From c489b4c8a088ae17897cb8e361141d4dfe00a54d Mon Sep 17 00:00:00 2001
From: AndiGob <andreas.gobbbin@hotmail.de>
Date: Tue, 10 Dec 2024 18:28:35 +0100
Subject: [PATCH 1/6] landing_gear_design: -Add owne function for wing tip
clearance check
---
.../landing_gear_design_conf.xml | 14 ++---
.../call_functions/_04_estimatelimitations.py | 11 +++-
.../sub_function/wingtipclearance.py | 61 +++++++++++++++++++
3 files changed, 77 insertions(+), 9 deletions(-)
create mode 100644 landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/wingtipclearance.py
diff --git a/landing_gear_design/landing_gear_design_conf.xml b/landing_gear_design/landing_gear_design_conf.xml
index 656a5388..3786d73c 100644
--- a/landing_gear_design/landing_gear_design_conf.xml
+++ b/landing_gear_design/landing_gear_design_conf.xml
@@ -99,17 +99,17 @@
</wing_strike_limit>
</ground_strike_limitations>
<nacelle_clearance description="Nacelle clearance according to CS25.149.">
- <value>7</value>
- <unit>degree</unit>
- <lower_boundary>5</lower_boundary>
- <upper_boundary>10</upper_boundary>
- <default>7</default>
+ <value>0.55</value>
+ <unit>m</unit>
+ <lower_boundary>0.45</lower_boundary>
+ <upper_boundary>0.90</upper_boundary>
+ <default>0.60</default>
</nacelle_clearance>
<strut_suspension description="Switch to use landing gear strut suspension systems. ('true': use, 'false': don't use">
<value>true</value>
<default>true</default>
<strut_suspension_travel>
- <value>0.4699</value>
+ <value>0.65</value>
<unit>m</unit>
<lower_boundary>0.35</lower_boundary>
<upper_boundary>0.95</upper_boundary>
@@ -117,7 +117,7 @@
</strut_suspension_travel>
</strut_suspension>
<landing_gear_bay_keel_beam_width description="Width of the landing gear bay keel beam.">
- <value>0.8</value>
+ <value>0.55</value>
<unit>m</unit>
<lower_boundary>0.5</lower_boundary>
<upper_boundary>1.5</upper_boundary>
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_04_estimatelimitations.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_04_estimatelimitations.py
index 4323022b..f7ecffce 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_04_estimatelimitations.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_04_estimatelimitations.py
@@ -2,6 +2,9 @@
import sys
import math
+# import own modules.
+from src.wing_mounted.empirical.landing_gear_design_tu_berlin.general.call_functions.sub_function.wingtipclearance import wing_tip_clearance # noPep8 e501
+
def estimate_limitations(dict_ac_exchange, dict_mod_config, landing_gear_description, runtime_output):
""" Hier beschreibung hin: Estimation of ground strike limitations in accordance to Sforza and CS-25
@@ -365,7 +368,11 @@ def estimate_limitations(dict_ac_exchange, dict_mod_config, landing_gear_descrip
landing_gear_description['main_gear_description']['main_gear_arrangement'] = main_gear_arrangement
landing_gear_description['nose_gear_description']['nose_gear_arrangement'] = nose_gear_arrangement
landing_gear_description['tail_tipping_point']['maximum_rotation_angle_landing'] = maximum_rotation_angle_landing
-
- runtime_output.debug('estimate_limitations successfully executed!')
+
+ # Call function to check the wing tip clearance.
+ landing_gear_description = wing_tip_clearance(dict_ac_exchange, dict_mod_config, landing_gear_description, runtime_output)
+
+ # debug print
+ runtime_output.debug('The function "estimate_limitations.py" successfully executed!')
return landing_gear_description
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/wingtipclearance.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/wingtipclearance.py
new file mode 100644
index 00000000..cba618ac
--- /dev/null
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/wingtipclearance.py
@@ -0,0 +1,61 @@
+# Import standard modules.
+import math
+
+
+def wing_tip_clearance(dict_ac_exchange, dict_mod_config, landing_gear_description, runtime_output):
+ """ Estimation of wing tip clearance in accordance to Torenbeek and CS-25
+ [ref. E. Torenbeek; 1982]
+ [ref. CS-25 Amendment 27; 2022]
+
+ :param dict dict_ac_exchange: Dict containing parameter and according values from aircraft exchange file
+ :param dict dict_mod_config: Dict containing parameter and according values from module configuration file
+ :param dict landing_gear_description: Dict containing parameter and values of current landing gear estimation
+ :param logging.Logger runtime_output: Logging object used for capturing log messages in the module
+ :return dict landing_gear_description: Dict containing parameter and values of current landing gear estimation
+ """
+ ''' initialize local parameter '''
+ wing_tip_clearance_angle = 0
+ minimum_required_clearance_angle = 5 # according to CS25.149 -> minimum 5 degree bank angle
+
+ ''' check wing tip clearance '''
+ try:
+ _, wing_reference_point_on_tip_in_y_value = \
+ next(reversed(list(dict_ac_exchange['wing_section_position_in_y'].items())), (None, None))
+ _, wing_reference_point_on_tip_in_z_value = \
+ next(reversed(list(dict_ac_exchange['wing_section_position_in_z'].items())), (None, None))
+
+ if wing_reference_point_on_tip_in_y_value is not None and wing_reference_point_on_tip_in_z_value is not None:
+ distance_between_wing_tip_and_outer_strut = \
+ round(wing_reference_point_on_tip_in_y_value
+ - landing_gear_description['landing_gear_positions']['main_gear_outer_strut_y_position'], 4)
+ wing_tip_ground_clearance = \
+ (landing_gear_description['lever_arms']['vertical_distance_between_ground_and_fuselage_center_line']
+ - wing_reference_point_on_tip_in_z_value)
+ wing_tip_clearance_angle = \
+ round(math.degrees(math.atan(wing_tip_ground_clearance/distance_between_wing_tip_and_outer_strut)), 4)
+
+ if wing_tip_clearance_angle < dict_mod_config['wing_strike_limit'] \
+ and not wing_tip_clearance_angle < minimum_required_clearance_angle:
+ raise ValueError('The resulting wing tip angle is below the specified clearance angle of: '
+ + str(dict_mod_config['wing_strike_limit']) + ' degrees!')
+ elif wing_tip_clearance_angle < minimum_required_clearance_angle:
+ raise ValueError('The resulting wing tip angle is below the required clearance angle of the '
+ 'CS25.149 of: ' + str(minimum_required_clearance_angle) + ' degrees!')
+ else:
+ runtime_output.print('The resulting wing tip angle conforms the specified clearance angle of: '
+ + str(dict_mod_config['wing_strike_limit']) + ' degrees!')
+
+ else:
+ raise ValueError('At least one wing parameter is missing in the aircraft exchange file, '
+ 'wing tip clearance could not be checked!')
+
+ # exception handling for wing tip clearance check
+ except ValueError as e:
+ runtime_output.error('Error: ' + str(e))
+
+ landing_gear_description['landing_gear_limitations']['wing_tip_clearance_angles'] = wing_tip_clearance_angle
+
+ # debug print
+ runtime_output.debug('estimate_clearances successfully executed!')
+
+ return landing_gear_description
--
GitLab
From ae3e906f4612d79dc45544c2ac1a065d4db6d4c3 Mon Sep 17 00:00:00 2001
From: AndiGob <andreas.gobbbin@hotmail.de>
Date: Tue, 10 Dec 2024 18:39:33 +0100
Subject: [PATCH 2/6] landing_gear_design: - Add owne function for nacelle
ground clearance check
---
.../call_functions/_05_estimateclearances.py | 38 -------------------
.../sub_function/nacellegroundclearance.py | 33 ++++++++++++++++
.../usermethoddatapreparation.py | 2 +
3 files changed, 35 insertions(+), 38 deletions(-)
create mode 100644 landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/nacellegroundclearance.py
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_05_estimateclearances.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_05_estimateclearances.py
index 2397d661..397cc577 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_05_estimateclearances.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_05_estimateclearances.py
@@ -17,7 +17,6 @@ def estimate_clearances(dict_ac_exchange, dict_mod_config, landing_gear_descript
specific_flag = False
required_flag = False
nacelle_clearance_angle = []
- wing_tip_clearance_angle = 0
minimum_required_clearance_angle = 5 # according to CS25.149 -> minimum 5 degree bank angle
propulsor_mounting_position = list(dict_ac_exchange['propulsor_mounting_position'].values())
nacelle_y_position = {key: value for key, value in dict_ac_exchange['engine_y_position'].items() if
@@ -86,44 +85,7 @@ def estimate_clearances(dict_ac_exchange, dict_mod_config, landing_gear_descript
except ValueError as e:
runtime_output.error('Error: ' + str(e))
- ''' check wing tip clearance '''
- try:
- _, wing_reference_point_on_tip_in_y_value = \
- next(reversed(list(dict_ac_exchange['wing_section_position_in_y'].items())), (None, None))
- _, wing_reference_point_on_tip_in_z_value = \
- next(reversed(list(dict_ac_exchange['wing_section_position_in_z'].items())), (None, None))
-
- if wing_reference_point_on_tip_in_y_value is not None and wing_reference_point_on_tip_in_z_value is not None:
- distance_between_wing_tip_and_outer_strut = \
- round(wing_reference_point_on_tip_in_y_value
- - landing_gear_description['landing_gear_positions']['main_gear_outer_strut_y_position'], 4)
- wing_tip_ground_clearance = \
- (landing_gear_description['lever_arms']['vertical_distance_between_ground_and_fuselage_center_line']
- - wing_reference_point_on_tip_in_z_value)
- wing_tip_clearance_angle = \
- round(math.degrees(math.atan(wing_tip_ground_clearance/distance_between_wing_tip_and_outer_strut)), 4)
-
- if wing_tip_clearance_angle < dict_mod_config['wing_strike_limit'] \
- and not wing_tip_clearance_angle < minimum_required_clearance_angle:
- raise ValueError('The resulting wing tip angle is below the specified clearance angle of: '
- + str(dict_mod_config['wing_strike_limit']) + ' degrees!')
- elif wing_tip_clearance_angle < minimum_required_clearance_angle:
- raise ValueError('The resulting wing tip angle is below the required clearance angle of the '
- 'CS25.149 of: ' + str(minimum_required_clearance_angle) + ' degrees!')
- else:
- runtime_output.print('The resulting wing tip angle conforms the specified clearance angle of: '
- + str(dict_mod_config['wing_strike_limit']) + ' degrees!')
-
- else:
- raise ValueError('At least one wing parameter is missing in the aircraft exchange file, '
- 'wing tip clearance could not be checked!')
-
- # exception handling for wing tip clearance check
- except ValueError as e:
- runtime_output.error('Error: ' + str(e))
-
landing_gear_description['landing_gear_limitations']['nacelle_ground_clearance_angles'] = nacelle_clearance_angle
- landing_gear_description['landing_gear_limitations']['wing_tip_clearance_angles'] = wing_tip_clearance_angle
# debug print
runtime_output.debug('estimate_clearances successfully executed!')
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/nacellegroundclearance.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/nacellegroundclearance.py
new file mode 100644
index 00000000..4ed78ed8
--- /dev/null
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/nacellegroundclearance.py
@@ -0,0 +1,33 @@
+def nacelle_ground_clearance(dict_ac_exchange, dict_mod_config, landing_gear_description, main_gear_arrangement, runtime_output):
+ """ Estimation of ancelle ground clearance in accordance to Torenbeek and CS-25.
+ [ref. E. Torenbeek; 1982]
+ [ref. CS-25 Amendment 27; 2022]
+
+ :param dict dict_ac_exchange: Dict containing parameter and according values from aircraft exchange file
+ :param dict dict_mod_config: Dict containing parameter and according values from module configuration file
+ :param dict landing_gear_description: Dict containing parameter and values of current landing gear estimation
+ :param dict main_gear_arrangement: Dict containing parameter and values of current main landing gear arrengment
+ :param logging.Logger runtime_output: Logging object used for capturing log messages in the module
+ :return list required_main_gear_strut_delta_length: List containing requiered delta lengths for each wing mounted nacelle
+ bool nacelle_ground_clearance_flag: Status flag if the ground clearance check is failed and a deltea length is required
+ """
+ ''' initialize local parameter '''
+ nacelle_ground_clearance_flag = False
+ required_main_gear_strut_delta_length = []
+
+ nacelle_y_position = {key: value for key, value in dict_ac_exchange['engine_y_position'].items() if value is not None}
+ nacelle_y_position = list(nacelle_y_position.values())
+ nacelle_z_position = {key: value for key, value in dict_ac_exchange['engine_z_position'].items() if value is not None}
+ nacelle_z_position = list(nacelle_z_position.values())
+ nacelle_section_widths = {key: value for key, value in dict_ac_exchange['nacelle_section_widths'].items() if value is not None}
+ nacelle_section_widths = list(nacelle_section_height.values())
+ nacelle_section_height = {key: value for key, value in dict_ac_exchange['nacelle_section_height'].items() if value is not None}
+ nacelle_section_height = list(nacelle_section_height.values())
+
+ # Check if the current propulsor is mounted to the wing
+ # -> if true: -> prepare wing nacelle paramter for ground clearance check
+ for key, value in dict_ac_exchange['propulsor_mounting_position'].item():
+ print(value)
+ print(key)
+
+ return required_main_gear_strut_delta_length, nacelle_ground_clearance_flag
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/usermethoddatapreparation.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/usermethoddatapreparation.py
index 7ecdb4e2..43a35197 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/usermethoddatapreparation.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/usermethoddatapreparation.py
@@ -76,6 +76,8 @@ def user_method_data_input_preparation(routing_dict):
['./analysis/masses_cg_inertia/most_forward_mass/mass_properties/center_of_gravity/y', float],
'most_forward_center_of_gravity_in_z_direction':
['./analysis/masses_cg_inertia/most_forward_mass/mass_properties/center_of_gravity/z', float],
+ 'nacelle_section_width':
+ ['./component_design/propulsion/specific/propulsion[@ID="0"]/nacelle[@ID="0"]/sections/section/[@ID="0"]/width', float], # noPep8 e501
'nacelle_section_height':
['./component_design/propulsion/specific/propulsion[@ID="0"]/nacelle[@ID="0"]/sections/section/[@ID="0"]/height', float], # noPep8 e501
'engine_x_position':
--
GitLab
From 0455de2ad721d527cedb25d88eb57c2fef7efee4 Mon Sep 17 00:00:00 2001
From: AndiGob <andreas.gobbbin@hotmail.de>
Date: Tue, 10 Dec 2024 23:33:38 +0100
Subject: [PATCH 3/6] landing_gear_design: - Add nacelle ground clearance check
to landing gear strut length estimation
---
.../call_functions/_01_estimatedistances.py | 8 +-
.../call_functions/_04_estimatelimitations.py | 22 +++++
.../call_functions/_05_estimateclearances.py | 93 -------------------
...stimatemasses.py => _05_estimatemasses.py} | 0
...{_07_estimatecog.py => _06_estimatecog.py} | 0
...geometry.py => _07_setexistinggeometry.py} | 0
.../sub_function/nacellegroundclearance.py | 40 ++++++--
.../sub_function/wingtipclearance.py | 2 +-
.../general/useexistinggeometry.py | 6 +-
9 files changed, 62 insertions(+), 109 deletions(-)
delete mode 100644 landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_05_estimateclearances.py
rename landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/{_06_estimatemasses.py => _05_estimatemasses.py} (100%)
rename landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/{_07_estimatecog.py => _06_estimatecog.py} (100%)
rename landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/{_08_setexistinggeometry.py => _07_setexistinggeometry.py} (100%)
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_01_estimatedistances.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_01_estimatedistances.py
index 301bfb86..a4902c22 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_01_estimatedistances.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_01_estimatedistances.py
@@ -192,15 +192,15 @@ def estimate_distances(dict_ac_exchange, dict_mod_config, landing_gear_descripti
fuselage_reference_point_z_key, fuselage_reference_point_z_value = \
next(iter(dict_ac_exchange['fuselage_reference_point_in_z_direction'].items()), (None, None))
if fuselage_reference_point_z_value is not None \
- and dict_ac_exchange['most_aft_center_of_gravity_in_z_direction'] is not None:
- if fuselage_reference_point_z_value <= dict_ac_exchange['most_aft_center_of_gravity_in_z_direction']:
+ and dict_ac_exchange['center_of_gravity_in_z'] is not None:
+ if fuselage_reference_point_z_value <= dict_ac_exchange['center_of_gravity_in_z']:
delta_height_fuselage_center_line_to_center_of_gravity = \
- abs(dict_ac_exchange['most_aft_center_of_gravity_in_z_direction']
+ abs(dict_ac_exchange['center_of_gravity_in_z']
- fuselage_reference_point_z_value)
else:
delta_height_fuselage_center_line_to_center_of_gravity = \
abs(fuselage_reference_point_z_value
- - dict_ac_exchange['most_aft_center_of_gravity_in_z_direction'])
+ - dict_ac_exchange['center_of_gravity_in_z'])
elif dict_ac_exchange['fuselage_type'] == 'single_aisle':
delta_height_fuselage_center_line_to_center_of_gravity = 0.5
elif dict_ac_exchange['fuselage_type'] == 'wide_body':
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_04_estimatelimitations.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_04_estimatelimitations.py
index f7ecffce..7689c8d3 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_04_estimatelimitations.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_04_estimatelimitations.py
@@ -4,6 +4,7 @@ import math
# import own modules.
from src.wing_mounted.empirical.landing_gear_design_tu_berlin.general.call_functions.sub_function.wingtipclearance import wing_tip_clearance # noPep8 e501
+from src.wing_mounted.empirical.landing_gear_design_tu_berlin.general.call_functions.sub_function.nacellegroundclearance import nacelle_ground_clearance # noPep8 e501
def estimate_limitations(dict_ac_exchange, dict_mod_config, landing_gear_description, runtime_output):
@@ -193,6 +194,25 @@ def estimate_limitations(dict_ac_exchange, dict_mod_config, landing_gear_descrip
'vertical_distance_between_ground_and_aft_center_of_gravity']
+ main_gear_arrangement['main_landing_gear_wing_mounting_position_in_z_direction'])
- (min_tire_diameter/2 * convert_inch_to_meter), 4)
+
+ # Check nacelle ground clearance if at least one engine is exisiting.
+ if dict_ac_exchange['engine_z_position'] is not None:
+ # Call function to check nacelle ground clearance.
+ required_main_gear_strut_delta_length, nacelle_ground_clearance_flag = \
+ nacelle_ground_clearance(dict_ac_exchange, dict_mod_config, landing_gear_description,
+ main_gear_arrangement, runtime_output)
+
+ # Check if nacelle ground clearance check is failed
+ # -> if true: -> start repositioning and resizing of main landing gear struts.
+ if nacelle_ground_clearance_flag:
+ if i == 1:
+ runtime_output.warning('Attention: At least one nacelle mounted to the wing '
+ 'falls below the minimum required nacelle ground clearance.')
+ runtime_output.print('Repositioning and resizing of landing gear struts started!')
+
+ # Add required delta length to the length of main landing gear struts.
+ main_gear_arrangement['main_gear_outer_strut_length'] += max(required_main_gear_strut_delta_length)
+
landing_gear_description['landing_gear_positions']['main_gear_z_position_outer_strut'] = \
round(main_gear_arrangement['main_landing_gear_wing_mounting_position_in_z_direction'], 4)
@@ -289,6 +309,8 @@ def estimate_limitations(dict_ac_exchange, dict_mod_config, landing_gear_descrip
+ 0.05)
i += 1
+ runtime_output.print('Repositioning and resizing of landing gear struts successfully finished!')
+
try:
# check if the turnover iteration failed -> if true: -> raise an error and abort program
if not main_gear_positioning_flag:
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_05_estimateclearances.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_05_estimateclearances.py
deleted file mode 100644
index 397cc577..00000000
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_05_estimateclearances.py
+++ /dev/null
@@ -1,93 +0,0 @@
-# Import standard modules.
-import math
-
-
-def estimate_clearances(dict_ac_exchange, dict_mod_config, landing_gear_description, runtime_output):
- """ Hier beschreibung hin: Estimation of ground clearances in accordance to Torenbeek and CS-25
- [ref. E. Torenbeek; 1982]
- [ref. CS-25 Amendment 27; 2022]
-
- :param dict dict_ac_exchange: Dict containing parameter and according values from aircraft exchange file
- :param dict dict_mod_config: Dict containing parameter and according values from module configuration file
- :param dict landing_gear_description: Dict containing parameter and values of current landing gear estimation
- :param logging.Logger runtime_output: Logging object used for capturing log messages in the module
- :return dict landing_gear_description: Dict containing parameter and values of current landing gear estimation
- """
- ''' initialize local parameter '''
- specific_flag = False
- required_flag = False
- nacelle_clearance_angle = []
- minimum_required_clearance_angle = 5 # according to CS25.149 -> minimum 5 degree bank angle
- propulsor_mounting_position = list(dict_ac_exchange['propulsor_mounting_position'].values())
- nacelle_y_position = {key: value for key, value in dict_ac_exchange['engine_y_position'].items() if
- value is not None}
- nacelle_y_position = list(nacelle_y_position.values())
- nacelle_z_position = {key: value for key, value in dict_ac_exchange['engine_z_position'].items() if
- value is not None}
- nacelle_z_position = list(nacelle_z_position.values())
- nacelle_section_height = {key: value for key, value in dict_ac_exchange['nacelle_section_height'].items() if
- value is not None}
- nacelle_section_height = list(nacelle_section_height.values())
- main_gear_outer_strut_y_position = landing_gear_description['landing_gear_positions'][
- 'main_gear_outer_strut_y_position']
-
- ''' check nacelle clearance '''
- try:
- # check if at least one engine exist in the aircraft exchange file
- if len(nacelle_y_position) > 0:
- index = 0
- # loop across all existing engines
- for position in nacelle_y_position:
- # check if the current engine is mounted to the wing -> if true: -> estimate clearance angle
- if propulsor_mounting_position[index] == 'wing':
- # check if the y-position of current engine is not within the outer landing gear leg position
- # -> if true: -> estimate clearance angle
- if abs(position) > main_gear_outer_strut_y_position:
- # estimate clearance angle between outer main landing gear strut and lowest point of nacelle
- distances = abs(position) - main_gear_outer_strut_y_position
- nacelle_ground_clearance = round(landing_gear_description['lever_arms'][
- 'vertical_distance_between_ground_and_fuselage_center_line']
- - abs(nacelle_z_position[index])
- - abs(nacelle_section_height[index]/2), 4)
- nacelle_clearance_angle.append(
- round(math.degrees(math.atan(nacelle_ground_clearance/distances)), 4))
- # Else condition: current engine is within the outer landing gear leg position
- # -> raise an error and skip nacelle ground clearance estimation
- else:
- raise ValueError('At least one wing mounted engine is within the outer landing gear leg '
- 'position. No valid configuration!')
- index += 1
-
- # loop across all existing nacelle clearance angles to check angle requirements
- for angle in nacelle_clearance_angle:
- if angle < dict_mod_config['nacelle_clearance'] and not angle < minimum_required_clearance_angle:
- specific_flag = True
- elif angle < minimum_required_clearance_angle:
- required_flag = True
-
- if specific_flag and not required_flag:
- raise ValueError('At least one wing mounted engine falls below the specified clearance angle of: '
- + str(dict_mod_config['nacelle_clearance']) + ' degrees!')
- elif required_flag:
- raise ValueError('At least one wing mounted engine falls below the required clearance angle of the '
- 'CS25.149 of: '
- + str(minimum_required_clearance_angle) + ' degrees!')
- else:
- runtime_output.print('All engines mounted to the wing conforms the specified clearance angle of: '
- + str(dict_mod_config['nacelle_clearance']) + ' degrees!')
-
- # Else condition: no engine exists in the aircraft exchange file -> print a warning
- else:
- runtime_output.warning('Attention: No engines available in the aircraft exchange file, '
- 'nacelle ground clearance could not be checked!')
-
- # exception handling for nacelle ground clearance check
- except ValueError as e:
- runtime_output.error('Error: ' + str(e))
-
- landing_gear_description['landing_gear_limitations']['nacelle_ground_clearance_angles'] = nacelle_clearance_angle
-
- # debug print
- runtime_output.debug('estimate_clearances successfully executed!')
-
- return landing_gear_description
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_06_estimatemasses.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_05_estimatemasses.py
similarity index 100%
rename from landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_06_estimatemasses.py
rename to landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_05_estimatemasses.py
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_07_estimatecog.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_06_estimatecog.py
similarity index 100%
rename from landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_07_estimatecog.py
rename to landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_06_estimatecog.py
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_08_setexistinggeometry.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_07_setexistinggeometry.py
similarity index 100%
rename from landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_08_setexistinggeometry.py
rename to landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_07_setexistinggeometry.py
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/nacellegroundclearance.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/nacellegroundclearance.py
index 4ed78ed8..4140caaa 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/nacellegroundclearance.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/nacellegroundclearance.py
@@ -12,22 +12,46 @@ def nacelle_ground_clearance(dict_ac_exchange, dict_mod_config, landing_gear_des
bool nacelle_ground_clearance_flag: Status flag if the ground clearance check is failed and a deltea length is required
"""
''' initialize local parameter '''
+ engine_counter = 0
nacelle_ground_clearance_flag = False
required_main_gear_strut_delta_length = []
-
+ wing_nacelle_bottom_position = []
+ wing_nacelle_inboard_position = []
nacelle_y_position = {key: value for key, value in dict_ac_exchange['engine_y_position'].items() if value is not None}
nacelle_y_position = list(nacelle_y_position.values())
nacelle_z_position = {key: value for key, value in dict_ac_exchange['engine_z_position'].items() if value is not None}
nacelle_z_position = list(nacelle_z_position.values())
- nacelle_section_widths = {key: value for key, value in dict_ac_exchange['nacelle_section_widths'].items() if value is not None}
- nacelle_section_widths = list(nacelle_section_height.values())
- nacelle_section_height = {key: value for key, value in dict_ac_exchange['nacelle_section_height'].items() if value is not None}
- nacelle_section_height = list(nacelle_section_height.values())
+ nacelle_section_widths = {key: value for key, value in dict_ac_exchange['nacelle_section_width'].items() if value is not None}
+ nacelle_section_widths = list(nacelle_section_widths.values())
+ nacelle_section_heights = {key: value for key, value in dict_ac_exchange['nacelle_section_height'].items() if value is not None}
+ nacelle_section_heights = list(nacelle_section_heights.values())
# Check if the current propulsor is mounted to the wing
# -> if true: -> prepare wing nacelle paramter for ground clearance check
- for key, value in dict_ac_exchange['propulsor_mounting_position'].item():
- print(value)
- print(key)
+ for _, value in dict_ac_exchange['propulsor_mounting_position'].items():
+ if value == 'wing':
+ idx_start = int(engine_counter * (len(nacelle_section_widths)/len(nacelle_y_position)))
+ idx_end = int(engine_counter * (len(nacelle_section_widths)/len(nacelle_y_position))
+ + (len(nacelle_section_widths)/len(nacelle_y_position)))
+ wing_nacelle_bottom_position.append(nacelle_z_position[engine_counter]
+ - max(nacelle_section_heights[idx_start:idx_end])/2)
+ wing_nacelle_inboard_position.append(abs(nacelle_y_position[engine_counter])
+ - max(nacelle_section_widths[idx_start:idx_end])/2)
+ engine_counter += 1
+
+ # Multiply every second nacelle inboard postion by -1
+ wing_nacelle_inboard_position = [value if index % 2 == 0 else -value
+ for index, value in enumerate(wing_nacelle_inboard_position)]
+ # Check if the posiotn of current nacelle under investigation is below the minimum required nacelle ground clearance.
+ for i in range(0, len(wing_nacelle_bottom_position)):
+ clearance_required = abs(wing_nacelle_bottom_position[i]) + dict_mod_config['nacelle_clearance']
+ clearance_available = landing_gear_description['lever_arms']['vertical_distance_between_ground_and_fuselage_center_line']
+ if (clearance_required > clearance_available):
+ nacelle_ground_clearance_flag = True
+ required_main_gear_strut_delta_length.append(clearance_required - clearance_available)
+
+ # debug print
+ runtime_output.debug('The function "nacelle_ground_clearance.py" successfully executed!')
+
return required_main_gear_strut_delta_length, nacelle_ground_clearance_flag
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/wingtipclearance.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/wingtipclearance.py
index cba618ac..4bb528a3 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/wingtipclearance.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/wingtipclearance.py
@@ -56,6 +56,6 @@ def wing_tip_clearance(dict_ac_exchange, dict_mod_config, landing_gear_descripti
landing_gear_description['landing_gear_limitations']['wing_tip_clearance_angles'] = wing_tip_clearance_angle
# debug print
- runtime_output.debug('estimate_clearances successfully executed!')
+ runtime_output.debug('The function "wing_tip_clearance.py" successfully executed!')
return landing_gear_description
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/useexistinggeometry.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/useexistinggeometry.py
index b8a5014c..de7b7432 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/useexistinggeometry.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/useexistinggeometry.py
@@ -4,10 +4,10 @@ import xml.etree.ElementTree as ET
# Import own modules.
from src.wing_mounted.empirical.landing_gear_design_tu_berlin.general.landinggeardesign import landing_gear_design # noPep8 e501
-from src.wing_mounted.empirical.landing_gear_design_tu_berlin.general.call_functions._07_estimatecog import estimate_cog
+from src.wing_mounted.empirical.landing_gear_design_tu_berlin.general.call_functions._06_estimatecog import estimate_cog
from src.wing_mounted.empirical.landing_gear_design_tu_berlin.general.plot_functions.generateacnplots import generate_acn_plots # noPep8 e501
-from src.wing_mounted.empirical.landing_gear_design_tu_berlin.general.call_functions._06_estimatemasses import estimate_masses # noPep8 e501
-from src.wing_mounted.empirical.landing_gear_design_tu_berlin.general.call_functions._08_setexistinggeometry import set_existing_geometry # noPep8 e501
+from src.wing_mounted.empirical.landing_gear_design_tu_berlin.general.call_functions._05_estimatemasses import estimate_masses # noPep8 e501
+from src.wing_mounted.empirical.landing_gear_design_tu_berlin.general.call_functions._07_setexistinggeometry import set_existing_geometry # noPep8 e501
from src.wing_mounted.empirical.landing_gear_design_tu_berlin.general.plot_functions.generatelandinggearplots import generate_landing_gear_plots # noPep8 e501
from src.wing_mounted.empirical.landing_gear_design_tu_berlin.general.aicraft_classification_number.estimateaircraftclassificationnumber import estimate_aircraft_classification_number # noPep8 e501
--
GitLab
From 3e8fa6f52a61ef8d586784c04de59a6b06a948a0 Mon Sep 17 00:00:00 2001
From: AndiGob <andreas.gobbbin@hotmail.de>
Date: Wed, 11 Dec 2024 13:03:47 +0100
Subject: [PATCH 4/6] landing_gear_design: -Upadet src code to run nacelle
clearance check inside of the strut length dimensioning
---
.../landing_gear_design_conf.xml | 10 ++--
.../call_functions/_04_estimatelimitations.py | 25 ++++++---
.../general/call_functions/_06_estimatecog.py | 6 +-
.../{ => sub_function}/convergencecheck.py | 0
.../sub_function/nacellegroundclearance.py | 1 -
.../{ => sub_function}/prepareexternaldata.py | 8 ++-
.../general/landinggeardesign.py | 12 +---
.../general/methodplot.py | 56 +++++++++----------
.../generatelandinggearplots.py | 38 +++++++------
9 files changed, 83 insertions(+), 73 deletions(-)
rename landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/{ => sub_function}/convergencecheck.py (100%)
rename landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/{ => sub_function}/prepareexternaldata.py (96%)
diff --git a/landing_gear_design/landing_gear_design_conf.xml b/landing_gear_design/landing_gear_design_conf.xml
index 3786d73c..8add8c37 100644
--- a/landing_gear_design/landing_gear_design_conf.xml
+++ b/landing_gear_design/landing_gear_design_conf.xml
@@ -99,25 +99,25 @@
</wing_strike_limit>
</ground_strike_limitations>
<nacelle_clearance description="Nacelle clearance according to CS25.149.">
- <value>0.55</value>
+ <value>0.45</value>
<unit>m</unit>
<lower_boundary>0.45</lower_boundary>
<upper_boundary>0.90</upper_boundary>
- <default>0.60</default>
+ <default>0.45</default>
</nacelle_clearance>
<strut_suspension description="Switch to use landing gear strut suspension systems. ('true': use, 'false': don't use">
<value>true</value>
<default>true</default>
<strut_suspension_travel>
- <value>0.65</value>
+ <value>0.60</value>
<unit>m</unit>
<lower_boundary>0.35</lower_boundary>
<upper_boundary>0.95</upper_boundary>
- <default>0.6</default>
+ <default>0.60</default>
</strut_suspension_travel>
</strut_suspension>
<landing_gear_bay_keel_beam_width description="Width of the landing gear bay keel beam.">
- <value>0.55</value>
+ <value>0.50</value>
<unit>m</unit>
<lower_boundary>0.5</lower_boundary>
<upper_boundary>1.5</upper_boundary>
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_04_estimatelimitations.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_04_estimatelimitations.py
index 7689c8d3..f74806d4 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_04_estimatelimitations.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_04_estimatelimitations.py
@@ -23,10 +23,10 @@ def estimate_limitations(dict_ac_exchange, dict_mod_config, landing_gear_descrip
convert_inch_to_meter = 0.0254
current_turn_over_angle = None
main_gear_positioning_flag = True
+ nacelle_ground_clearance_flag = False
max_outside_diameter_in_inch = float()
minimum_required_wheel_base = 0.0
main_gear_tires = landing_gear_description['main_gear_description']['main_gear_tires']
- nose_gear_tires = landing_gear_description['nose_gear_description']['nose_gear_tires']
main_gear_arrangement = landing_gear_description['main_gear_description']['main_gear_arrangement']
nose_gear_arrangement = landing_gear_description['nose_gear_description']['nose_gear_arrangement']
tail_tipping_point = landing_gear_description['tail_tipping_point']
@@ -50,7 +50,9 @@ def estimate_limitations(dict_ac_exchange, dict_mod_config, landing_gear_descrip
''' Tail strike take-off and landing limitation '''
i = 0
# while loop to iterate the landing gear strut length to avoid turn over
- while i < 1000 and not limitation_flag:
+ while i < 1000 and not limitation_flag or not nacelle_ground_clearance_flag:
+ # Reset nacelle ground clearance flag for next iteration
+ nacelle_ground_clearance_flag = False
# Estimate minimum forward main landing gear position for tail strike take-off and landing limitation
# check if strut suspension system should be used for limit estimation
# -> if true: -> add maximum strut suspension travel to vertical distance between center of gravity and ground
@@ -189,11 +191,12 @@ def estimate_limitations(dict_ac_exchange, dict_mod_config, landing_gear_descrip
if dict_ac_exchange['fuselage_type'] == 'wide_body':
main_gear_arrangement['main_landing_gear_wing_mounting_position_in_z_direction'] = -1.3
- main_gear_arrangement['main_gear_outer_strut_length'] = \
- round((landing_gear_description['lever_arms'][
- 'vertical_distance_between_ground_and_aft_center_of_gravity']
- + main_gear_arrangement['main_landing_gear_wing_mounting_position_in_z_direction'])
- - (min_tire_diameter/2 * convert_inch_to_meter), 4)
+ if 'main_gear_outer_strut_length' not in main_gear_arrangement:
+ main_gear_arrangement['main_gear_outer_strut_length'] = \
+ round((landing_gear_description['lever_arms'][
+ 'vertical_distance_between_ground_and_aft_center_of_gravity']
+ + main_gear_arrangement['main_landing_gear_wing_mounting_position_in_z_direction'])
+ - (min_tire_diameter/2 * convert_inch_to_meter), 4)
# Check nacelle ground clearance if at least one engine is exisiting.
if dict_ac_exchange['engine_z_position'] is not None:
@@ -212,6 +215,12 @@ def estimate_limitations(dict_ac_exchange, dict_mod_config, landing_gear_descrip
# Add required delta length to the length of main landing gear struts.
main_gear_arrangement['main_gear_outer_strut_length'] += max(required_main_gear_strut_delta_length)
+ # Recalculate distance between ground and fusealge center line.
+ landing_gear_description['lever_arms']['vertical_distance_between_ground_and_fuselage_center_line'] = \
+ (main_gear_arrangement['main_gear_outer_strut_length']
+ + abs(landing_gear_description['main_gear_description']['main_gear_arrangement'][
+ 'main_landing_gear_wing_mounting_position_in_z_direction'])
+ + (max_outside_diameter_in_inch/2 * convert_inch_to_meter))
landing_gear_description['landing_gear_positions']['main_gear_z_position_outer_strut'] = \
round(main_gear_arrangement['main_landing_gear_wing_mounting_position_in_z_direction'], 4)
@@ -231,7 +240,7 @@ def estimate_limitations(dict_ac_exchange, dict_mod_config, landing_gear_descrip
round(main_gear_arrangement['main_gear_outer_strut_length']
+ abs(main_gear_arrangement['main_landing_gear_wing_mounting_position_in_z_direction'])
- landing_gear_description['fuselage_parameter']['fuselage_height'] / 2
- + 0.6, 4)
+ + (landing_gear_description['fuselage_parameter']['fuselage_height'] / 2 / 5), 4)
''' estimate y-position of nose and main gear struts '''
# Check if the fuselage_width is not given in the aircraft exchange file
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_06_estimatecog.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_06_estimatecog.py
index 955ca198..e26bb48c 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_06_estimatecog.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_06_estimatecog.py
@@ -34,18 +34,18 @@ def estimate_cog(dict_ac_exchange, dict_mod_config, landing_gear_description, ru
nose_gear_cog['nose_gear_cog_global']['y'] = 0.0
# global cog in z-direction
- fuselage_reference_point_in_z_direction_key, fuselage_reference_point_in_z_direction_value = \
+ _, fuselage_reference_point_in_z_direction_value = \
next(iter(dict_ac_exchange['fuselage_reference_point_in_z_direction'].items()), (None, None))
if fuselage_reference_point_in_z_direction_value is not None:
nose_gear_cog['nose_gear_cog_global']['z'] = \
round(fuselage_reference_point_in_z_direction_value
- landing_gear_description['fuselage_parameter']['fuselage_height'] / 2
- + 0.6, 4)
+ + (landing_gear_description['fuselage_parameter']['fuselage_height'] / 2 / 5), 4)
else:
nose_gear_cog['nose_gear_cog_global']['z'] = \
round(0.0
- landing_gear_description['fuselage_parameter']['fuselage_height'] / 2
- + 0.6, 4)
+ + (landing_gear_description['fuselage_parameter']['fuselage_height'] / 2 / 5), 4)
''' estimate main gear center of gravity '''
# estimate global cog for main gear assembly
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/convergencecheck.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/convergencecheck.py
similarity index 100%
rename from landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/convergencecheck.py
rename to landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/convergencecheck.py
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/nacellegroundclearance.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/nacellegroundclearance.py
index 4140caaa..eb0e89ba 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/nacellegroundclearance.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/nacellegroundclearance.py
@@ -42,7 +42,6 @@ def nacelle_ground_clearance(dict_ac_exchange, dict_mod_config, landing_gear_des
# Multiply every second nacelle inboard postion by -1
wing_nacelle_inboard_position = [value if index % 2 == 0 else -value
for index, value in enumerate(wing_nacelle_inboard_position)]
-
# Check if the posiotn of current nacelle under investigation is below the minimum required nacelle ground clearance.
for i in range(0, len(wing_nacelle_bottom_position)):
clearance_required = abs(wing_nacelle_bottom_position[i]) + dict_mod_config['nacelle_clearance']
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/prepareexternaldata.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/prepareexternaldata.py
similarity index 96%
rename from landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/prepareexternaldata.py
rename to landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/prepareexternaldata.py
index 1815313e..65035865 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/prepareexternaldata.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/prepareexternaldata.py
@@ -17,7 +17,7 @@ def prepare_external_data(paths_and_names, routing_dict, dict_ac_exchange, dict_
"""
''' set most forward and most aftward center of gravity position for maximum take-off mass condition '''
- # TODO: this have to remove if the correct cog positions for mtom are writen!!!
+ # TODO: this have to remove if the correct cog positions for mtom are writen!!! (line 20 to 45)
dict_ac_exchange['dihedral_angle_wing'] = 4.5 # angle in degree
if dict_ac_exchange['center_of_gravity_in_x'] is not None \
and dict_ac_exchange['wing_reference_point_global_in_x'] is not None:
@@ -37,6 +37,12 @@ def prepare_external_data(paths_and_names, routing_dict, dict_ac_exchange, dict_
elif dict_ac_exchange['center_of_gravity_in_x'] is not None:
dict_ac_exchange['most_aft_center_of_gravity_in_x_direction'] = (dict_ac_exchange['center_of_gravity_in_x'] + 0.5)
dict_ac_exchange['most_forward_center_of_gravity_in_x_direction'] = (dict_ac_exchange['center_of_gravity_in_x'] - 0.5)
+
+ if dict_ac_exchange['most_aft_center_of_gravity_in_z_direction'] is not None:
+ dict_ac_exchange['most_aft_center_of_gravity_in_z_direction'] = dict_ac_exchange['center_of_gravity_in_z'] - 0.1
+
+ if dict_ac_exchange['most_forward_center_of_gravity_in_z_direction'] is not None:
+ dict_ac_exchange['most_forward_center_of_gravity_in_z_direction'] = dict_ac_exchange['center_of_gravity_in_z'] - 0.05
''' transform local position of input parameter into global positions '''
# transform wing reference points
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/landinggeardesign.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/landinggeardesign.py
index a742d7bb..ee879380 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/landinggeardesign.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/landinggeardesign.py
@@ -5,10 +5,10 @@ import math
import importlib
# Import own modules.
-from src.wing_mounted.empirical.landing_gear_design_tu_berlin.general.call_functions.convergencecheck import convergence_check # noPep8 e501
from src.wing_mounted.empirical.landing_gear_design_tu_berlin.general.plot_functions.generateacnplots import generate_acn_plots # noPep8 e501
-from src.wing_mounted.empirical.landing_gear_design_tu_berlin.general.call_functions.prepareexternaldata import prepare_external_data # noPep8 e501
from src.wing_mounted.empirical.landing_gear_design_tu_berlin.general.plot_functions.generatelandinggearplots import generate_landing_gear_plots # noPep8 e501
+from src.wing_mounted.empirical.landing_gear_design_tu_berlin.general.call_functions.sub_function.convergencecheck import convergence_check # noPep8 e501
+from src.wing_mounted.empirical.landing_gear_design_tu_berlin.general.call_functions.sub_function.prepareexternaldata import prepare_external_data # noPep8 e501
from src.wing_mounted.empirical.landing_gear_design_tu_berlin.general.aicraft_classification_number.estimateaircraftclassificationnumber import estimate_aircraft_classification_number # noPep8 e501
@@ -31,7 +31,6 @@ def landing_gear_design(paths_and_names, routing_dict, dict_ac_exchange, dict_mo
''' Initialize local parameter '''
word_to_insert_after = 'estimate'
- files_to_remove = ['prepareexternaldata.py', 'convergencecheck.py']
landing_gear_description = {'working_directory': paths_and_names['working_directory']}
''' Run landing gear design '''
@@ -55,11 +54,6 @@ def landing_gear_design(paths_and_names, routing_dict, dict_ac_exchange, dict_mo
routing_dict['module_import_name'].replace('.', '/')
+ '/general/call_functions' + '/' + entry)]
- # Remove unnecessary files from call function list.
- for file in files_to_remove:
- if file in call_function_list:
- call_function_list.remove(file)
-
call_function_list = sorted(call_function_list, key=lambda x: (int(x.split('_')[1]), x))
# initialize convergence criteria
@@ -137,6 +131,6 @@ def landing_gear_design(paths_and_names, routing_dict, dict_ac_exchange, dict_mo
landing_gear_description['current_tool_level'] = int(routing_dict['tool_level'])
# Debug print for function landing_gear_design.
- runtime_output.debug('landing_gear_design successfully executed!')
+ runtime_output.debug('The functioin "landing_gear_design.py" successfully executed!')
return landing_gear_description
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/methodplot.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/methodplot.py
index 3bcd611a..6be72ab0 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/methodplot.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/methodplot.py
@@ -175,34 +175,6 @@ def create_landing_gear_plots(paths_and_names, data_dict, plot_directory, runtim
for point in data_dict['dict_landing_gear_output']['strut_positions']:
ax.scatter(point[0], point[1], color='gray')
- # Plot engines if available.
- if 'nacelle_plot_list' in data_dict['dict_landing_gear_output']:
- theta = np.linspace(0, 2*np.pi, 100)
- i = 0
- while i < len(data_dict['dict_landing_gear_output']['nacelle_plot_list']):
- y1 = (data_dict['dict_landing_gear_output']['nacelle_plot_list'][i][0]
- + data_dict['dict_landing_gear_output']['nacelle_plot_list'][i][2] * np.cos(theta))
- z1 = (data_dict['dict_landing_gear_output']['nacelle_plot_list'][i][1]
- + data_dict['dict_landing_gear_output']['nacelle_plot_list'][i][2] * np.sin(theta))
- y2 = (data_dict['dict_landing_gear_output']['nacelle_plot_list'][i][0]
- + (data_dict['dict_landing_gear_output']['nacelle_plot_list'][i][2]
- * (1 - data_dict['dict_landing_gear_output']['nacelle_plot_list'][i][3]/100)) * np.cos(theta))
- z2 = (data_dict['dict_landing_gear_output']['nacelle_plot_list'][i][1]
- + (data_dict['dict_landing_gear_output']['nacelle_plot_list'][i][2]
- * (1 - data_dict['dict_landing_gear_output']['nacelle_plot_list'][i][3]/100)) * np.sin(theta))
- ax.plot(y1, z1, color='black')
- ax.plot(y2, z2, color='black')
- vertices = np.vstack((np.column_stack((y1, z1)),
- np.column_stack((y2[::-1], z2[::-1]))))
- polygon = Polygon(vertices, closed=True, color='gray', alpha=0.15)
- vertices_inner = np.column_stack((y2[::-1], z2[::-1]))
- fig.gca().add_patch(polygon)
- polygon_inner = Polygon(vertices_inner, closed=True, color='gray', alpha=0.05)
- fig.gca().add_patch(polygon_inner)
- ax.scatter(data_dict['dict_landing_gear_output']['nacelle_plot_list'][i][0],
- data_dict['dict_landing_gear_output']['nacelle_plot_list'][i][1], color='gray')
- i += 1
-
# Plot wing if available.
if 'wing_plot_list' in data_dict['dict_landing_gear_output']:
i = 0
@@ -250,6 +222,34 @@ def create_landing_gear_plots(paths_and_names, data_dict, plot_directory, runtim
else:
runtime_output.warning('Attention! The Use existing geometry mode is selected. '
'Clearance and limitation angle are not plotted.')
+
+ # Plot nacelle if available.
+ if 'nacelle_plot_list' in data_dict['dict_landing_gear_output']:
+ theta = np.linspace(0, 2*np.pi, 100)
+ i = 0
+ while i < len(data_dict['dict_landing_gear_output']['nacelle_plot_list']):
+ y1 = (data_dict['dict_landing_gear_output']['nacelle_plot_list'][i][0]
+ + data_dict['dict_landing_gear_output']['nacelle_plot_list'][i][2] * np.cos(theta))
+ z1 = (data_dict['dict_landing_gear_output']['nacelle_plot_list'][i][1]
+ + data_dict['dict_landing_gear_output']['nacelle_plot_list'][i][2] * np.sin(theta))
+ y2 = (data_dict['dict_landing_gear_output']['nacelle_plot_list'][i][0]
+ + (data_dict['dict_landing_gear_output']['nacelle_plot_list'][i][2]
+ * (1 - data_dict['dict_landing_gear_output']['nacelle_plot_list'][i][3]/100)) * np.cos(theta))
+ z2 = (data_dict['dict_landing_gear_output']['nacelle_plot_list'][i][1]
+ + (data_dict['dict_landing_gear_output']['nacelle_plot_list'][i][2]
+ * (1 - data_dict['dict_landing_gear_output']['nacelle_plot_list'][i][3]/100)) * np.sin(theta))
+ ax.plot(y1, z1, color='black')
+ ax.plot(y2, z2, color='black')
+ vertices = np.vstack((np.column_stack((y1, z1)),
+ np.column_stack((y2[::-1], z2[::-1]))))
+ polygon = Polygon(vertices, closed=True, color='gray', alpha=0.8)
+ vertices_inner = np.column_stack((y2[::-1], z2[::-1]))
+ fig.gca().add_patch(polygon)
+ polygon_inner = Polygon(vertices_inner, closed=True, color='gray', alpha=0.15)
+ fig.gca().add_patch(polygon_inner)
+ ax.scatter(data_dict['dict_landing_gear_output']['nacelle_plot_list'][i][0],
+ data_dict['dict_landing_gear_output']['nacelle_plot_list'][i][1], color='gray')
+ i += 1
# Remove frame
fig.gca().spines['top'].set_visible(False)
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/plot_functions/generatelandinggearplots.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/plot_functions/generatelandinggearplots.py
index 160009db..c7694e4e 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/plot_functions/generatelandinggearplots.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/plot_functions/generatelandinggearplots.py
@@ -183,24 +183,6 @@ def generate_landing_gear_plots(dict_ac_exchange, landing_gear_description, runt
round(abs(2 * landing_gear_description['landing_gear_positions']['main_gear_outer_strut_y_position']), 2)
]
- # Check if engine data are available -> if true: -> prepare plotting.
- _, nacelle_y_position_value = \
- next(iter(dict_ac_exchange['engine_y_position'].items()), (None, None))
-
- if nacelle_y_position_value is not None:
- nacelle_plot_list = []
- cleaned_nacelle_dict = {key: value for key, value in dict_ac_exchange['nacelle_section_height'].items()
- if value is not None}
- i = 0
- y_pos_list = list(dict_ac_exchange['engine_y_position'].values())
- z_pos_list = list(dict_ac_exchange['engine_z_position'].values())
- radius_list = max(list(cleaned_nacelle_dict.values()))
- for i in range(0, len(y_pos_list)):
- # List contains the following entries: [y_pos, z_pos, radius, wall_thickness_in_percent]
- nacelle_plot_list.append([y_pos_list[i], z_pos_list[i], radius_list/2, 18])
-
- dict_landing_gear_output['nacelle_plot_list'] = nacelle_plot_list
-
# Check if wing data are available -> if true: -> prepare plotting.
_, wing_section_y_position_value = \
next(iter(dict_ac_exchange['wing_chord_length_on_section'].items()), (None, None))
@@ -244,6 +226,26 @@ def generate_landing_gear_plots(dict_ac_exchange, landing_gear_description, runt
dict_landing_gear_output['wing_clearance_list'] = wing_clearance_list
else:
dict_landing_gear_output['wing_clearance_list'] = None
+
+ # Check if engine data are available -> if true: -> prepare plotting.
+ _, nacelle_y_position_value = \
+ next(iter(dict_ac_exchange['engine_y_position'].items()), (None, None))
+
+ if nacelle_y_position_value is not None:
+ nacelle_plot_list = []
+ cleaned_nacelle_dict = {key: value for key, value in dict_ac_exchange['nacelle_section_height'].items()
+ if value is not None}
+ i = 0
+ y_pos_list = list(dict_ac_exchange['engine_y_position'].values())
+ z_pos_list = list(dict_ac_exchange['engine_z_position'].values())
+ nacelle_diameter_list = max(list(cleaned_nacelle_dict.values()))
+ engine_diameter = nacelle_diameter_list - nacelle_diameter_list / 100 * 9 # 9 percent wall thickness of total nacelle diameter assumed
+ nacelle_width = round(nacelle_diameter_list - engine_diameter, 2) * 100 # nacelle wall width in cm for plotting
+ for i in range(0, len(y_pos_list)):
+ # List contains the following entries: [y_pos, z_pos, radius, wall_thickness_in_percent]
+ nacelle_plot_list.append([y_pos_list[i], z_pos_list[i], nacelle_diameter_list/2, nacelle_width])
+
+ dict_landing_gear_output['nacelle_plot_list'] = nacelle_plot_list
''' generate output data for side view of landing gear design '''
--
GitLab
From 0346d6d5ab72adfd9d3dec4f7da750b0ab8db31d Mon Sep 17 00:00:00 2001
From: AndiGob <andreas.gobbbin@hotmail.de>
Date: Wed, 11 Dec 2024 15:48:25 +0100
Subject: [PATCH 5/6] landing_gear_deisgn: - bugFix: -> correction of nacelle
clearance iteration flag from False to True
---
.../general/call_functions/_04_estimatelimitations.py | 4 ++--
.../call_functions/sub_function/nacellegroundclearance.py | 3 ++-
2 files changed, 4 insertions(+), 3 deletions(-)
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_04_estimatelimitations.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_04_estimatelimitations.py
index f74806d4..a5ba7371 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_04_estimatelimitations.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_04_estimatelimitations.py
@@ -23,7 +23,7 @@ def estimate_limitations(dict_ac_exchange, dict_mod_config, landing_gear_descrip
convert_inch_to_meter = 0.0254
current_turn_over_angle = None
main_gear_positioning_flag = True
- nacelle_ground_clearance_flag = False
+ nacelle_ground_clearance_flag = True
max_outside_diameter_in_inch = float()
minimum_required_wheel_base = 0.0
main_gear_tires = landing_gear_description['main_gear_description']['main_gear_tires']
@@ -50,7 +50,7 @@ def estimate_limitations(dict_ac_exchange, dict_mod_config, landing_gear_descrip
''' Tail strike take-off and landing limitation '''
i = 0
# while loop to iterate the landing gear strut length to avoid turn over
- while i < 1000 and not limitation_flag or not nacelle_ground_clearance_flag:
+ while i < 1000 and not limitation_flag or nacelle_ground_clearance_flag:
# Reset nacelle ground clearance flag for next iteration
nacelle_ground_clearance_flag = False
# Estimate minimum forward main landing gear position for tail strike take-off and landing limitation
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/nacellegroundclearance.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/nacellegroundclearance.py
index eb0e89ba..d8ef3a97 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/nacellegroundclearance.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/nacellegroundclearance.py
@@ -46,10 +46,11 @@ def nacelle_ground_clearance(dict_ac_exchange, dict_mod_config, landing_gear_des
for i in range(0, len(wing_nacelle_bottom_position)):
clearance_required = abs(wing_nacelle_bottom_position[i]) + dict_mod_config['nacelle_clearance']
clearance_available = landing_gear_description['lever_arms']['vertical_distance_between_ground_and_fuselage_center_line']
+ # Check if the required nachell clearance is greater than the current available clearance.
if (clearance_required > clearance_available):
nacelle_ground_clearance_flag = True
required_main_gear_strut_delta_length.append(clearance_required - clearance_available)
-
+
# debug print
runtime_output.debug('The function "nacelle_ground_clearance.py" successfully executed!')
--
GitLab
From ec5a292bb3bba2ae802d7d7f1614c19a9c57876a Mon Sep 17 00:00:00 2001
From: AndiGob <andreas.gobbbin@hotmail.de>
Date: Wed, 11 Dec 2024 15:54:08 +0100
Subject: [PATCH 6/6] landing_gear_design: - Add header to all python src files
---
landing_gear_design/main.py | 20 +++++++++++++++++++
landing_gear_design/src/datapostprocessing.py | 20 +++++++++++++++++++
landing_gear_design/src/datapreprocessing.py | 20 +++++++++++++++++++
landing_gear_design/src/readlayertext.py | 20 +++++++++++++++++++
.../estimateaircraftclassificationnumber.py | 20 +++++++++++++++++++
.../flexible_pavement/acnflexcomp.py | 20 +++++++++++++++++++
.../alpha_factor_from_curve.py | 20 +++++++++++++++++++
.../flexible_pavement/cvrg.py | 20 +++++++++++++++++++
.../initializeacnflexparameter.py | 20 +++++++++++++++++++
.../setacnflexinputparameter.py | 20 +++++++++++++++++++
.../flexible_pavement/storeflexcurvefits.py | 20 +++++++++++++++++++
.../call_functions/_00_estimatepositions.py | 20 +++++++++++++++++++
.../call_functions/_01_estimatedistances.py | 20 +++++++++++++++++++
.../call_functions/_02_estimateloads.py | 20 +++++++++++++++++++
.../call_functions/_03_estimatetires.py | 20 +++++++++++++++++++
.../call_functions/_04_estimatelimitations.py | 20 +++++++++++++++++++
.../call_functions/_05_estimatemasses.py | 20 +++++++++++++++++++
.../general/call_functions/_06_estimatecog.py | 20 +++++++++++++++++++
.../call_functions/_07_setexistinggeometry.py | 20 +++++++++++++++++++
.../sub_function/convergencecheck.py | 20 +++++++++++++++++++
.../sub_function/nacellegroundclearance.py | 20 +++++++++++++++++++
.../sub_function/prepareexternaldata.py | 20 +++++++++++++++++++
.../sub_function/wingtipclearance.py | 20 +++++++++++++++++++
.../general/landinggeardesign.py | 20 +++++++++++++++++++
.../general/methodhtmlreport.py | 20 +++++++++++++++++++
.../general/methodplot.py | 20 +++++++++++++++++++
.../general/methodtexoutput.py | 20 +++++++++++++++++++
.../general/methodxmlexport.py | 20 +++++++++++++++++++
.../plot_functions/generateacnplots.py | 20 +++++++++++++++++++
.../generatelandinggearplots.py | 20 +++++++++++++++++++
.../general/useexistinggeometry.py | 20 +++++++++++++++++++
.../kerosene/methodkerosene.py | 20 +++++++++++++++++++
.../liquid_hydrogen/methodliquidhydrogen.py | 20 +++++++++++++++++++
.../usermethoddatapreparation.py | 20 +++++++++++++++++++
34 files changed, 680 insertions(+)
diff --git a/landing_gear_design/main.py b/landing_gear_design/main.py
index e3eacb65..2deba33d 100644
--- a/landing_gear_design/main.py
+++ b/landing_gear_design/main.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
"""Calculation module main file."""
# Import standard modules.
import logging
diff --git a/landing_gear_design/src/datapostprocessing.py b/landing_gear_design/src/datapostprocessing.py
index 618a030c..45613b7e 100644
--- a/landing_gear_design/src/datapostprocessing.py
+++ b/landing_gear_design/src/datapostprocessing.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
"""Module providing functions for data postprocessing."""
# Import standard modules.
diff --git a/landing_gear_design/src/datapreprocessing.py b/landing_gear_design/src/datapreprocessing.py
index c2f9833a..de8078f0 100644
--- a/landing_gear_design/src/datapreprocessing.py
+++ b/landing_gear_design/src/datapreprocessing.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
"""Module providing functions for data preprocessing."""
# Import standard modules.
import importlib
diff --git a/landing_gear_design/src/readlayertext.py b/landing_gear_design/src/readlayertext.py
index 86d7c856..a334aa21 100644
--- a/landing_gear_design/src/readlayertext.py
+++ b/landing_gear_design/src/readlayertext.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
"""File providing functions to read layer text from aircraft XML file."""
# Import standard libraries.
import sys
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/estimateaircraftclassificationnumber.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/estimateaircraftclassificationnumber.py
index 62c3229b..27ba034d 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/estimateaircraftclassificationnumber.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/estimateaircraftclassificationnumber.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
# Import standard modules.
import os
import sys
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/flexible_pavement/acnflexcomp.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/flexible_pavement/acnflexcomp.py
index 8f8d79d2..5af142ba 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/flexible_pavement/acnflexcomp.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/flexible_pavement/acnflexcomp.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
# Import standard modules.
import math
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/flexible_pavement/alpha_factor_from_curve.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/flexible_pavement/alpha_factor_from_curve.py
index 67d1c92e..852d9d03 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/flexible_pavement/alpha_factor_from_curve.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/flexible_pavement/alpha_factor_from_curve.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
# imports for python
import math
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/flexible_pavement/cvrg.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/flexible_pavement/cvrg.py
index 8b9176a5..f2efa92a 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/flexible_pavement/cvrg.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/flexible_pavement/cvrg.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
import math
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/flexible_pavement/initializeacnflexparameter.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/flexible_pavement/initializeacnflexparameter.py
index 8162d6aa..f6a89f42 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/flexible_pavement/initializeacnflexparameter.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/flexible_pavement/initializeacnflexparameter.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
# Import own modules.
from src.wing_mounted.empirical.landing_gear_design_tu_berlin.general.aicraft_classification_number.flexible_pavement.storeflexcurvefits import store_flex_curve_fits # noPep8 e501
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/flexible_pavement/setacnflexinputparameter.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/flexible_pavement/setacnflexinputparameter.py
index 20afc060..e27d4890 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/flexible_pavement/setacnflexinputparameter.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/flexible_pavement/setacnflexinputparameter.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
def set_acn_flex_input_parameter(paths_and_names, landing_gear_description, dict_ac_exchange, dict_mod_config,
runtime_output, dict_acn_flex_parameter, dict_constants):
""" This function prepares all input parameter to estimate the aircraft classification number in accordance to
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/flexible_pavement/storeflexcurvefits.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/flexible_pavement/storeflexcurvefits.py
index 9fb0a7d0..1b6d3e62 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/flexible_pavement/storeflexcurvefits.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/aicraft_classification_number/flexible_pavement/storeflexcurvefits.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
def store_flex_curve_fits():
""" This function initialized the acn parameter in accordance to ICAO COMFAA tool.
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_00_estimatepositions.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_00_estimatepositions.py
index 18fc1f9c..f39d7af5 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_00_estimatepositions.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_00_estimatepositions.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
def estimate_positions(dict_ac_exchange, dict_mod_config, landing_gear_description, runtime_output):
""" This function estimates start values of the x-positions for nose and main landing gear in meter.
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_01_estimatedistances.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_01_estimatedistances.py
index a4902c22..33f5f5d1 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_01_estimatedistances.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_01_estimatedistances.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
# Import standard modules.
import math
import sys
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_02_estimateloads.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_02_estimateloads.py
index 62ad5496..7752d6de 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_02_estimateloads.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_02_estimateloads.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
# Import standard modules.
import sys
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_03_estimatetires.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_03_estimatetires.py
index aa59d620..2826fa3c 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_03_estimatetires.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_03_estimatetires.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
# Import standard modules.
import os
import sys
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_04_estimatelimitations.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_04_estimatelimitations.py
index a5ba7371..9fb94f4e 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_04_estimatelimitations.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_04_estimatelimitations.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
# Import standard modules.
import sys
import math
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_05_estimatemasses.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_05_estimatemasses.py
index 0ff412ff..a76079b3 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_05_estimatemasses.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_05_estimatemasses.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
def estimate_masses(dict_ac_exchange, dict_mod_config, landing_gear_description, runtime_output):
""" Hier beschreibung hin: Estimation of undercarriage masses in accordance to Torenbeek.
[ref. E. Torenbeek; 1982]
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_06_estimatecog.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_06_estimatecog.py
index e26bb48c..3753f21e 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_06_estimatecog.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_06_estimatecog.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
def estimate_cog(dict_ac_exchange, dict_mod_config, landing_gear_description, runtime_output):
""" Hier beschreibung hin: Estimation of undercarriage center of gravity.
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_07_setexistinggeometry.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_07_setexistinggeometry.py
index a892e3e5..120dad4e 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_07_setexistinggeometry.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_07_setexistinggeometry.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
# Import standard modules.
import os
import sys
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/convergencecheck.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/convergencecheck.py
index 81e28215..81410f46 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/convergencecheck.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/convergencecheck.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
def convergence_check(landing_gear_description, convergence_parameter, runtime_output, convergence_flag, i):
""" Module checks the convergence of landing gear design an prepared the log-file and console prints.
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/nacellegroundclearance.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/nacellegroundclearance.py
index d8ef3a97..54617ff0 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/nacellegroundclearance.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/nacellegroundclearance.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
def nacelle_ground_clearance(dict_ac_exchange, dict_mod_config, landing_gear_description, main_gear_arrangement, runtime_output):
""" Estimation of ancelle ground clearance in accordance to Torenbeek and CS-25.
[ref. E. Torenbeek; 1982]
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/prepareexternaldata.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/prepareexternaldata.py
index 65035865..1ed7ed68 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/prepareexternaldata.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/prepareexternaldata.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
# Import own modules.
import math
import pyaixml as aixml
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/wingtipclearance.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/wingtipclearance.py
index 4bb528a3..62628583 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/wingtipclearance.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/sub_function/wingtipclearance.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
# Import standard modules.
import math
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/landinggeardesign.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/landinggeardesign.py
index ee879380..5edb3eb9 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/landinggeardesign.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/landinggeardesign.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
# Import standard modules.
import os
import sys
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/methodhtmlreport.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/methodhtmlreport.py
index e8689c07..06752f72 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/methodhtmlreport.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/methodhtmlreport.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
"""Module providing report functionalities for current calculation method."""
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/methodplot.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/methodplot.py
index 6be72ab0..9cf6f9d3 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/methodplot.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/methodplot.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
"""Module providing plotting functionalities for current calculation method."""
# Import standard libraries.
import os
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/methodtexoutput.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/methodtexoutput.py
index 40c7f635..05e9a708 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/methodtexoutput.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/methodtexoutput.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
"""Module providing report functionalities for current calculation method."""
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/methodxmlexport.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/methodxmlexport.py
index aa317cb3..adf8c4ae 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/methodxmlexport.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/methodxmlexport.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
"""Module providing export functionalities for current calculation method."""
# Import standard libraries.
import xml.etree.ElementTree as ET
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/plot_functions/generateacnplots.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/plot_functions/generateacnplots.py
index ed6e4ddd..d5c0fb75 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/plot_functions/generateacnplots.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/plot_functions/generateacnplots.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
# Import standard modules.
import math
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/plot_functions/generatelandinggearplots.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/plot_functions/generatelandinggearplots.py
index c7694e4e..6bd72cfe 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/plot_functions/generatelandinggearplots.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/plot_functions/generatelandinggearplots.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
# Import standard modules.
import numpy as np
from matplotlib import pyplot as plt
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/useexistinggeometry.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/useexistinggeometry.py
index de7b7432..603881c6 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/useexistinggeometry.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/useexistinggeometry.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
# Import standard modules.
import sys
import xml.etree.ElementTree as ET
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/kerosene/methodkerosene.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/kerosene/methodkerosene.py
index 3ac4ac5d..98cdf452 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/kerosene/methodkerosene.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/kerosene/methodkerosene.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
"""Module providing calculation functions provided by the user."""
# Import standard modules.
import os
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/liquid_hydrogen/methodliquidhydrogen.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/liquid_hydrogen/methodliquidhydrogen.py
index 013d5da7..a6168255 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/liquid_hydrogen/methodliquidhydrogen.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/liquid_hydrogen/methodliquidhydrogen.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
"""Module providing calculation functions provided by the user."""
# Import standard modules.
import os
diff --git a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/usermethoddatapreparation.py b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/usermethoddatapreparation.py
index 43a35197..774f9358 100644
--- a/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/usermethoddatapreparation.py
+++ b/landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/usermethoddatapreparation.py
@@ -1,3 +1,23 @@
+# UNICADO - UNIversity Conceptual Aircraft Design and Optimization
+#
+# Copyright (C) 2024 UNICADO consortium
+#
+# This program is free software: you can redistribute it and/or modify
+# it under the terms of the GNU General Public License as published by
+# the Free Software Foundation, either version 3 of the License, or
+# (at your option) any later version.
+#
+# This program is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
+# GNU General Public License for more details.
+#
+# You should have received a copy of the GNU General Public License
+# along with this program. If not, see <https://www.gnu.org/licenses/>.
+#
+# Description:
+# This file is part of UNICADO.
+
"""Module providing functions for the preparation of user data."""
import pycoordinatesystemconversion as py11csc
--
GitLab