From f9c9e639c07b5c797b192161c5206c00523f249a Mon Sep 17 00:00:00 2001
From: AndiGob <andreas.gobbbin@hotmail.de>
Date: Tue, 1 Apr 2025 13:44:06 +0200
Subject: [PATCH 1/3] landing_gear_design: - fix minimum percentage of nose
gear load error for different aircraft configurations
---
.../landing_gear_design_conf.xml | 26 +-
.../general/methodplot.py | 39 +-
.../generatelandinggearplots.py | 430 +++++++++---------
.../kerosene/methodkerosene.py | 23 +-
.../liquid_hydrogen/methodliquidhydrogen.py | 25 +-
.../usermethoddatapreparation.py | 10 +
6 files changed, 318 insertions(+), 235 deletions(-)
diff --git a/landing_gear_design/landing_gear_design_conf.xml b/landing_gear_design/landing_gear_design_conf.xml
index aee8566e..6b4d725a 100644
--- a/landing_gear_design/landing_gear_design_conf.xml
+++ b/landing_gear_design/landing_gear_design_conf.xml
@@ -1,4 +1,4 @@
-<?xml version="1.0" encoding="utf-8" ?>
+<?xml version="1.0" encoding="utf-8" ?>
<module_configuration_file Name="Landing Gear Design Runtime Configuration"> <!-- Change naming according to module name -->
<control_settings description="General control settings for this tool">
<aircraft_exchange_file_name description="Specify the name of the exchange file">
@@ -124,7 +124,7 @@
<default>0.7</default>
</landing_gear_bay_keel_beam_width>
<landing_gear_mass_correction_factor>
- <value>1</value>
+ <value>1.0</value>
<unit>1</unit>
<lower_boundary>0.5</lower_boundary>
<upper_boundary>1.5</upper_boundary>
@@ -216,6 +216,28 @@
<default>5.2</default>
</specific_nose_gear_starting_x_position>
</use_specific_nose_gear_starting_x_position>
+ <use_specific_minimum_percentage_of_nose_gear_load description="Switch to select using a specific starting position in x-direction for the nose gear strut(s). ('true': use, 'false': dont use">
+ <value>false</value>
+ <default>false</default>
+ <specific_minimum_percentage_of_nose_gear_load description="Set specific starting position in x-direction for the nose gear strut(s).">
+ <value>2.5</value>
+ <unit>percent</unit>
+ <lower_boundary>2.5</lower_boundary>
+ <upper_boundary>7.5</upper_boundary>
+ <default>6.0</default>
+ </specific_minimum_percentage_of_nose_gear_load>
+ </use_specific_minimum_percentage_of_nose_gear_load>
+ <use_specific_maximum_percentage_of_nose_gear_load description="Switch to select using a specific starting position in x-direction for the nose gear strut(s). ('true': use, 'false': dont use">
+ <value>false</value>
+ <default>false</default>
+ <specific_maximum_percentage_of_nose_gear_load description="Set specific starting position in x-direction for the nose gear strut(s).">
+ <value>25.0</value>
+ <unit>percent</unit>
+ <lower_boundary>15.0</lower_boundary>
+ <upper_boundary>25.0</upper_boundary>
+ <default>20.0</default>
+ </specific_maximum_percentage_of_nose_gear_load>
+ </use_specific_maximum_percentage_of_nose_gear_load>
</nose_gear_parameter>
<main_gear_parameter description="Parameter settings for the main landing gear design.">
<minimum_number_of_main_gear_tires_per_strut description="Set the number of minimum allowed tires per one main landing gear strut.">
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 30c41d12..2dba3608 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
@@ -40,23 +40,28 @@ def method_plot(paths_and_names, routing_dict, data_dict, method_specific_output
:param logging.Logger runtime_output: Logging object used for capturing log messages in the module
:return: None
"""
- # Check path to directory for figure outputs
- project_directory = paths_and_names["project_directory"]
- plot_directory = project_directory + '/reporting/plots'
- if not os.path.isdir(plot_directory):
- os.makedirs(plot_directory)
-
- ''' visualisation of results '''
- # generate acn plot
- # call function to create the plots of acn methode
- # create_acn_plot(paths_and_names, data_dict['acn_estimation']['gross_mass_list'],
- # data_dict['acn_estimation']['aircraft_classification_number_output_list'],
- # data_dict['acn_estimation']['InputAlpha'], plot_directory)
-
- # call function to create the top and side view plots of landing gear design
- create_landing_gear_plots(paths_and_names, data_dict, plot_directory, runtime_output)
-
- runtime_output.print('Plots for landing gear design are successfully generated and saved.')
+ # Check if plot data is available otherwise skip plotting
+ if not data_dict['dict_landing_gear_output'] == {}:
+ # Check path to directory for figure outputs
+ project_directory = paths_and_names["project_directory"]
+ plot_directory = project_directory + '/reporting/plots'
+ if not os.path.isdir(plot_directory):
+ os.makedirs(plot_directory)
+
+ ''' visualisation of results '''
+ # generate acn plot
+ # call function to create the plots of acn methode
+ # create_acn_plot(paths_and_names, data_dict['acn_estimation']['gross_mass_list'],
+ # data_dict['acn_estimation']['aircraft_classification_number_output_list'],
+ # data_dict['acn_estimation']['InputAlpha'], plot_directory)
+
+ # call function to create the top and side view plots of landing gear design
+ create_landing_gear_plots(paths_and_names, data_dict, plot_directory, runtime_output)
+
+ runtime_output.print('Plots for landing gear design are successfully generated and saved.')
+ else:
+ runtime_output.print('Plots for landing gear design are not generated.')
+
return
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 a4832d23..4a9db916 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
@@ -31,246 +31,254 @@ def generate_landing_gear_plots(dict_ac_exchange, landing_gear_description, runt
:param logging.Logger runtime_output: Logging object used for capturing log messages in the module
:return: dict dict_landing_gear_output: Dictionary contains all outputs for plot generation of landing gear design
"""
- ''' initialize local parameter '''
- dict_landing_gear_output = {}
- convert_inch_to_meter = 0.0254
+ if not dict_ac_exchange['configuration_type'] == 'blended_wing_body':
+
+ ''' initialize local parameter '''
+ dict_landing_gear_output = {}
+ convert_inch_to_meter = 0.0254
- ''' generate global reference point '''
- dict_landing_gear_output['global_reference_point'] = {'x': 0.0, 'y': 0.0, 'z': 0.0},
+ ''' generate global reference point '''
+ dict_landing_gear_output['global_reference_point'] = {'x': 0.0, 'y': 0.0, 'z': 0.0},
- ''' generate output data for front view of landing gear design '''
- max_fuselage_section_upper_height = round(max(dict_ac_exchange['fuselage_section_upper_height'].values()), 4)
- max_fuselage_section_lower_height = -round(max(dict_ac_exchange['fuselage_section_lower_height'].values()), 4)
- semi_fuselage_section_width = round(max(dict_ac_exchange['fuselage_section_width'].values())/2, 4)
+ ''' generate output data for front view of landing gear design '''
+ max_fuselage_section_upper_height = round(max(dict_ac_exchange['fuselage_section_upper_height'].values()), 4)
+ max_fuselage_section_lower_height = -round(max(dict_ac_exchange['fuselage_section_lower_height'].values()), 4)
+ semi_fuselage_section_width = round(max(dict_ac_exchange['fuselage_section_width'].values())/2, 4)
- # Compute the value of y for the upper and lower boundaries of the hyperellipse
- dict_landing_gear_output['width_cross_section_points'] = np.linspace(-semi_fuselage_section_width,
- semi_fuselage_section_width,
- 500)
- dict_landing_gear_output['upper_cross_section_points'] = \
- (max_fuselage_section_upper_height * np.sqrt(1 - (pow(dict_landing_gear_output['width_cross_section_points'], 2)
- / pow(semi_fuselage_section_width, 2))))
- dict_landing_gear_output['lower_cross_section_points'] = \
- (max_fuselage_section_lower_height * np.sqrt(1 - (pow(dict_landing_gear_output['width_cross_section_points'], 2)
- / pow(semi_fuselage_section_width, 2))))
+ # Compute the value of y for the upper and lower boundaries of the hyperellipse
+ dict_landing_gear_output['width_cross_section_points'] = np.linspace(-semi_fuselage_section_width,
+ semi_fuselage_section_width,
+ 500)
+ dict_landing_gear_output['upper_cross_section_points'] = \
+ (max_fuselage_section_upper_height * np.sqrt(1 - (pow(dict_landing_gear_output['width_cross_section_points'], 2)
+ / pow(semi_fuselage_section_width, 2))))
+ dict_landing_gear_output['lower_cross_section_points'] = \
+ (max_fuselage_section_lower_height * np.sqrt(1 - (pow(dict_landing_gear_output['width_cross_section_points'], 2)
+ / pow(semi_fuselage_section_width, 2))))
- # Generate a list of lists of all tires are visible in the front view.
- tire_plot_list = []
- strut_positions = []
+ # Generate a list of lists of all tires are visible in the front view.
+ tire_plot_list = []
+ strut_positions = []
- # Add nose gear tires to tire plot list.
- if landing_gear_description['nose_gear_description']['nose_gear_arrangement']['number_of_nose_gear_struts'] == 1:
+ # Add nose gear tires to tire plot list.
+ if landing_gear_description['nose_gear_description']['nose_gear_arrangement']['number_of_nose_gear_struts'] == 1:
+ max_section_width = float(next((value['max_section_width_in_inch'] for value in
+ landing_gear_description['nose_gear_description'][
+ 'nose_gear_tires'].values()
+ if 'max_section_width_in_inch' in value), None))
+ max_tire_diameter = float(next((value['max_outside_diameter_in_inch'] for value in
+ landing_gear_description['nose_gear_description'][
+ 'nose_gear_tires'].values()
+ if 'max_outside_diameter_in_inch' in value), None))
+ i = 0
+ while i < landing_gear_description['nose_gear_description']['nose_gear_arrangement']['number_of_nose_gear_tires_per_strut']: # noPep8 e501
+ tire_plot_list.append(
+ [round(landing_gear_description['landing_gear_positions']['nose_gear_strut_y_position']
+ + landing_gear_description['landing_gear_cog']['nose_gear_cog'][
+ 'tire_positions_per_strut']['y'][i]
+ - (max_section_width / 2 * convert_inch_to_meter), 4),
+ round(landing_gear_description['landing_gear_positions']['nose_gear_z_position']
+ + landing_gear_description['landing_gear_cog']['nose_gear_cog'][
+ 'tire_positions_per_strut']['z'][i]
+ - (max_tire_diameter / 2 * convert_inch_to_meter), 4),
+ max_section_width * convert_inch_to_meter,
+ max_tire_diameter * convert_inch_to_meter])
+ i += 1
+ strut_positions.append([landing_gear_description['landing_gear_positions']['nose_gear_strut_y_position'],
+ landing_gear_description['landing_gear_positions']['nose_gear_z_position']])
+ strut_positions.append([landing_gear_description['landing_gear_positions']['nose_gear_strut_y_position'],
+ landing_gear_description['landing_gear_positions']['nose_gear_z_position']
+ - landing_gear_description['nose_gear_description']['nose_gear_arrangement'][
+ 'nose_gear_strut_length']])
+
+ # Add main gear tires to tire plot list.
max_section_width = float(next((value['max_section_width_in_inch'] for value in
- landing_gear_description['nose_gear_description'][
- 'nose_gear_tires'].values()
+ landing_gear_description['main_gear_description'][
+ 'main_gear_tires'].values()
if 'max_section_width_in_inch' in value), None))
max_tire_diameter = float(next((value['max_outside_diameter_in_inch'] for value in
- landing_gear_description['nose_gear_description'][
- 'nose_gear_tires'].values()
+ landing_gear_description['main_gear_description'][
+ 'main_gear_tires'].values()
if 'max_outside_diameter_in_inch' in value), None))
i = 0
- while i < landing_gear_description['nose_gear_description']['nose_gear_arrangement']['number_of_nose_gear_tires_per_strut']: # noPep8 e501
- tire_plot_list.append(
- [round(landing_gear_description['landing_gear_positions']['nose_gear_strut_y_position']
- + landing_gear_description['landing_gear_cog']['nose_gear_cog'][
- 'tire_positions_per_strut']['y'][i]
- - (max_section_width / 2 * convert_inch_to_meter), 4),
- round(landing_gear_description['landing_gear_positions']['nose_gear_z_position']
- + landing_gear_description['landing_gear_cog']['nose_gear_cog'][
- 'tire_positions_per_strut']['z'][i]
- - (max_tire_diameter / 2 * convert_inch_to_meter), 4),
- max_section_width * convert_inch_to_meter,
- max_tire_diameter * convert_inch_to_meter])
- i += 1
- strut_positions.append([landing_gear_description['landing_gear_positions']['nose_gear_strut_y_position'],
- landing_gear_description['landing_gear_positions']['nose_gear_z_position']])
- strut_positions.append([landing_gear_description['landing_gear_positions']['nose_gear_strut_y_position'],
- landing_gear_description['landing_gear_positions']['nose_gear_z_position']
- - landing_gear_description['nose_gear_description']['nose_gear_arrangement'][
- 'nose_gear_strut_length']])
-
- # Add main gear tires to tire plot list.
- max_section_width = float(next((value['max_section_width_in_inch'] for value in
- landing_gear_description['main_gear_description'][
- 'main_gear_tires'].values()
- if 'max_section_width_in_inch' in value), None))
- max_tire_diameter = float(next((value['max_outside_diameter_in_inch'] for value in
- landing_gear_description['main_gear_description'][
- 'main_gear_tires'].values()
- if 'max_outside_diameter_in_inch' in value), None))
- i = 0
- while i < landing_gear_description['main_gear_description'][
- 'main_gear_arrangement']['number_of_main_gear_tires_per_outer_strut'] and i < 2:
- tire_plot_list.append(
- [round(landing_gear_description['landing_gear_positions']['main_gear_outer_strut_y_position']
- + landing_gear_description['landing_gear_cog']['main_gear_cog'][
- 'tire_positions_per_outer_strut']['y'][i]
- - (max_section_width / 2 * convert_inch_to_meter), 4),
- round(landing_gear_description['landing_gear_positions']['main_gear_z_position_outer_strut']
- + landing_gear_description['landing_gear_cog']['main_gear_cog'][
- 'tire_positions_per_outer_strut']['z'][i]
- - (max_tire_diameter / 2 * convert_inch_to_meter), 4),
- max_section_width * convert_inch_to_meter,
- max_tire_diameter * convert_inch_to_meter])
- i += 1
- strut_positions.append([landing_gear_description['landing_gear_positions']['main_gear_outer_strut_y_position'],
- landing_gear_description['landing_gear_positions']['main_gear_z_position_outer_strut']])
- strut_positions.append([landing_gear_description['landing_gear_positions']['main_gear_outer_strut_y_position'],
- landing_gear_description['landing_gear_positions']['main_gear_z_position_outer_strut']
- - landing_gear_description['main_gear_description']['main_gear_arrangement'][
- 'main_gear_outer_strut_length']])
- strut_positions.append([-landing_gear_description['landing_gear_positions']['main_gear_outer_strut_y_position'],
- landing_gear_description['landing_gear_positions']['main_gear_z_position_outer_strut']])
- strut_positions.append([-landing_gear_description['landing_gear_positions']['main_gear_outer_strut_y_position'],
- landing_gear_description['landing_gear_positions']['main_gear_z_position_outer_strut']
- - landing_gear_description['main_gear_description']['main_gear_arrangement'][
- 'main_gear_outer_strut_length']])
-
- tire_plot_list.append([-tire_plot_list[-1][0] - tire_plot_list[-1][2],
- tire_plot_list[-1][1],
- tire_plot_list[-1][2],
- tire_plot_list[-1][3]
- ])
- if landing_gear_description['main_gear_description']['main_gear_arrangement'][
- 'number_of_main_gear_tires_per_outer_strut'] > 1:
- tire_plot_list.append([-tire_plot_list[-3][0] - tire_plot_list[-3][2],
- tire_plot_list[-3][1],
- tire_plot_list[-3][2],
- tire_plot_list[-3][3]
- ])
-
- if 'number_of_main_gear_inner_struts' in landing_gear_description['main_gear_description']['main_gear_arrangement']:
- i = 0
while i < landing_gear_description['main_gear_description'][
- 'main_gear_arrangement']['number_of_main_gear_tires_per_inner_strut'] and i < 2:
+ 'main_gear_arrangement']['number_of_main_gear_tires_per_outer_strut'] and i < 2:
tire_plot_list.append(
- [round(landing_gear_description['landing_gear_positions']['main_gear_inner_strut_y_position']
- + landing_gear_description['landing_gear_cog']['main_gear_cog'][
- 'tire_positions_per_inner_strut']['y'][i]
- - (max_section_width / 2 * convert_inch_to_meter), 4),
- round(landing_gear_description['landing_gear_positions']['main_gear_z_position_inner_strut']
- + landing_gear_description['landing_gear_cog']['main_gear_cog'][
- 'tire_positions_per_inner_strut']['z'][i]
- - (max_tire_diameter / 2 * convert_inch_to_meter), 4),
- max_section_width * convert_inch_to_meter,
- max_tire_diameter * convert_inch_to_meter])
+ [round(landing_gear_description['landing_gear_positions']['main_gear_outer_strut_y_position']
+ + landing_gear_description['landing_gear_cog']['main_gear_cog'][
+ 'tire_positions_per_outer_strut']['y'][i]
+ - (max_section_width / 2 * convert_inch_to_meter), 4),
+ round(landing_gear_description['landing_gear_positions']['main_gear_z_position_outer_strut']
+ + landing_gear_description['landing_gear_cog']['main_gear_cog'][
+ 'tire_positions_per_outer_strut']['z'][i]
+ - (max_tire_diameter / 2 * convert_inch_to_meter), 4),
+ max_section_width * convert_inch_to_meter,
+ max_tire_diameter * convert_inch_to_meter])
i += 1
- strut_positions.append([landing_gear_description['landing_gear_positions']['main_gear_inner_strut_y_position'],
- landing_gear_description['landing_gear_positions']['main_gear_z_position_inner_strut']])
- strut_positions.append([landing_gear_description['landing_gear_positions']['main_gear_inner_strut_y_position'],
- landing_gear_description['landing_gear_positions']['main_gear_z_position_inner_strut']
+ strut_positions.append([landing_gear_description['landing_gear_positions']['main_gear_outer_strut_y_position'],
+ landing_gear_description['landing_gear_positions']['main_gear_z_position_outer_strut']])
+ strut_positions.append([landing_gear_description['landing_gear_positions']['main_gear_outer_strut_y_position'],
+ landing_gear_description['landing_gear_positions']['main_gear_z_position_outer_strut']
+ - landing_gear_description['main_gear_description']['main_gear_arrangement'][
+ 'main_gear_outer_strut_length']])
+ strut_positions.append([-landing_gear_description['landing_gear_positions']['main_gear_outer_strut_y_position'],
+ landing_gear_description['landing_gear_positions']['main_gear_z_position_outer_strut']])
+ strut_positions.append([-landing_gear_description['landing_gear_positions']['main_gear_outer_strut_y_position'],
+ landing_gear_description['landing_gear_positions']['main_gear_z_position_outer_strut']
- landing_gear_description['main_gear_description']['main_gear_arrangement'][
- 'main_gear_inner_strut_length']])
+ 'main_gear_outer_strut_length']])
+ tire_plot_list.append([-tire_plot_list[-1][0] - tire_plot_list[-1][2],
+ tire_plot_list[-1][1],
+ tire_plot_list[-1][2],
+ tire_plot_list[-1][3]
+ ])
if landing_gear_description['main_gear_description']['main_gear_arrangement'][
- 'number_of_main_gear_inner_struts'] > 1:
- tire_plot_list.append([-tire_plot_list[-1][0] - tire_plot_list[-1][2],
- tire_plot_list[-1][1],
- tire_plot_list[-1][2],
- tire_plot_list[-1][3]
- ])
- strut_positions.append(
- [-landing_gear_description['landing_gear_positions']['main_gear_inner_strut_y_position'],
- landing_gear_description['landing_gear_positions']['main_gear_z_position_inner_strut']])
- strut_positions.append(
- [-landing_gear_description['landing_gear_positions']['main_gear_inner_strut_y_position'],
- landing_gear_description['landing_gear_positions']['main_gear_z_position_inner_strut']
- - landing_gear_description['main_gear_description']['main_gear_arrangement'][
- 'main_gear_inner_strut_length']])
+ 'number_of_main_gear_tires_per_outer_strut'] > 1:
+ tire_plot_list.append([-tire_plot_list[-3][0] - tire_plot_list[-3][2],
+ tire_plot_list[-3][1],
+ tire_plot_list[-3][2],
+ tire_plot_list[-3][3]
+ ])
+
+ if 'number_of_main_gear_inner_struts' in landing_gear_description['main_gear_description']['main_gear_arrangement']:
+ i = 0
+ while i < landing_gear_description['main_gear_description'][
+ 'main_gear_arrangement']['number_of_main_gear_tires_per_inner_strut'] and i < 2:
+ tire_plot_list.append(
+ [round(landing_gear_description['landing_gear_positions']['main_gear_inner_strut_y_position']
+ + landing_gear_description['landing_gear_cog']['main_gear_cog'][
+ 'tire_positions_per_inner_strut']['y'][i]
+ - (max_section_width / 2 * convert_inch_to_meter), 4),
+ round(landing_gear_description['landing_gear_positions']['main_gear_z_position_inner_strut']
+ + landing_gear_description['landing_gear_cog']['main_gear_cog'][
+ 'tire_positions_per_inner_strut']['z'][i]
+ - (max_tire_diameter / 2 * convert_inch_to_meter), 4),
+ max_section_width * convert_inch_to_meter,
+ max_tire_diameter * convert_inch_to_meter])
+ i += 1
+ strut_positions.append([landing_gear_description['landing_gear_positions']['main_gear_inner_strut_y_position'],
+ landing_gear_description['landing_gear_positions']['main_gear_z_position_inner_strut']])
+ strut_positions.append([landing_gear_description['landing_gear_positions']['main_gear_inner_strut_y_position'],
+ landing_gear_description['landing_gear_positions']['main_gear_z_position_inner_strut']
+ - landing_gear_description['main_gear_description']['main_gear_arrangement'][
+ 'main_gear_inner_strut_length']])
if landing_gear_description['main_gear_description']['main_gear_arrangement'][
- 'number_of_main_gear_tires_per_inner_strut'] > 1:
- tire_plot_list.append([-tire_plot_list[-3][0] - tire_plot_list[-3][2],
- tire_plot_list[-3][1],
- tire_plot_list[-3][2],
- tire_plot_list[-3][3]
- ])
+ 'number_of_main_gear_inner_struts'] > 1:
+ tire_plot_list.append([-tire_plot_list[-1][0] - tire_plot_list[-1][2],
+ tire_plot_list[-1][1],
+ tire_plot_list[-1][2],
+ tire_plot_list[-1][3]
+ ])
+ strut_positions.append(
+ [-landing_gear_description['landing_gear_positions']['main_gear_inner_strut_y_position'],
+ landing_gear_description['landing_gear_positions']['main_gear_z_position_inner_strut']])
+ strut_positions.append(
+ [-landing_gear_description['landing_gear_positions']['main_gear_inner_strut_y_position'],
+ landing_gear_description['landing_gear_positions']['main_gear_z_position_inner_strut']
+ - landing_gear_description['main_gear_description']['main_gear_arrangement'][
+ 'main_gear_inner_strut_length']])
- dict_landing_gear_output['tire_plot_list'] = tire_plot_list
- dict_landing_gear_output['strut_positions'] = strut_positions
+ if landing_gear_description['main_gear_description']['main_gear_arrangement'][
+ 'number_of_main_gear_tires_per_inner_strut'] > 1:
+ tire_plot_list.append([-tire_plot_list[-3][0] - tire_plot_list[-3][2],
+ tire_plot_list[-3][1],
+ tire_plot_list[-3][2],
+ tire_plot_list[-3][3]
+ ])
- dict_landing_gear_output['landing_gear_track'] = \
- [(landing_gear_description['landing_gear_positions']['main_gear_outer_strut_y_position'],
- landing_gear_description['landing_gear_positions']['main_gear_z_position_outer_strut']
- - landing_gear_description['main_gear_description']['main_gear_arrangement']['main_gear_outer_strut_length']
- - 2/3 * (max_tire_diameter * convert_inch_to_meter)
- ),
- (-landing_gear_description['landing_gear_positions']['main_gear_outer_strut_y_position'],
- landing_gear_description['landing_gear_positions']['main_gear_z_position_outer_strut']
- - landing_gear_description['main_gear_description']['main_gear_arrangement']['main_gear_outer_strut_length']
- - 2/3 * (max_tire_diameter * convert_inch_to_meter)
- ),
- round(abs(2 * landing_gear_description['landing_gear_positions']['main_gear_outer_strut_y_position']), 2)
- ]
+ dict_landing_gear_output['tire_plot_list'] = tire_plot_list
+ dict_landing_gear_output['strut_positions'] = strut_positions
- # 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))
- if wing_section_y_position_value is not None:
- section_profile_thickness = 0.115
- wing_plot_list = []
- y_pos_list = list(dict_ac_exchange['wing_section_position_in_y'].values())
- z_pos_list = list(dict_ac_exchange['wing_section_position_in_z'].values())
- chord_length = list(dict_ac_exchange['wing_chord_length_on_section'].values())
- i = 0
- while i < len(dict_ac_exchange['wing_chord_length_on_section']):
- section_height = round(chord_length[i] * section_profile_thickness, 4)
- y = round(y_pos_list[i] + dict_ac_exchange['wing_reference_point_global_in_y'], 4)
- z1 = round(z_pos_list[i] + 1/2 * section_height, 4)
- z2 = round(z_pos_list[i] - 1/2 * section_height, 4)
- wing_plot_list.append([y, z1, z2])
- if dict_ac_exchange['wing_symmetry']:
- wing_plot_list.append([-y, z1, z2])
- i += 1
+ dict_landing_gear_output['landing_gear_track'] = \
+ [(landing_gear_description['landing_gear_positions']['main_gear_outer_strut_y_position'],
+ landing_gear_description['landing_gear_positions']['main_gear_z_position_outer_strut']
+ - landing_gear_description['main_gear_description']['main_gear_arrangement']['main_gear_outer_strut_length']
+ - 2/3 * (max_tire_diameter * convert_inch_to_meter)
+ ),
+ (-landing_gear_description['landing_gear_positions']['main_gear_outer_strut_y_position'],
+ landing_gear_description['landing_gear_positions']['main_gear_z_position_outer_strut']
+ - landing_gear_description['main_gear_description']['main_gear_arrangement']['main_gear_outer_strut_length']
+ - 2/3 * (max_tire_diameter * convert_inch_to_meter)
+ ),
+ round(abs(2 * landing_gear_description['landing_gear_positions']['main_gear_outer_strut_y_position']), 2)
+ ]
- dict_landing_gear_output['wing_plot_list'] = sorted(wing_plot_list, key=lambda x: x[0])
+ # 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))
+ if wing_section_y_position_value is not None:
+ section_profile_thickness = 0.115
+ wing_plot_list = []
+ y_pos_list = list(dict_ac_exchange['wing_section_position_in_y'].values())
+ z_pos_list = list(dict_ac_exchange['wing_section_position_in_z'].values())
+ chord_length = list(dict_ac_exchange['wing_chord_length_on_section'].values())
+ i = 0
+ while i < len(dict_ac_exchange['wing_chord_length_on_section']):
+ section_height = round(chord_length[i] * section_profile_thickness, 4)
+ y = round(y_pos_list[i] + dict_ac_exchange['wing_reference_point_global_in_y'], 4)
+ z1 = round(z_pos_list[i] + 1/2 * section_height, 4)
+ z2 = round(z_pos_list[i] - 1/2 * section_height, 4)
+ wing_plot_list.append([y, z1, z2])
+ if dict_ac_exchange['wing_symmetry']:
+ wing_plot_list.append([-y, z1, z2])
+ i += 1
- # Generate data for wing clearance plot
- if 'wing_tip_clearance_angles' in landing_gear_description['landing_gear_limitations']:
- wing_clearance_list = [
- [round(landing_gear_description['landing_gear_positions']['main_gear_outer_strut_y_position']
- + abs(landing_gear_description['landing_gear_cog']['main_gear_cog'][
- 'tire_positions_per_outer_strut']['y'][0])
- + (max_section_width / 2 * convert_inch_to_meter), 4),
- round(landing_gear_description['landing_gear_positions']['main_gear_z_position_outer_strut']
- + landing_gear_description['landing_gear_cog']['main_gear_cog'][
- 'tire_positions_per_outer_strut']['z'][0]
- - (max_tire_diameter / 2 * convert_inch_to_meter), 4)],
- [y_pos_list[-1],
- round(landing_gear_description['landing_gear_positions']['main_gear_z_position_outer_strut']
- + landing_gear_description['landing_gear_cog']['main_gear_cog'][
- 'tire_positions_per_outer_strut']['z'][0]
- - (max_tire_diameter / 2 * convert_inch_to_meter), 4)],
- [round(landing_gear_description['landing_gear_limitations']['wing_tip_clearance_angles'], 2)]]
+ dict_landing_gear_output['wing_plot_list'] = sorted(wing_plot_list, key=lambda x: x[0])
- 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))
+ # Generate data for wing clearance plot
+ if 'wing_tip_clearance_angles' in landing_gear_description['landing_gear_limitations']:
+ wing_clearance_list = [
+ [round(landing_gear_description['landing_gear_positions']['main_gear_outer_strut_y_position']
+ + abs(landing_gear_description['landing_gear_cog']['main_gear_cog'][
+ 'tire_positions_per_outer_strut']['y'][0])
+ + (max_section_width / 2 * convert_inch_to_meter), 4),
+ round(landing_gear_description['landing_gear_positions']['main_gear_z_position_outer_strut']
+ + landing_gear_description['landing_gear_cog']['main_gear_cog'][
+ 'tire_positions_per_outer_strut']['z'][0]
+ - (max_tire_diameter / 2 * convert_inch_to_meter), 4)],
+ [y_pos_list[-1],
+ round(landing_gear_description['landing_gear_positions']['main_gear_z_position_outer_strut']
+ + landing_gear_description['landing_gear_cog']['main_gear_cog'][
+ 'tire_positions_per_outer_strut']['z'][0]
+ - (max_tire_diameter / 2 * convert_inch_to_meter), 4)],
+ [round(landing_gear_description['landing_gear_limitations']['wing_tip_clearance_angles'], 2)]]
- 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['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))
- dict_landing_gear_output['nacelle_plot_list'] = nacelle_plot_list
+ 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])
- ''' generate output data for side view of landing gear design '''
+ dict_landing_gear_output['nacelle_plot_list'] = nacelle_plot_list
- ''' generate output data for top view of landing gear design '''
+ ''' generate output data for side view of landing gear design '''
+ ''' generate output data for top view of landing gear design '''
+
+ # Else condition: -> current aircraft configuration is a blended wing body -> plotting currently not implemented
+ else:
+ dict_landing_gear_output = {}
+ runtime_output.warning('Attention! The current aircraft configuration is a blended wing body. \n'
+ ' Plotting for this configuration is currently not implemented!')
+
# debug print
runtime_output.debug('generate_landing_gear_plots successfully executed!')
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 5cf30390..eb21ba2d 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
@@ -59,8 +59,27 @@ def method_kerosene(paths_and_names, routing_dict, dict_ac_exchange, dict_mod_co
dict_ac_exchange['lift_coefficient_lift_off'] = 2.1 # dimensionless
dict_ac_exchange['lift_curve_slope_take_off'] = 4.5 # 1/radians
dict_ac_exchange['maximum_take_off_stall_speed'] = 75 # m/s
- dict_mod_config['minimum_percentage_nose_gear_load'] = 6.0
- dict_mod_config['maximum_percentage_nose_gear_load'] = 20.0
+
+ # Set minimum and maximum percentage of nose gear load depending on the aircraft configuration
+ if any(value == 'wing' for value in dict_ac_exchange['propulsor_mounting_position'].values()):
+ if dict_ac_exchange['fuselage_type'] == 'single_aisle' and dict_ac_exchange['configuration_type'] == 'tube_and_wing':
+ dict_mod_config['minimum_percentage_nose_gear_load'] = 6.0
+ dict_mod_config['maximum_percentage_nose_gear_load'] = 20.0
+
+ elif dict_ac_exchange['fuselage_type'] == 'wide_body' or dict_ac_exchange['configuration_type'] == 'blended_wing_body':
+ dict_mod_config['minimum_percentage_nose_gear_load'] = 4.0
+ dict_mod_config['maximum_percentage_nose_gear_load'] = 21.5
+ else:
+ dict_mod_config['minimum_percentage_nose_gear_load'] = 3.5
+ dict_mod_config['maximum_percentage_nose_gear_load'] = 23.0
+
+ # Check if a specific minimum percentage given by th module configuration file should be used
+ if dict_mod_config['use_specific_minimum_percentage_of_nose_gear_load']:
+ dict_mod_config['minimum_percentage_nose_gear_load'] = dict_mod_config['specific_minimum_percentage_of_nose_gear_load']
+
+ # Check if a specific maximum percentage given by th module configuration file should be used
+ if dict_mod_config['use_specific_maximum_percentage_of_nose_gear_load']:
+ dict_mod_config['maximum_percentage_nose_gear_load'] = dict_mod_config['specific_maximum_percentage_of_nose_gear_load']
# check which sizing mode is selected -> if no valid mode is selected -> raise an error and abort program
if dict_mod_config['program_mode'] == 'mode_0' or dict_mod_config['program_mode'] == 'mode_1':
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 dec22be1..54c9488b 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
@@ -60,15 +60,34 @@ def method_liquid_hydrogen(paths_and_names, routing_dict, dict_ac_exchange, dict
dict_ac_exchange['lift_coefficient_lift_off'] = 2.1 # dimensionless
dict_ac_exchange['lift_curve_slope_take_off'] = 4.5 # 1/radians
dict_ac_exchange['maximum_take_off_stall_speed'] = 75 # m/s
- dict_mod_config['minimum_percentage_nose_gear_load'] = 4.0
- dict_mod_config['maximum_percentage_nose_gear_load'] = 20.0
+
+ # Set minimum and maximum percentage of nose gear load depending on the aircraft configuration
+ if any(value == 'wing' for value in dict_ac_exchange['propulsor_mounting_position'].values()):
+ if dict_ac_exchange['fuselage_type'] == 'single_aisle' and dict_ac_exchange['configuration_type'] == 'tube_and_wing':
+ dict_mod_config['minimum_percentage_nose_gear_load'] = 4.0
+ dict_mod_config['maximum_percentage_nose_gear_load'] = 20.0
+
+ elif dict_ac_exchange['fuselage_type'] == 'wide_body' or dict_ac_exchange['configuration_type'] == 'blended_wing_body':
+ dict_mod_config['minimum_percentage_nose_gear_load'] = 3.0
+ dict_mod_config['maximum_percentage_nose_gear_load'] = 22.0
+ else:
+ dict_mod_config['minimum_percentage_nose_gear_load'] = 2.5
+ dict_mod_config['maximum_percentage_nose_gear_load'] = 25.0
+
+ # Check if a specific minimum percentage given by th module configuration file should be used
+ if dict_mod_config['use_specific_minimum_percentage_of_nose_gear_load']:
+ dict_mod_config['minimum_percentage_nose_gear_load'] = dict_mod_config['specific_minimum_percentage_of_nose_gear_load']
+
+ # Check if a specific maximum percentage given by th module configuration file should be used
+ if dict_mod_config['use_specific_maximum_percentage_of_nose_gear_load']:
+ dict_mod_config['maximum_percentage_nose_gear_load'] = dict_mod_config['specific_maximum_percentage_of_nose_gear_load']
# check which sizing mode is selected -> if no valid mode is selected -> raise an error and abort program
if dict_mod_config['program_mode'] == 'mode_0' or dict_mod_config['program_mode'] == 'mode_1':
# check if sizing mode "mode_0" is selected -> if true: -> perform landing gear design estimation
if dict_mod_config['program_mode'] == 'mode_0':
liquid_hydrogen_output_dict = landing_gear_design(paths_and_names, routing_dict, dict_ac_exchange,
- dict_mod_config, runtime_output)
+ dict_mod_config, runtime_output)
# Check if sizing mode "mode_1" is selected
# -> if true: -> perform retrofit landing gear design from existing geometry
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 ec5acbf8..addac59d 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
@@ -54,6 +54,8 @@ def user_method_data_input_preparation(routing_dict):
['./analysis/masses_cg_inertia/design_mass/mass_properties/center_of_gravity/y', float],
'center_of_gravity_in_z':
['./analysis/masses_cg_inertia/design_mass/mass_properties/center_of_gravity/z', float],
+ 'configuration_type':
+ ['./requirements_and_specifications/design_specification/configuration/configuration_type', str],
'fuselage_type':
['./requirements_and_specifications/design_specification/configuration/fuselage_definition/fuselage_type', str], # noPep8 e501
'fuselage_reference_point_in_x_direction':
@@ -222,6 +224,14 @@ def user_method_data_input_preparation(routing_dict):
[tmp_specific + '/nose_gear_parameter/use_specific_nose_gear_starting_x_position', bool],
'specific_nose_gear_starting_x_position':
[tmp_specific + '/nose_gear_parameter/use_specific_nose_gear_starting_x_position/specific_nose_gear_starting_x_position', float], # noPep8 e501
+ 'use_specific_minimum_percentage_of_nose_gear_load':
+ [tmp_specific + '/nose_gear_parameter/use_specific_minimum_percentage_of_nose_gear_load', bool],
+ 'specific_minimum_percentage_of_nose_gear_load':
+ [tmp_specific + '/nose_gear_parameter/use_specific_minimum_percentage_of_nose_gear_load/specific_minimum_percentage_of_nose_gear_load', float], # noPep8 e501
+ 'use_specific_maximum_percentage_of_nose_gear_load':
+ [tmp_specific + '/nose_gear_parameter/use_specific_maximum_percentage_of_nose_gear_load', bool],
+ 'specific_maximum_percentage_of_nose_gear_load':
+ [tmp_specific + '/nose_gear_parameter/use_specific_maximum_percentage_of_nose_gear_load/specific_maximum_percentage_of_nose_gear_load', float],
'minimum_number_of_main_gear_tires_per_strut':
[tmp_specific + '/main_gear_parameter/minimum_number_of_main_gear_tires_per_strut', int],
'dynamic_change_of_number_of_main_gear_struts':
--
GitLab
From 33cd5e75b31a258d0e53899b2b20870d52586d5a Mon Sep 17 00:00:00 2001
From: AndiGob <andreas.gobbbin@hotmail.de>
Date: Tue, 1 Apr 2025 14:47:51 +0200
Subject: [PATCH 2/3] landing_gear_design: - fix to skipp nacelle ground
clearance check if no engine is mounted to the aircarft
---
.../sub_function/nacellegroundclearance.py | 58 +++++++++++--------
1 file changed, 34 insertions(+), 24 deletions(-)
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 ea5ab4b1..04ce6563 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
@@ -46,31 +46,41 @@ def nacelle_ground_clearance(dict_ac_exchange, dict_mod_config, landing_gear_des
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 _, 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
+ # Check if at least one engine and nacelle are mounted to the aircraft
+ # -> if true: -> estimaet nacelle ground clearance
+ if len(nacelle_y_position) > 0:
+ # Check if the current propulsor is mounted to the wing
+ # -> if true: -> prepare wing nacelle paramter for ground clearance check
+ 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']
+ # 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)
- # 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']
- # 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)
-
+ # Else condition: No engine is mounted to the aircraft -> print warning and skip nacelle ground clearance check
+ else:
+ nacelle_ground_clearance_flag = False
+ required_main_gear_strut_delta_length = 0
+ runtime_output.warning('Attention! There are currently no engines mounted on the aircraft. '
+ 'Ground clearance check of the nacelle skipped!')
+
# debug print
runtime_output.debug('The function "nacelle_ground_clearance.py" successfully executed!')
--
GitLab
From 872fead1a021d7c05721a03a4233030ef21dbbc2 Mon Sep 17 00:00:00 2001
From: AndiGob <andreas.gobbbin@hotmail.de>
Date: Tue, 1 Apr 2025 15:20:53 +0200
Subject: [PATCH 3/3] =?UTF-8?q?landing=5Fgear=5Fdesign:=20-=20update=20des?=
=?UTF-8?q?cription=20of=20module=20configuration=20file=20regarding=20rev?=
=?UTF-8?q?iewer=20comments=20of=20F.=20Sch=C3=BCltke?=
MIME-Version: 1.0
Content-Type: text/plain; charset=UTF-8
Content-Transfer-Encoding: 8bit
---
landing_gear_design/landing_gear_design_conf.xml | 12 ++++++------
1 file changed, 6 insertions(+), 6 deletions(-)
diff --git a/landing_gear_design/landing_gear_design_conf.xml b/landing_gear_design/landing_gear_design_conf.xml
index 6b4d725a..113fe8d8 100644
--- a/landing_gear_design/landing_gear_design_conf.xml
+++ b/landing_gear_design/landing_gear_design_conf.xml
@@ -123,9 +123,9 @@
<upper_boundary>1.5</upper_boundary>
<default>0.7</default>
</landing_gear_bay_keel_beam_width>
- <landing_gear_mass_correction_factor>
+ <landing_gear_mass_correction_factor description="Mass correction factor for the landing gear arrangement.">
<value>1.0</value>
- <unit>1</unit>
+ <unit>1.0</unit>
<lower_boundary>0.5</lower_boundary>
<upper_boundary>1.5</upper_boundary>
<default>1.0</default>
@@ -216,10 +216,10 @@
<default>5.2</default>
</specific_nose_gear_starting_x_position>
</use_specific_nose_gear_starting_x_position>
- <use_specific_minimum_percentage_of_nose_gear_load description="Switch to select using a specific starting position in x-direction for the nose gear strut(s). ('true': use, 'false': dont use">
+ <use_specific_minimum_percentage_of_nose_gear_load description="Switch to select using a specific minimum percentage of nose gear load. ('true': use, 'false': dont use">
<value>false</value>
<default>false</default>
- <specific_minimum_percentage_of_nose_gear_load description="Set specific starting position in x-direction for the nose gear strut(s).">
+ <specific_minimum_percentage_of_nose_gear_load description="Set specific minimum percentage of nose gear load.">
<value>2.5</value>
<unit>percent</unit>
<lower_boundary>2.5</lower_boundary>
@@ -227,10 +227,10 @@
<default>6.0</default>
</specific_minimum_percentage_of_nose_gear_load>
</use_specific_minimum_percentage_of_nose_gear_load>
- <use_specific_maximum_percentage_of_nose_gear_load description="Switch to select using a specific starting position in x-direction for the nose gear strut(s). ('true': use, 'false': dont use">
+ <use_specific_maximum_percentage_of_nose_gear_load description="Switch to select using a specific maximum percentage of nose gear load. ('true': use, 'false': dont use">
<value>false</value>
<default>false</default>
- <specific_maximum_percentage_of_nose_gear_load description="Set specific starting position in x-direction for the nose gear strut(s).">
+ <specific_maximum_percentage_of_nose_gear_load description="Set specific maximum percentage of nose gear load.">
<value>25.0</value>
<unit>percent</unit>
<lower_boundary>15.0</lower_boundary>
--
GitLab