Tank capacity check

Tank capacity check only for kerosene, added exception for h2.

weight_and_balance_analysis/src/tube_and_wing/standard/basic/methodbasic.py

@@ -389,7 +389,9 @@ def method_basic(paths_and_names, routing_dict, dict_ac_exchange, dict_mod_confi
         kwargs_base['starting_cg'] = starting_cg
         kwargs_base['starting_mass'] = starting_mass
 
-    cg_positions_dict['defueling_cg'] = [value * mac / 100 + x_leading_edge_mac for value in cg_positions_dict['defueling']]
+    cg_pos_out = {}
+    cg_pos_out['defueling_xCG'] = [value * mac / 100 +
+                                         x_leading_edge_mac for value in cg_positions_dict['defueling']]
 
     # Calculate most forward and aft CG
     all_cg_positions_over_mac = [
@@ -505,7 +507,7 @@ def method_basic(paths_and_names, routing_dict, dict_ac_exchange, dict_mod_confi
         "Refueling CG change": cg_positions_dict["refueling"],
         "Refueling mass change": total_mass_dict["refueling"],
         "Defueling CG change": cg_positions_dict["defueling"],
-        "Defueling xCG": cg_positions_dict["defueling_cg"],
+        "Defueling xCG": cg_pos_out["defueling_xCG"],
         "Defueling mass change": total_mass_dict["defueling"],
         "Defueling mode": defueling_mode,
         "Passengers boarding front back CG change": cg_positions_dict["passengers_boarding"],
@@ -1190,8 +1192,9 @@ def calculate_fuel_mass_properties(tanks, fuel_mass, routing_dict, dict_ac_excha
             runtime_output.critical(
                 "Fuel mass calculation failed ... Not enough capacity in tanks!")
         else:
-            raise ValueError(
-                "Fuel mass calculation failed ... Not enough capacity in tanks!")
+            if tanks[0].energy_carrier == 'kerosene':
+                raise ValueError(
+                    "Fuel mass calculation failed ... Not enough capacity in tanks!")
 
     fuel_mass_properties = MassPropertiesIO().initialize_zero()
     fuel_mass_properties.mass = sum(
@@ -1496,7 +1499,7 @@ def calculate_design_payload_mass(transport_task_data, accomodation, fuselage_ma
 
     # cargodeck + passenger_deck + additional cargo
     design_payload_mass.center_of_gravity = fuselage_mass_properties.center_of_gravity
-    design_payload_mass.center_of_gravity['x'] =(sum(accomodation.seating_spacing_x_coordinate) + sum(
+    design_payload_mass.center_of_gravity['x'] = (sum(accomodation.seating_spacing_x_coordinate) + sum(
         accomodation.cargo_spacing_x_coordinate)) / (len(accomodation.seating_spacing_x_coordinate) + len(
             accomodation.cargo_spacing_x_coordinate))
     design_payload_mass.initialize_zero_inertia()