'wing_symmetry': [tmp_wing_path + 'parameters/symmetric', bool],
+ 'wing_section_chord_origin_x': [tmp_wing_section_path + 'chord_origin/x', float],
+ 'wing_section_chord_origin_y': [tmp_wing_section_path + 'chord_origin/y', float],
+ 'wing_section_chord_origin_z': [tmp_wing_section_path + 'chord_origin/z', float],
+ 'wing_section_chord_length': [tmp_wing_section_path + 'chord_length', float],
+ 'wing_section_profile': [tmp_wing_section_path + 'profile', str],
+ # Wing spar data.
+ 'spar_position_inner_spanwise': [tmp_spar_path + 'position/inner_position/spanwise', float],
+ 'spar_position_inner_chord': [tmp_spar_path + 'position/inner_position/chord/to', float],
+ 'spar_position_outer_spanwise': [tmp_spar_path + 'position/outer_position/spanwise', float],
+ 'spar_position_outer_chord': [tmp_spar_path + 'position/outer_position/chord/to', float],
+ # Empennage data.
+ 'empennage_name': [tmp_empennage_path + 'name', str],
+ 'empennage_position_x': ['./component_design/empennage/position/x', float],
+ 'empennage_position_y': ['./component_design/empennage/position/y', float],
+ 'empennage_position_z': ['./component_design/empennage/position/z', float],
+ 'empennage_symmetry': [tmp_empennage_path + 'parameters/symmetric', bool],
+ 'empennage_entity_position_x': [tmp_empennage_path + 'position/x', float],
+ 'empennage_entity_position_y': [tmp_empennage_path + 'position/y', float],
+ 'empennage_entity_position_z': [tmp_empennage_path + 'position/z', float],
+ 'empennage_section_chord_origin_x': [tmp_empennage_section_path + 'chord_origin/x', float],
+ 'empennage_section_chord_origin_y': [tmp_empennage_section_path + 'chord_origin/y', float],
+ 'empennage_section_chord_origin_z': [tmp_empennage_section_path + 'chord_origin/z', float],
+ 'empennage_section_chord_length': [tmp_empennage_section_path + 'chord_length', float],
+ 'empennage_section_profile': [tmp_empennage_section_path + 'profile', str],
+ # Empennage spar data.
+ 'empennage_spar_position_inner_spanwise': [tmp_empennage_spar_path +
+ 'position/inner_position/spanwise', float],
+ 'empennage_spar_position_inner_chord': [tmp_empennage_spar_path + 'position/inner_position/chord/to', float],
+ 'empennage_spar_position_outer_spanwise': [tmp_empennage_spar_path +
+ 'position/outer_position/spanwise', float],
+ 'empennage_spar_position_outer_chord': [tmp_empennage_spar_path + 'position/outer_position/chord/to', float],
+ }
+
+ """Module configuration file."""
+ # Enter all general parameters to be extracted from the module configuration file. 'general parameters' means
+ # parameters that do not differ according to the user layer. It should be noted that 'tmp_general' is only used to
+ # shorten the path information in the 'general_data_to_extract_from_module_configuration_dict'.
+ tmp_general = ('./program_settings/configuration[@ID="tube_and_wing"]/fidelity[@ID="empirical"]/'
+ + 'tank_design_tu_berlin/general/')
+ general_data_to_extract_from_module_configuration_dict = {
+ 'mass_technology_factor': [tmp_general + 'mass_technology_factor', float]
+ }
+
+ # Enter all specific parameters to be extracted from the module configuration file. 'specific parameters' means
+ # parameters that differ according to the user layer. It should be noted that 'tmp_specific' is only used to
+ # shorten the path information in the 'specific_data_to_extract_from_module_configuration_dict'.
+ tmp_specific = ('./program_settings/configuration[@ID="tube_and_wing"]/fidelity[@ID="empirical"]/'
+ + 'tank_design_tu_berlin/specific/')
+ specific_data_to_extract_from_module_configuration_dict = {
+ 'kerosene_gravimetric_energy_density':
+ [tmp_specific + 'kerosene_gravimetric_energy_density', float],
+ 'kerosene_volumetric_energy_density':
+ [tmp_specific + 'kerosene_volumetric_energy_density', float],
+ 'liquid_hydrogen_gravimetric_energy_density':
+ [tmp_specific + 'liquid_hydrogen_tank_structure/liquid_hydrogen_gravimetric_energy_density', float],
+ 'liquid_hydrogen_volumetric_energy_density':
+ [tmp_specific + 'liquid_hydrogen_tank_structure/liquid_hydrogen_volumetric_energy_density', float],
+ 'material_wall':
+ [tmp_specific + 'liquid_hydrogen_tank_structure/material_wall', str],
+ 'density_wall':
+ [tmp_specific + 'liquid_hydrogen_tank_structure/density_wall', float],
+ 'thickness_wall_calculation_method':
+ [tmp_specific + 'liquid_hydrogen_tank_structure/thickness_wall_calculation_method', str],
+ 'mass_pumps':
+ [tmp_specific + 'liquid_hydrogen_tank_structure/mass_pumps', float],
+ 'mass_baffle':
+ [tmp_specific + 'liquid_hydrogen_tank_structure/mass_baffle', float],
+ 'type_insulation':
+ [tmp_specific + 'liquid_hydrogen_tank_insulation/type_insulation', str],
+ 'material_insulation':
+ [tmp_specific + 'liquid_hydrogen_tank_insulation/material_insulation', str],
+ 'thickness_insulation':
+ [tmp_specific + 'liquid_hydrogen_tank_insulation/thickness_insulation', float],
+ 'density_insulation':
+ [tmp_specific + 'liquid_hydrogen_tank_insulation/density_insulation', float],
+ 'type_end_cap':
+ [tmp_specific + 'liquid_hydrogen_tank_design_parameter/type_end_cap', str],
+ 'internal_pressure':
+ [tmp_specific + 'liquid_hydrogen_tank_design_parameter/internal_pressure', float],
+ 'factor_usable_diameter':
+ [tmp_specific + 'miscellaneous/factor_usable_diameter', float],
+ 'factor_volume_allowance':
+ [tmp_specific + 'miscellaneous/factor_volume_allowance', float],
+ 'a_to_d_factor':
+ [tmp_specific + 'kerosene_tank_design_parameter/a_to_d_factor', float],
+ 'factor_volume_usable':
+ [tmp_specific + 'kerosene_tank_design_parameter/factor_volume_usable', float],
+ 'temperature_expansion_allowance':
+ [tmp_specific + 'kerosene_tank_design_parameter/temperature_expansion_allowance', float],
+ # Obelisk calculation method name.
+ 'obelisk_volume_calculation_method':
+ [tmp_specific + 'kerosene_tank_design_parameter/obelisk_calculation_method', str],
+ 'buffer_inner_tank_segment':
+ [tmp_specific + 'kerosene_tank_design_parameter/buffer_inner_tank_segment', float],
+ 'buffer_outer_tank_segment':
+ [tmp_specific + 'kerosene_tank_design_parameter/buffer_outer_tank_segment', float],
+ 'buffer_center_tank_segment':
+ [tmp_specific + 'kerosene_tank_design_parameter/buffer_center_tank_segment', float]
+ }
+
+ # Merge module configuration dictionaries.
+ data_to_extract_from_module_configuration_dict = (general_data_to_extract_from_module_configuration_dict
+ | specific_data_to_extract_from_module_configuration_dict)
+
+ return data_to_extract_from_aircraft_exchange_dict, data_to_extract_from_module_configuration_dict
+
+
+def user_method_data_output_preparation(data_dict):
+ """Prepare user-specific output data based on the calculation method results.
+
+ This function is responsible for preparing the user-specific output data based on the results of the calculation
+ method. The 'data_dict' input parameter contains the results of the module execution.
+ The data for the key parameters output must be specified in the following format in order to be written correctly
+ to the aircraft exchange file by the 'write_key_data_to_aircraft_exchange_file' function in the following step:
+ dict = {'parameter_name': [path to parameter node, value, name (if needed)], ...}
+ Important notes:
+ (1) It should be noted that only key parameters may be written that have been previously defined by the module
+ manager.
+ (2) Attention must be paid to the proper path specifications, otherwise warnings may be issued or, in the worst
+ case, errors may occur subsequently resulting in the write process and consequently the entire program being
+ aborted.
+ (3) If the path specifications contain IDs, these must start at '0' and be defined in ascending order without
+ gaps.
+ For the method-specific output, a path list and a dictionary is necessary to properly write the data to the
+ method-specific XML file.
+ the dictionary must be specified in the following format:
+ dict = ...
+ Note: If the user wants to export data from the design and study mission, two path lists and dictionaries are
+ necessary.
+
+ :param dict data_dict: Dictionary containing the results of the module execution
+ :returns:
+ - dict key_output_dict: Output dictionary containing key parameters that are written to aircraft XML file
+ - dict method_specific_output_dict: Dictionary containing specific parameters that are written to
+ method-specific output XML
+ """
+
+ """ Convert coordinates from aircraft coordinate system to CGAL."""
+ # Implement function here...
+
+ """Key parameters output."""
+ total_position_path = './component_design/tank/position/'
+ total_mass_path = './component_design/tank/mass_properties/'
+ total_inertia_path = './component_design/tank/mass_properties/inertia/'
+ total_cog_path = './component_design/tank/mass_properties/center_of_gravity/'
+ # data_dict['total_tank_parameters']['position'] = \
+ # coordinate_system_conversion(data_dict['total_tank_parameters']['position'])
+
+ key_output_dict = {
+ # Total tank parameter.
+ 'x':
+ [total_position_path + 'x',
+ data_dict['total_tank_parameters']['position']['x']],
+ 'y':
+ [total_position_path + 'y',
+ data_dict['total_tank_parameters']['position']['y']],
+ 'z':
+ [total_position_path + 'z',
+ data_dict['total_tank_parameters']['position']['z']],
+ 'mass':
+ [total_mass_path + 'mass',
+ data_dict['total_tank_parameters']['mass']],
+ 'j_xx':
+ [total_inertia_path + 'j_xx',
+ data_dict['total_tank_parameters']['inertia']['j_xx']],
+ 'j_yy':
+ [total_inertia_path + 'j_yy',
+ data_dict['total_tank_parameters']['inertia']['j_yy']],
+ 'j_zz':
+ [total_inertia_path + 'j_zz',
+ data_dict['total_tank_parameters']['inertia']['j_zz']],
+ 'j_xy':
+ [total_inertia_path + 'j_xy',
+ data_dict['total_tank_parameters']['inertia']['j_xy']],
+ 'j_xz':
+ [total_inertia_path + 'j_xz',
+ data_dict['total_tank_parameters']['inertia']['j_xz']],
+ 'j_yx':
+ [total_inertia_path + 'j_yx',
+ data_dict['total_tank_parameters']['inertia']['j_yx']],
+ 'j_yz':
+ [total_inertia_path + 'j_yz',
+ data_dict['total_tank_parameters']['inertia']['j_yz']],
+ 'j_zx':
+ [total_inertia_path + 'j_zx',
+ data_dict['total_tank_parameters']['inertia']['j_zx']],
+ 'j_zy':
+ [total_inertia_path + 'j_zy',
+ data_dict['total_tank_parameters']['inertia']['j_zy']],
+ 'cog_x':
+ [total_cog_path + 'x',
+ data_dict['total_tank_parameters']['center_of_gravity']['x']],
+ 'cog_y':
+ [total_cog_path + 'y',
+ data_dict['total_tank_parameters']['center_of_gravity']['y']],
+ 'cog_z':
+ [total_cog_path + 'z',
+ data_dict['total_tank_parameters']['center_of_gravity']['z']]
+ }
+
+ # Generate dictionary for each tank entity.
+ j = 0
+ while j < data_dict['number_of_tanks']:
+ tank_path_id = './component_design/tank/specific/tank[@ID="' + str(j) + '"]/'
+ tank_id = 'tank_' + str(j)
+ # data_dict[tank_id]['geometry']['total']['position'] = \
+ # coordinate_system_conversion(data_dict[tank_id]['geometry']['total']['position'])
+ tank_output_dict = {
+ 'name_id' + str(j):
+ [tank_path_id + 'name',
+ 'tank_' + str(j)],
+ 'designator_id' + str(j):
+ [tank_path_id + 'designator',
+ data_dict[tank_id]['tank_location'] + '_' + data_dict[tank_id]['tank_position']],
+ 'x_id' + str(j):
+ [tank_path_id + 'position/x',
+ round(data_dict[tank_id]['geometry']['total']['position']['x'], 9)],
+ 'y_id' + str(j):
+ [tank_path_id + 'position/y',
+ round(data_dict[tank_id]['geometry']['total']['position']['y'], 9)],
+ 'z_id' + str(j):
+ [tank_path_id + 'position/z',
+ round(data_dict[tank_id]['geometry']['total']['position']['z'], 9)],
+ 'direction_x_id' + str(j):
+ [tank_path_id + 'direction/x',
+ data_dict[tank_id]['geometry']['total']['direction']['x']],
+ 'direction_y_id' + str(j):
+ [tank_path_id + 'direction/y',
+ data_dict[tank_id]['geometry']['total']['direction']['y']],
+ 'direction_z_id' + str(j):
+ [tank_path_id + 'direction/z',
+ data_dict[tank_id]['geometry']['total']['direction']['z']],
+ 'mass_id' + str(j):
+ [tank_path_id + 'mass_properties/mass',
+ data_dict[tank_id]['geometry']['total']['mass']],
+ 'j_xx_id' + str(j):
+ [tank_path_id + 'mass_properties/inertia/j_xx',
+ data_dict[tank_id]['geometry']['total']['inertia']['j_xx']],
+ 'j_yy_id' + str(j):
+ [tank_path_id + 'mass_properties/inertia/j_yy',
+ data_dict[tank_id]['geometry']['total']['inertia']['j_yy']],
+ 'j_zz_id' + str(j):
+ [tank_path_id + 'mass_properties/inertia/j_zz',
+ data_dict[tank_id]['geometry']['total']['inertia']['j_zz']],
+ 'j_xy_id' + str(j):
+ [tank_path_id + 'mass_properties/inertia/j_xy',
+ data_dict[tank_id]['geometry']['total']['inertia']['j_xy']],
+ 'j_xz_id' + str(j):
+ [tank_path_id + 'mass_properties/inertia/j_xz',
+ data_dict[tank_id]['geometry']['total']['inertia']['j_xz']],
+ 'j_yx_id' + str(j):
+ [tank_path_id + 'mass_properties/inertia/j_yx',
+ data_dict[tank_id]['geometry']['total']['inertia']['j_yx']],
+ 'j_yz_id' + str(j):
+ [tank_path_id + 'mass_properties/inertia/j_yz',
+ data_dict[tank_id]['geometry']['total']['inertia']['j_yz']],
+ 'j_zx_id' + str(j):
+ [tank_path_id + 'mass_properties/inertia/j_zx',
+ data_dict[tank_id]['geometry']['total']['inertia']['j_zx']],
+ 'j_zy_id' + str(j):
+ [tank_path_id + 'mass_properties/inertia/j_zy',
+ data_dict[tank_id]['geometry']['total']['inertia']['j_zy']],
+ 'cog_x_id' + str(j):
+ [tank_path_id + 'mass_properties/center_of_gravity/x',
+ data_dict[tank_id]['geometry']['total']['center_of_gravity']['x']],
+ 'cog_y_id' + str(j):
+ [tank_path_id + 'mass_properties/center_of_gravity/y',
+ data_dict[tank_id]['geometry']['total']['center_of_gravity']['y']],
+ 'cog_z_id' + str(j):
+ [tank_path_id + 'mass_properties/center_of_gravity/z',
+ data_dict[tank_id]['geometry']['total']['center_of_gravity']['z']],
+ 'energy_id' + str(j):
+ [tank_path_id + 'maximum_energy_capacity',
+ data_dict[tank_id]['energy_available']],
+ 'required_energy_id' + str(j):
+ [tank_path_id + 'energy_capacity_required_for_mission',
+ data_dict[tank_id]['energy_required_for_mission']],
+ 'centroid_x_id' + str(j):
+ [tank_path_id + 'mass_properties/centroid/x',
+ round(data_dict[tank_id]['geometry']['total']['centroid']['x'], 9)],
+ 'centroid_y_id' + str(j):
+ [tank_path_id + 'mass_properties/centroid/y',
+ round(data_dict[tank_id]['geometry']['total']['centroid']['y'], 9)],
+ 'centroid_z_id' + str(j):
+ [tank_path_id + 'mass_properties/centroid/z',
+ round(data_dict[tank_id]['geometry']['total']['centroid']['z'], 9)],
+ }
+
+ # Iterate over tank sections of each tank entity.
+ i = 0
+ if data_dict[tank_id]['energy_carrier_name'] == 'kerosene':
+ number_of_sections = 2
+ section_names = ['inner_surface', 'outer_surface']
+ if data_dict[tank_id]['tank_location'] == 'fuselage' and data_dict[tank_id]['tank_position'] == 'center':
+ number_of_sections = sum(1 for k in data_dict[tank_id]['geometry'].keys()
+ if k.startswith('cross_section_'))
+ section_names = [k for k in data_dict[tank_id]['geometry'].keys() if k.startswith('cross_section_')]
+ section_names = sorted(section_names, key=lambda x: int(x.split('_')[-1]))
+ if data_dict[tank_id]['tank_location'] == 'horizontal_stabilizer' and (
+ data_dict[tank_id]['tank_position'] == 'total'):
+ number_of_sections = sum(1 for k in data_dict[tank_id]['geometry'].keys()
+ if k.startswith('cross_section_'))
+ section_names = [k for k in data_dict[tank_id]['geometry'].keys() if k.startswith('cross_section_')]
+ section_names = sorted(section_names, key=lambda x: int(x.split('_')[-1]))
+ else:
+ number_of_sections = sum(1 for k in data_dict[tank_id]['geometry'].keys()
+ if k.startswith('cross_section_'))
+ section_names = [k for k in data_dict[tank_id]['geometry'].keys() if k.startswith('cross_section_')]
+ section_names = sorted(section_names, key=lambda x: int(x.split('_')[-1]))
+ while i < number_of_sections:
+ tank_section_path = tank_path_id + 'geometry/cross_section[@ID="' + str(i) + '"]/'
+ tank_section_name = 'tank_section_' + str(i)
+ # data_dict[tank_id]['geometry'][section_names[i]]['position'] = \
+ # coordinate_system_conversion(data_dict[tank_id]['geometry'][section_names[i]]['position'])
+ # Check if the energy carrier of current tank is kerosene
+ # -> if true: -> use coordinate transformation for wing tanks.
+ if data_dict['tank_' + str(j)]['energy_carrier_name'] == 'kerosene':
+ tank_section_output_dict = {
+ 'cross_section_name_id' + str(j) + '_id' + str(i):
+ [tank_section_path + 'name',
+ tank_section_name],
+ 'cross_section_x_id' + str(j) + '_id' + str(i):
+ [tank_section_path + 'position/x',
+ round(data_dict[tank_id]['geometry'][section_names[i]]['position']['x'], 9)],
+ 'cross_section_y_id' + str(j) + '_id' + str(i):
+ [tank_section_path + 'position/y',
+ round(data_dict[tank_id]['geometry'][section_names[i]]['position']['z'], 9)],
+ 'cross_section_z_id' + str(j) + '_id' + str(i):
+ [tank_section_path + 'position/z',
+ round(data_dict[tank_id]['geometry'][section_names[i]]['position']['y'], 9)],
+ 'shape_id' + str(j) + '_id' + str(i):
+ [tank_section_path + 'shape',
+ data_dict[tank_id]['geometry'][section_names[i]]['shape']],
+ 'height_id' + str(j) + '_id' + str(i):
+ [tank_section_path + 'height',
+ data_dict[tank_id]['geometry'][section_names[i]]['height']],
+ 'width_id' + str(j) + '_id' + str(i):
+ [tank_section_path + 'width',
+ data_dict[tank_id]['geometry'][section_names[i]]['width']],
+ 'length_id' + str(j) + '_id' + str(i):
+ [tank_section_path + 'length',
+ data_dict[tank_id]['geometry'][section_names[i]]['length']]
+ }
+ # Else condition: The energy carrier of current tank is not kerosene
+ # -> use coordinate transformation for fuselage tanks.
+ else:
+ tank_section_output_dict = {
+ 'cross_section_name_id' + str(j) + '_id' + str(i):
+ [tank_section_path + 'name',
+ tank_section_name],
+ 'cross_section_x_id' + str(j) + '_id' + str(i):
+ [tank_section_path + 'position/x',
+ round(data_dict[tank_id]['geometry'][section_names[i]]['position']['y'] * -1, 9)],
+ 'cross_section_y_id' + str(j) + '_id' + str(i):
+ [tank_section_path + 'position/y',
+ round(data_dict[tank_id]['geometry'][section_names[i]]['position']['z'], 9)],
+ 'cross_section_z_id' + str(j) + '_id' + str(i):
+ [tank_section_path + 'position/z',
+ round(data_dict[tank_id]['geometry'][section_names[i]]['position']['x'], 9)],
+ 'shape_id' + str(j) + '_id' + str(i):
+ [tank_section_path + 'shape',
+ data_dict[tank_id]['geometry'][section_names[i]]['shape']],
+ 'height_id' + str(j) + '_id' + str(i):
+ [tank_section_path + 'height',
+ data_dict[tank_id]['geometry'][section_names[i]]['height']],
+ 'width_id' + str(j) + '_id' + str(i):
+ [tank_section_path + 'width',
+ data_dict[tank_id]['geometry'][section_names[i]]['width']],
+ 'length_id' + str(j) + '_id' + str(i):
+ [tank_section_path + 'length',
+ data_dict[tank_id]['geometry'][section_names[i]]['length']]
+ }
+ # merge dictionary to one single output dictionary
+ tank_output_dict.update(tank_section_output_dict)
+ i += 1
+
+ key_output_dict.update(tank_output_dict)
+ j += 1
+
+ # Add additional fuselage length.
+ additional_length_dict = {
+ 'additional_fuselage_length': ['./component_design/tank/specific/additional_fuselage_length',
+ data_dict['total_tank_parameters']['additional_fuselage_length']]
+ }
+
+ key_output_dict.update(additional_length_dict)
+
+ """Method-specific output."""
+ method_specific_output_dict = {}
+ for key, value in key_output_dict.items():
+ if 'mass_properties' not in value[0]:
+ method_specific_output_dict[key] = value
+
+ return key_output_dict, method_specific_output_dict
+
+
+def coordinate_system_conversion(element):
+ if len(element.keys()) > 3:
+ element_3d = py11csc.Element3D(element["j_xx"], element["j_xy"], element["j_xz"],
+ element["j_yx"], element["j_yy"], element["j_yz"],
+ element["j_zx"], element["j_zy"], element["j_zz"])
+ element_3d.AC2CGAL()
+ for k in element.keys():
+ element[k] = getattr(element_3d, k.split("_")[-1])()
+ return element
+ else:
+ element_3d = py11csc.Element3D(element["x"], element["y"], element["z"])
+ element_3d.AC2CGAL()
+ for k in element.keys():
+ element[k] = getattr(element_3d, k)()
+ return element
diff --git a/tank_design/tank_design_conf.xml b/tank_design/tank_design_conf.xml
index d205a1e2c14a4149b7ac6a70378638bbf0596994..cf99c495d6f789eb71e93c2ba8e9d88473c26457 100644
--- a/tank_design/tank_design_conf.xml
+++ b/tank_design/tank_design_conf.xml
@@ -1,5 +1,5 @@
<?xml version="1.0" encoding="UTF-8" ?>
- <module_configuration_file Name="Tank Design Runtime Configuration"> <!-- Change naming according to module name -->
+ <module_configuration_file Name="Tank Design Runtime Configuration">
<control_settings description="General control settings for this tool">
<aircraft_exchange_file_name description="Specify the name of the exchange file">
<value>csmr-2020.xml</value>
@@ -10,42 +10,47 @@
<own_tool_level description="Specify the tool level of this tool">
<value>2</value>
</own_tool_level>
- <console_output description="Selector to specify the console output. Selector: mode_0 (Off) / mode_1 (only out/err/warn) / mode_2 (1 + info) / mode_3 (2 + debug)">
- <value>mode_1</value>
- </console_output>
- <log_file_output description="Selector to specify the log file output. Selector: mode_0 (Off) / mode_1 (only out/err/warn) / mode_2 (1 + info) / mode_3 (2 + debug)">
- <value>mode_1</value>
- </log_file_output>
- <plot_output description="Specify the way plotting shall be handled">
- <enable description="Switch to enable plotting. Switch: true (On) / false (Off)">
- <value>true</value>
- </enable>
- <copy_plotting_files description="Switch if plotting files shall be copied. Switch: true (On) / false (Off)">
- <value>true</value>
- </copy_plotting_files>
- <delete_plotting_files_from_tool_folder description="Switch if plotting files shall be deleted from folder. Switch: true (On) / false (Off)">
- <value>true</value>
- </delete_plotting_files_from_tool_folder>
- </plot_output>
- <report_output description="Switch to generate an HTML report. Switch: true (On) / false (Off)">
- <value>true</value>
- </report_output>
- <tex_report description="Switch to generate a Tex report. Switch: true (On) / false (Off)">
- <value>true</value>
- </tex_report>
- <write_info_files description="Switch to generate info files. Switch: true (On) / false (Off)">
- <value>true</value>
- </write_info_files>
- <log_file description="Specify the name of the log file">
- <value>tank_design.log</value>
- </log_file>
- <inkscape_path description="Path to the inkscape application (DEFAULT: Use inkscape from the UNICADO repo structure)">
- <value>DEFAULT</value>
- </inkscape_path>
- <gnuplot_path description="Path to the gnuplot application (DEFAULT: Use gnuplot from the UNICADO repo structure)">
- <value>DEFAULT</value>
- </gnuplot_path>
- </control_settings>
+ <console_output description="Selector to specify the console output. Selector: mode_0 (Off) / mode_1 (only out/err/warn) / mode_2 (1 + info) / mode_3 (2 + debug)">
+ <value>mode_1</value>
+ </console_output>
+ <log_file_output description="Selector to specify the log file output. Selector: mode_0 (Off) / mode_1 (only out/err/warn) / mode_2 (1 + info) / mode_3 (2 + debug)">
+ <value>mode_1</value>
+ </log_file_output>
+ <plot_output description="Specify the way plotting shall be handled">
+ <enable description="Switch to enable plotting. Switch: true (On) / false (Off)">
+ <value>true</value>
+ </enable>
+ <copy_plotting_files description="Switch if plotting files shall be copied. Switch: true (On) / false (Off)">
+ <value>true</value>
+ </copy_plotting_files>
+ <delete_plotting_files_from_tool_folder description="Switch if plotting files shall be deleted from folder. Switch: true (On) / false (Off)">
+ <value>true</value>
+ </delete_plotting_files_from_tool_folder>
+ </plot_output>
+ <report_output description="Switch to generate an HTML report. Switch: true (On) / false (Off)">
+ <value>true</value>
+ </report_output>
+ <tex_report description="Switch to generate a Tex report. Switch: true (On) / false (Off)">
+ <value>true</value>
+ </tex_report>
+ <write_info_files description="Switch to generate info files. Switch: true (On) / false (Off)">
+ <value>true</value>
+ </write_info_files>
+ <log_file description="Specify the name of the log file">
+ <value>tank_design.log</value>
+ </log_file>
+ <inkscape_path description="Path to the inkscape application (DEFAULT: Use inkscape from the UNICADO repo structure)">
+ <value>DEFAULT</value>
+ </inkscape_path>
+ <gnuplot_path description="Path to the gnuplot application (DEFAULT: Use gnuplot from the UNICADO repo structure)">
+ <value>DEFAULT</value>
+ </gnuplot_path>
+ <program_specific_control_settings description="Program specific control settings for this tool">
+ <xml_output description="Switch to export module specific data to XML ('true': On, 'false': Off)">
+ <value>true</value>
+ </xml_output>
+ </program_specific_control_settings>
+ </control_settings>
<program_settings description="program settings">
<configuration ID="tube_and_wing">
<fidelity_name description="Select fidelity name (options: empirical, numerical,...)">
@@ -68,111 +73,12 @@
</general>
<specific>
<!-- Specific parameters for kerosene tank design. -->
- <kerosene_gravimetric_energy_density description="Gravimetric energy density Jet A-1.">
- <value>43100000</value>
- <unit>J/kg</unit>
- <lower_boundary>0</lower_boundary>
- <upper_boundary>100000000</upper_boundary>
- <default>43100000</default>
- </kerosene_gravimetric_energy_density>
- <kerosene_volumetric_energy_density description="Volumetric energy density Jet A-1.">
- <value>34100000000</value>
- <unit>J/m^3</unit>
- <lower_boundary>0</lower_boundary>
- <upper_boundary>40000000000</upper_boundary>
- <default>34100000000</default>
- </kerosene_volumetric_energy_density>
- <liquid_hydrogen_tank_structure>
- <liquid_hydrogen_gravimetric_energy_density description="Gravimetric energy density.">
- <value>119930000</value>
- <unit>J/kg</unit>
- <lower_boundary>0</lower_boundary>
- <upper_boundary>120000000</upper_boundary>
- <default>119930000</default>
- </liquid_hydrogen_gravimetric_energy_density>
- <liquid_hydrogen_volumetric_energy_density description="Volumetric energy density.">
- <value>8491000000</value>
- <unit>J/m^3</unit>
- <lower_boundary>0</lower_boundary>
- <upper_boundary>8500000000</upper_boundary>
- <default>8491000000</default>
- </liquid_hydrogen_volumetric_energy_density>
- <!-- Tank structure related parameters-->
- <material_wall description="Tank wall material (options: aluminum)">
- <value>aluminum</value>
- <default>aluminum</default>
- </material_wall>
- <density_wall description="Density of wall material (for aluminum: 2850)">
- <value>2850</value>
- <unit>kg/m^3</unit>
- <lower_boundary>0</lower_boundary>
- <upper_boundary>5000</upper_boundary>
- <default>2850</default>
- </density_wall>
- <thickness_wall_calculation_method description="Method for calculation of wall thickness (options: asme, ad-2000)">
- <value>asme</value>
- <default>asme</default>
- </thickness_wall_calculation_method>
- <mass_baffle description="Additional mass of baffles">
- <value>45</value>
- <unit>kg</unit>
- <lower_boundary>0</lower_boundary>
- <upper_boundary>100</upper_boundary>
- <default>45</default>
- </mass_baffle>
- <mass_pumps description="Additional mass of pumps">
- <value>9.26</value>
- <unit>kg</unit>
- <lower_boundary>0</lower_boundary>
- <upper_boundary>100</upper_boundary>
- <default>9.26</default>
- </mass_pumps>
- </liquid_hydrogen_tank_structure>
- <liquid_hydrogen_tank_insulation>
- <!-- Tank insulation related parameters-->
- <type_insulation description="Insulation type (options: internal, external)">
- <value>external</value>
- <default>external</default>
- </type_insulation>
- <material_insulation description="Insulation material (options: polyurethane_foam)">
- <value>polyurethane_foam</value>
- <default>polyurethane_foam</default>
- </material_insulation>
- <thickness_insulation description="Thickness of insulation">
- <value>0.2</value>
- <unit>m</unit>
- <lower_boundary>0</lower_boundary>
- <upper_boundary>1.0</upper_boundary>
- <default>0.2</default>
- </thickness_insulation>
- <density_insulation description="Density of insulation material (for polyurethane foam: 32)">
- <value>32</value>
- <unit>kg/m^3</unit>
- <lower_boundary>0</lower_boundary>
- <upper_boundary>100</upper_boundary>
- <default>32</default>
- </density_insulation>
- </liquid_hydrogen_tank_insulation>
- <liquid_hydrogen_tank_design_parameter>
- <!-- Design parameters-->
- <type_end_cap description="Tank end cap type (options: hemispherical, torispherical)">
- <value>torispherical</value>
- <default>torispherical</default>
- </type_end_cap>
- <internal_pressure description="Internal tank pressure (venting pressure)">
- <value>1.5</value>
- <unit>bar</unit>
- <lower_boundary>1</lower_boundary>
- <upper_boundary>5</upper_boundary>
- <default>1.5</default>
- </internal_pressure>
- </liquid_hydrogen_tank_design_parameter>
- <kerosene_tank_design_parameter>
+ <kerosene_tank_design_parameter description="Parameters for kerosene tank design">
<obelisk_calculation_method description="Obelisk volume calculation method (Torenbeek or Simpson).">
<value>Simpson</value>
<default>Torenbeek</default>
</obelisk_calculation_method>
- <a_to_d_factor>
+ <a_to_d_factor description="Factor ...">
<value>0.9</value>
<unit>1</unit>
<lower_boundary>0</lower_boundary>
@@ -215,6 +121,75 @@
<default>0.01</default>
</buffer_center_tank_segment>
</kerosene_tank_design_parameter>
+ <!-- Specific parameters for liquid hydrogen tank design. -->
+ <liquid_hydrogen_tank_design_parameter description="Parameters for liquid hydrogen tank design">
+ <!-- Design parameters-->
+ <type_end_cap description="Tank end cap type (options: hemispherical, torispherical)">
+ <value>torispherical</value>
+ <default>torispherical</default>
+ </type_end_cap>
+ <internal_pressure description="Internal tank pressure (venting pressure)">
+ <value>1.5</value>
+ <unit>bar</unit>
+ <lower_boundary>1</lower_boundary>
+ <upper_boundary>5</upper_boundary>
+ <default>1.5</default>
+ </internal_pressure>
+ <!-- Tank insulation related parameters-->
+ <type_insulation description="Insulation type (options: internal, external)">
+ <value>external</value>
+ <default>external</default>
+ </type_insulation>
+ <material_insulation description="Insulation material (options: polyurethane_foam)">
+ <value>polyurethane_foam</value>
+ <default>polyurethane_foam</default>
+ </material_insulation>
+ <thickness_insulation description="Thickness of insulation">
+ <value>0.2</value>
+ <unit>m</unit>
+ <lower_boundary>0</lower_boundary>
+ <upper_boundary>1.0</upper_boundary>
+ <default>0.2</default>
+ </thickness_insulation>
+ <density_insulation description="Density of insulation material (for polyurethane foam: 32)">
+ <value>32</value>
+ <unit>kg/m^3</unit>
+ <lower_boundary>0</lower_boundary>
+ <upper_boundary>100</upper_boundary>
+ <default>32</default>
+ </density_insulation>
+ <!-- Tank structure related parameters-->
+ <material_wall description="Tank wall material (options: aluminum)">
+ <value>aluminum</value>
+ <default>aluminum</default>
+ </material_wall>
+ <density_wall description="Density of wall material (for aluminum: 2850)">
+ <value>2850</value>
+ <unit>kg/m^3</unit>
+ <lower_boundary>0</lower_boundary>
+ <upper_boundary>5000</upper_boundary>
+ <default>2850</default>
+ </density_wall>
+ <thickness_wall_calculation_method description="Method for calculation of wall thickness (options: asme, ad-2000)">
+ <value>asme</value>
+ <default>asme</default>
+ </thickness_wall_calculation_method>
+ <mass_baffle description="Additional mass of baffles">
+ <value>45</value>
+ <unit>kg</unit>
+ <lower_boundary>0</lower_boundary>
+ <upper_boundary>100</upper_boundary>
+ <default>45</default>
+ </mass_baffle>
+ <mass_pumps description="Additional mass of pumps">
+ <value>9.26</value>
+ <unit>kg</unit>
+ <lower_boundary>0</lower_boundary>
+ <upper_boundary>100</upper_boundary>
+ <default>9.26</default>
+ </mass_pumps>
+ </liquid_hydrogen_tank_design_parameter>
+ <!-- Miscellaneous parameters for tank design. -->
<miscellaneous>
<!-- Miscellaneous parameters-->
<factor_usable_diameter description="Usable fraction of fuselage outside diameter">