var_type=bool,
default_value=False,
unit='1',
descr='Option to extract loads from results',
xpath=CEASIOM_XPATH + '/aerodynamics/su2/results/extractLoads',
gui=True,
gui_name='Extract loads',
gui_group='Results',
)
# ----- Output -----
cpacs_inout.add_output(
var_name='start_time',
var_type=str,
default_value=None,
unit='1',
descr='Start time of the last SU2 calculation',
xpath=SU2_XPATH + '/startTime',
)
cpacs_inout.add_output(
var_name='end_time',
var_type=str,
default_value=None,
unit='1',
descr='Start time of the last SU2 calculation',
xpath=SU2_XPATH + '/endTime',
)
cpacs_inout.add_output(
var_name='wetted_area',
)
cpacs_inout.add_input(
var_name='cruise_alt',
default_value=12000,
unit='m',
descr='Aircraft cruise altitude',
xpath=CEASIOM_XPATH + '/ranges/cruiseAltitude',
)
# ===== Output =====
cpacs_inout.add_output(
var_name='cd0',
default_value=None,
unit='1',
descr='Skin friction drag coefficient',
xpath=CEASIOM_XPATH + '/aerodynamics/su2/skinFriction/cd0',
)
cpacs_inout.add_output(
var_name='main_wing_area',
default_value=None,
unit='m^2',
descr='Wing area of the main (largest) wing',
xpath=CEASIOM_XPATH + '/geometry/analyses/wingArea',
)
cpacs_inout.add_output(
var_name='main_wing_span',
default_value=None,
xpath=REF_XPATH + "/area",
)
cpacs_inout.add_input(
var_name="length",
default_value=None,
unit="m",
descr="Reference length for force and moment coefficients",
xpath=REF_XPATH + "/length",
)
cpacs_inout.add_input(
var_name="wing",
default_value=None,
unit="-",
descr="Aircraft lifting surface",
xpath=WINGS_XPATH,
)
# ----- Output -----
cpacs_inout.add_output(
var_name="aeromap_PyTornado", # name to change...
# var_type=CPACS_aeroMap, # no type pour output, would it be useful?
default_value=None,
unit="-",
descr="aeroMap with aero coefficients calculated by PyTornado",
xpath=AEROPERFORMANCE_XPATH + "/aeroMap/aeroPerformanceMap",
)
)
cpacs_inout.add_input(
var_name="cruise_alt",
default_value=12000,
unit="m",
descr="Aircraft cruise altitude",
xpath=RANGE_XPATH + "/cruiseAltitude",
)
# ===== Output =====
cpacs_inout.add_output(
var_name="cd0",
default_value=None,
unit="1",
descr="Skin friction drag coefficient",
xpath=SF_XPATH + "/cd0",
)
cpacs_inout.add_output(
var_name="main_wing_area",
default_value=None,
unit="m^2",
descr="Wing area of the main (largest) wing",
xpath=GEOM_XPATH + "/analyses/wingArea",
)
cpacs_inout.add_output(
var_name="main_wing_span",
default_value=None,
xpath=CEASIOM_XPATH + '/propulsion/tSFC',
gui=True,
gui_name='TSFC',
gui_group='Cruise',
)
# TODO: Missing some imput about engines
# ----- Output -----
# TODO: check if all input are there
cpacs_inout.add_output(
var_name='maximum_take_off_mass',
default_value=None,
unit='[kg]',
descr='Maximum take of mass',
xpath=AIRCRAFT_XPATH +
'/model/analyses/massBreakdown/designMasses/mTOM/mass',
)
cpacs_inout.add_output(
var_name='zero_fuel_mass',
default_value=None,
unit='[kg]',
descr='Zero fuel mass',
xpath=AIRCRAFT_XPATH +
'/model/analyses/massBreakdown/designMasses/mZFM/mass',
)
cpacs_inout.add_output(
var_name='mass_fuel_max',
cpacs/vehicles/engines/engine[..]/name
cpacs/vehicles/engines/engine/analyses/mass/mass
True if the User define the Engines in the EngineData class Belongs to the UserInputs Class
Number of Engines Belongs to the EngineData class
Name of each engine Belongs to the EngineData class, [..] stands for the number of the engine
Mass of a single mounted engine (Dry Weight) Belongs to the EngineData class
"""
# ----- Output -----
cpacs_inout.add_output(
var_name='maximum_take_off_mass',
default_value=None,
unit='[kg]',
descr='Maximum take of mass',
xpath=AIRCRAFT_XPATH +
'/model/analyses/massBreakdown/designMasses/mTOM/mass',
)
cpacs_inout.add_output(
var_name='zero_fuel_mass',
default_value=None,
unit='[kg]',
descr='Zero fuel mass',
xpath=AIRCRAFT_XPATH +
'/model/analyses/massBreakdown/designMasses/mZFM/mass',
)
cpacs_inout.add_output(
var_name='mass_fuel_max',
unit='m^2',
descr='Reference area for force and moment coefficients',
xpath=REFS_XPATH + '/area')
cpacs_inout.add_input(
var_name='length',
default_value=None,
unit='m',
descr='Reference length for force and moment coefficients',
xpath=REFS_XPATH + '/length')
cpacs_inout.add_input(
var_name='wing',
default_value=None,
unit='-',
descr='Aircraft lifting surface',
xpath=WING_XPATH,
)
# ----- Output -----
cpacs_inout.add_output(
var_name='aeromap_PyTornado', # name to change...
# var_type=CPACS_aeroMap, # no type pour output, would it be useful?
default_value=None,
unit='-',
descr='aeroMap with aero coefficients calculated by PyTornado',
xpath=
'/cpacs/vehicles/aircraft/model/analyses/aeroPerformance/aeroMap[i]/aeroPerformanceMap',
)
cpacs_inout.add_input(
var_name="ref_area",
var_type=float,
default_value=None,
unit="m^2",
descr="Aircraft reference area",
xpath=REF_XPATH + "/area",
gui=False,
gui_name=None,
gui_group=None,
)
# ===== Output =====
cpacs_inout.add_output(
var_name="target_cl",
default_value=None,
unit="1",
descr="Value of CL to achieve to have a level flight with the given conditions",
xpath=SU2_XPATH + "/targetCL",
)
cpacs_inout.add_output(
var_name="fixed_cl",
default_value=None,
unit="-",
descr="FIXED_CL_MODE parameter for SU2",
xpath=SU2_XPATH + "/fixedCL",
)
# ----- Output -----
# TODO: add it or not?
# cpacs_inout.add_output(
# var_name='wetted_area',
# var_type=float,
# default_value=None,
# unit='m^2',
# descr='Aircraft wetted area calculated by SU2',
# xpath=CEASIOMPY_XPATH + '/geometry/analyses/wettedArea',
# )
cpacs_inout.add_output(
var_name="su2_def_mesh_list",
var_type=list,
default_value=None,
unit="1",
descr="List of SU2 deformed meshes generated by SU2MeshDef",
xpath=SU2_XPATH + "/availableDeformedMesh",
)
cpacs_inout.add_output(
var_name="bc_wall_list",
var_type=list,
default_value=None,
unit="1",
descr="Wall boundary conditions found in the SU2 mesh",
xpath=SU2_XPATH + "/boundaryConditions/wall",
)
var_type=float,
default_value=0.1,
unit="-",
descr="Unusable fuel percentage [0 - 1]",
xpath=FUEL_XPATH + "/resFuelPerc",
gui=True,
gui_name="Unusable fuel",
gui_group="Fuel",
)
# ----- Output -----
cpacs_inout.add_output(
var_name="mf_for_climb",
default_value=None,
unit="kg",
descr="Fuel used for climb",
xpath=FUEL_CONSUMPTION_XPATH + "/fuelForClimb",
)
cpacs_inout.add_output(
var_name="mf_for_cruise",
default_value=None,
unit="kg",
descr="Fuel used for Cruise",
xpath=FUEL_CONSUMPTION_XPATH + "/fuelForCruise",
)
cpacs_inout.add_output(
var_name="mf_for_loiter",
default_value=None,
)
cpacs_inout.add_input(
var_name='cruise_alt',
default_value=12000,
unit='m',
descr='Aircraft cruise altitude',
cpacs_path=CEASIOM_XPATH + '/ranges/cruiseAltitude',
)
# ===== Output =====
cpacs_inout.add_output(
var_name='cd0',
default_value=None,
unit='1',
descr='Skin friction drag coefficient',
cpacs_path=CEASIOM_XPATH + '/aerodynamics/su2/skinFriction/cd0',
)
cpacs_inout.add_output(
var_name='wing_area',
default_value=None,
unit='m^2',
descr='Wing area of the main (largest) wing',
cpacs_path=CEASIOM_XPATH + '/geometry/analysis/wingArea',
)
cpacs_inout.add_output(
var_name='wing_span',
default_value=None,
)
# ----- Output -----
# TODO: add it or not?
# cpacs_inout.add_output(
# var_name='wetted_area',
# var_type=float,
# default_value=None,
# unit='m^2',
# descr='Aircraft wetted area calculated by SU2',
# xpath=CEASIOM_XPATH + '/geometry/analyses/wettedArea',
# )
cpacs_inout.add_output(
var_name='su2_def_mesh_list',
var_type=list,
default_value=None,
unit='1',
descr='List of SU2 deformed meshes generated by SU2MeshDef',
xpath=SU2_XPATH + '/availableDeformedMesh',
)
cpacs_inout.add_output(var_name='bc_wall_list',
var_type=list,
default_value=None,
unit='1',
descr='Wall boundary conditions found in the SU2 mesh',
xpath=CEASIOM_XPATH +
'/aerodynamics/su2/boundaryConditions/wall')
unit="1",
descr="Absolute path to the SUMO file",
xpath=SUMOFILE_XPATH,
gui=True,
gui_name="SUMO File path",
gui_group="Inputs",
)
cpacs_inout.add_input(
var_name="refine_level",
var_type="float",
default_value=1.0,
unit="1",
descr="0 is baseline, +1 env. equal double mesh points",
xpath=MESH_XPATH + "/sumoOptions/refinementLevel",
gui=True,
gui_name="Refinement Level",
gui_group="SUMO options",
)
# ----- Output -----
cpacs_inout.add_output(
var_name="su2_mesh_path",
var_type="pathtype",
default_value=None,
unit="1",
descr="Absolute path of the SU2 mesh",
xpath=SU2MESH_XPATH,
)
default_value=False,
unit='1',
descr='Convert engine from CEASIOMpy',
xpath=CEASIOM_XPATH + '/engine/includeEngine',
gui=True,
gui_name='Include engine',
gui_group='Option',
)
cpacs_inout.add_input(
var_name='include_pylon',
var_type=bool,
default_value=False,
unit='1',
descr='Convert engine from CEASIOMpy',
xpath=CEASIOM_XPATH + '/engine/includePylon',
gui=True,
gui_name='Include pylon',
gui_group='Option',
)
# ----- Output -----
cpacs_inout.add_output(
var_name='sumo_file_path',
default_value=None,
unit='1',
descr='Path to the SUMO file generated by CPACS2SUMO',
xpath='/cpacs/toolspecific/CEASIOMpy/filesPath/sumoFilePath',
)
#
# cpacs_inout.add_input(
# var_name='aeromap_uid',
# var_type=list,
# default_value=None,
# xpath='/cpacs/toolspecific/CEASIOMpy/aerodynamics/skinFriction/aeroMapToCalculate',
# gui=include_gui,
# gui_name='__AEROMAP_CHECHBOX',
# )
cpacs_inout.add_input(
var_name="other_var",
var_type=list,
default_value=[2, 33, 444],
unit="[unit]",
xpath="/cpacs/toolspecific/CEASIOMpy/test/myList",
gui=include_gui,
gui_name="Choice",
gui_group="My Selection",
)
# ----- Output -----
cpacs_inout.add_output(
var_name="output",
default_value=None,
unit="1",
descr="Description of the output",
xpath="/cpacs/toolspecific/CEASIOMpy/test/myOutput",
)
var_type=bool,
default_value=False,
unit=None,
descr="Save all plot during the stability analysis",
xpath=STABILITY_STATIC_XPATH + "/savePlots",
gui=True,
gui_name="Save Stbility plots",
gui_group="Output",
)
# ===== Output =====
cpacs_inout.add_output(
var_name="longitudinaly_stable",
default_value=None,
unit="1",
descr="Is the aircraft longitudinaly stable",
xpath=STABILITY_STATIC_XPATH + "/results/longitudinalStaticStable",
)
cpacs_inout.add_output(
var_name="dirrectionaly_stable",
default_value=None,
unit="1",
descr="Is the aircraft dirrectionaly stable",
xpath=STABILITY_STATIC_XPATH + "/results/directionnalStaticStable",
)
cpacs_inout.add_output(
var_name="trim_alt_longi_list",
cpacs/vehicles/engines/engine[..]/name
cpacs/vehicles/engines/engine/analyses/mass/mass
True if the User define the Engines in the EngineData class Belongs to the UserInputs Class
Number of Engines Belongs to the EngineData class
Name of each engine Belongs to the EngineData class, [..] stands for the number of the engine
Mass of a single mounted engine (Dry Weight) Belongs to the EngineData class
"""
# ----- Output -----
cpacs_inout.add_output(
var_name="maximum_take_off_mass",
default_value=None,
unit="[kg]",
descr="Maximum take of mass",
xpath=MASSBREAKDOWN_XPATH + "/designMasses/mTOM/mass",
)
cpacs_inout.add_output(
var_name="zero_fuel_mass",
default_value=None,
unit="[kg]",
descr="Zero fuel mass",
xpath=MASSBREAKDOWN_XPATH + "/designMasses/mZFM/mass",
)
cpacs_inout.add_output(
var_name="mass_fuel_max",
default_value=None,
var_type=bool,
default_value=False,
unit='1',
descr='Option to extract loads from results',
xpath=CEASIOM_XPATH + '/aerodynamics/su2/results/extractLoads',
gui=True,
gui_name='Extract loads',
gui_group='Results',
)
# ----- Output -----
cpacs_inout.add_output(
var_name='start_time',
var_type=str,
default_value=None,
unit='1',
descr='Start time of the last SU2 calculation',
xpath=SU2_XPATH + '/startTime',
)
cpacs_inout.add_output(
var_name='end_time',
var_type=str,
default_value=None,
unit='1',
descr='Start time of the last SU2 calculation',
xpath=SU2_XPATH + '/endTime',
)
cpacs_inout.add_output(
var_name='wetted_area',
var_type=bool,
default_value=False,
unit="1",
descr="Option to extract loads from results",
xpath=SU2_XPATH + "/results/extractLoads",
gui=True,
gui_name="Extract loads",
gui_group="Results",
)
# ----- Output -----
cpacs_inout.add_output(
var_name="start_time",
var_type=str,
default_value=None,
unit="1",
descr="Start time of the last SU2 calculation",
xpath=SU2_XPATH + "/startTime",
)
cpacs_inout.add_output(
var_name="end_time",
var_type=str,
default_value=None,
unit="1",
descr="Start time of the last SU2 calculation",
xpath=SU2_XPATH + "/endTime",
)
cpacs_inout.add_output(
var_name="wetted_area",
var_name='ref_area',
var_type=float,
default_value=None,
unit='m^2',
descr='Aircraft reference area',
xpath=AIRCRAFT_XPATH + '/model/reference/area',
gui=False,
gui_name=None,
gui_group=None,
)
#===== Output =====
cpacs_inout.add_output(
var_name='target_cl',
default_value=None,
unit='1',
descr='Value of CL to achieve to have a level flight with the given conditions',
xpath=CEASIOM_XPATH + '/aerodynamics/su2/targetCL',
)
cpacs_inout.add_output(
var_name='fixed_cl',
default_value=None,
unit='-',
descr='FIXED_CL_MODE parameter for SU2',
xpath=CEASIOM_XPATH + '/aerodynamics/su2/fixedCL',
)
#
# cpacs_inout.add_input(
# var_name='aeromap_uid',
# var_type=list,
# default_value=None,
# xpath='/cpacs/toolspecific/CEASIOMpy/aerodynamics/skinFriction/aeroMapToCalculate',
# gui=include_gui,
# gui_name='__AEROMAP_CHECHBOX',
# )
cpacs_inout.add_input(
var_name='other_var',
var_type=list,
default_value= [2,33,444],
unit='[unit]',
xpath='/cpacs/toolspecific/CEASIOMpy/test/myList',
gui=include_gui,
gui_name='Choice',
gui_group='My Selection'
)
# ----- Output -----
cpacs_inout.add_output(
var_name='output',
default_value=None,
unit='1',
descr='Description of the output',
xpath='/cpacs/toolspecific/CEASIOMpy/test/myOutput',
)
var_type=float,
default_value=0.1,
unit='-',
descr='Unusable fuel percentage [0 - 1]',
xpath=CEASIOMPY_XPATH + '/fuels/resFuelPerc',
gui=True,
gui_name='Unusable fuel',
gui_group='Fuel',
)
# ----- Output -----
cpacs_inout.add_output(
var_name='mf_for_climb',
default_value=None,
unit='kg',
descr='Fuel used for climb',
xpath=FUEL_CONSUMPTION_XPATH + '/fuelForClimb',
)
cpacs_inout.add_output(
var_name='mf_for_cruise',
default_value=None,
unit='kg',
descr='Fuel used for Cruise',
xpath=FUEL_CONSUMPTION_XPATH + '/fuelForCruise',
)
cpacs_inout.add_output(
var_name='mf_for_loiter',
default_value=None,
var_type=bool,
default_value=False,
unit=None,
descr='Save all plot during the stability analysis',
xpath=STABILITY_STATIC_XPATH + '/savePlots',
gui=True,
gui_name='Save Stbility plots',
gui_group='Output',
)
# ===== Output =====
cpacs_inout.add_output(
var_name='longitudinaly_stable',
default_value=None,
unit='1',
descr='Is the aircraft longitudinaly stable',
xpath=STABILITY_STATIC_XPATH+'/results/longitudinalStaticStable',
)
cpacs_inout.add_output(
var_name='dirrectionaly_stable',
default_value=None,
unit='1',
descr='Is the aircraft dirrectionaly stable',
xpath=STABILITY_STATIC_XPATH+'/results/directionnalStaticStable',
)
cpacs_inout.add_output(
var_name='trim_alt_longi_list',
descr='Absolute path to the SUMO file',
xpath=CEASIOM_XPATH + '/filesPath/sumoFilePath',
gui=True,
gui_name='SUMO File path',
gui_group='Inputs',
)
cpacs_inout.add_input(
var_name='refine_level',
var_type='float',
default_value=1.0,
unit='1',
descr='0 is baseline, +1 env. equal double mesh points',
xpath=CEASIOM_XPATH + '/mesh/sumoOptions/refinementLevel',
gui=True,
gui_name='Refinement Level',
gui_group='SUMO options',
)
# ----- Output -----
cpacs_inout.add_output(
var_name='su2_mesh_path',
var_type='pathtype',
default_value=None,
unit='1',
descr='Absolute path of the SU2 mesh',
xpath=CEASIOM_XPATH + '/filesPath/su2Mesh',
)
unit="1",
descr="Convert engine from CEASIOMpy",
xpath=CEASIOMPY_XPATH + "/engine/includeEngine",
gui=True,
gui_name="Include engine",
gui_group="Option",
)
cpacs_inout.add_input(
var_name="include_pylon",
var_type=bool,
default_value=False,
unit="1",
descr="Convert engine from CEASIOMpy",
xpath=CEASIOMPY_XPATH + "/engine/includePylon",
gui=True,
gui_name="Include pylon",
gui_group="Option",
)
# ----- Output -----
cpacs_inout.add_output(
var_name="sumo_file_path",
default_value=None,
unit="1",
descr="Path to the SUMO file generated by CPACS2SUMO",
xpath=SUMOFILE_XPATH,
)
