landing_gear_design: - delete unnecessary parameter

landing_gear_design/src/wing_mounted/empirical/landing_gear_design_tu_berlin/general/call_functions/_04_estimatelimitations.py

@@ -149,9 +149,9 @@ def estimate_limitations(dict_ac_exchange, dict_mod_config, landing_gear_descrip
                     landing_gear_description['lever_arms']['distance_between_main_gear_and_rearmost_center_of_gravity']\
                         = landing_gear_limitations['minimum_distance_between_main_landing_gear_and_aft_most_center_of_gravity']  # noPep8 e501
 
-        wing_reference_point_key, wing_reference_point_value = \
+        _, wing_reference_point_value = \
             next(reversed(list(dict_ac_exchange['wing_section_position_in_x'].items())), (None, None))
-        wing_chord_length_key, wing_chord_length_value = \
+        _, wing_chord_length_value = \
             next(reversed(list(dict_ac_exchange['wing_chord_length_on_section'].items())), (None, None))
         # Check if the resulting minimum forward main gear position is not within 90 percent of the wing depth
         #  but retractable is selected -> if true: -> Set main gear positioning flag to False
@@ -166,7 +166,7 @@ def estimate_limitations(dict_ac_exchange, dict_mod_config, landing_gear_descrip
         min_tire_diameter = min([float(value['min_outside_diameter_in_inch'])
                                  for key, value in main_gear_tires.items() if 'min_outside_diameter_in_inch' in value])
 
-        fuselage_section_width_key, fuselage_section_width_value = \
+        _, fuselage_section_width_value = \
             next(iter(dict_ac_exchange['fuselage_section_width'].items()), (None, None))
         if dict_ac_exchange['dihedral_angle_wing'] is not None \
                 and dict_ac_exchange['rear_spar_position_center_wing_box_in_z_direction'] is not None \
@@ -221,7 +221,7 @@ def estimate_limitations(dict_ac_exchange, dict_mod_config, landing_gear_descrip
                 max(dict_ac_exchange['fuselage_section_width'].values())
 
         # nose landing gear strut y-postion
-        fuselage_reference_point_key, fuselage_reference_point_value = \
+        _, fuselage_reference_point_value = \
             next(iter(dict_ac_exchange['fuselage_reference_point_in_y_direction'].items()), (None, None))
         if fuselage_reference_point_value is not None:
             if nose_gear_arrangement['number_of_nose_gear_struts'] == 1: