aircraft.models.weights.general_aviation.general_aviation_weights

Module Contents

Classes

GAInstrumentsWeightInputs

Parameters (in English units!)

GAInstrumentsWeightModel

GeneralAviationWeights

Attributes

W_wing_est

class aircraft.models.weights.general_aviation.general_aviation_weights.GAInstrumentsWeightInputs

Parameters (in English units!)

S_fuse_planform: Union[float, int, csdl_alpha.Variable, None]
mach_max: Union[float, int, csdl_alpha.Variable]
num_flight_crew: Union[float, int, csdl_alpha.Variable]
num_fuselage_mounted_engines: Union[float, int, csdl_alpha.Variable]
num_wing_mounted_engines: Union[float, int, csdl_alpha.Variable]
xl: Union[float, int, csdl_alpha.Variable]
xlw: Union[float, int, csdl_alpha.Variable]
class aircraft.models.weights.general_aviation.general_aviation_weights.GAInstrumentsWeightModel
evaluate(inputs: GAInstrumentsWeightInputs)
class aircraft.models.weights.general_aviation.general_aviation_weights.GeneralAviationWeights(design_gross_weight: Union[csdl_alpha.Variable, float, int], dynamic_pressure: Union[csdl_alpha.Variable, float, int])
evaluate_avionics_weight(design_range: Union[float, int, csdl_alpha.Variable], num_flight_crew: Union[int, csdl_alpha.Variable], fuselage_plan_form_area: Union[float, int, csdl_alpha.Variable, None], fuselage_length: Union[float, int, csdl_alpha.Variable] = None, fuselage_width: Union[float, int, csdl_alpha.Variable] = None, correction_factor: Union[float, csdl_alpha.Variable] = 1.0)
evaluate_fuselage_weight(S_wet: Union[float, int, csdl_alpha.Variable], ulf: Union[float, int, csdl_alpha.Variable] = 3.75, fuselage_length: Union[float, int, csdl_alpha.Variable] = None, avergae_fuselage_diameter: Union[float, int, csdl_alpha.Variable] = None, correction_factor: Union[float, int, csdl_alpha.Variable] = 1.0)
evaluate_horizontal_tail_weight(S_ref: Union[float, int, csdl_alpha.Variable], ulf: Union[float, int, csdl_alpha.Variable] = 4.5, correction_factor: Union[float, int, csdl_alpha.Variable] = 1.0)
evaluate_main_landing_gear_weight(fuselage_length: Union[float, int, csdl_alpha.Variable], design_range: Union[float, int, csdl_alpha.Variable], W_ramp: Union[float, int, csdl_alpha.Variable], correction_factor: Union[float, int] = 1.0)
evaluate_vertical_tail_weight(S_ref: Union[float, int, csdl_alpha.Variable], AR: Union[float, int, csdl_alpha.Variable], thickness_to_chord: Union[float, int, csdl_alpha.Variable], sweep_c4: Union[float, int, csdl_alpha.Variable], ulf: Union[float, int, csdl_alpha.Variable] = 4.5, hht: Union[float, int, csdl_alpha.Variable] = 0.0, correction_factor: Union[float, int, csdl_alpha.Variable] = 1.0)
evaluate_wing_weight(S_ref: Union[float, int, csdl_alpha.Variable], fuel_weight: Union[float, int, csdl_alpha.Variable], AR: Union[float, int, csdl_alpha.Variable], sweep: Union[float, int, csdl_alpha.Variable], taper_ratio: Union[float, int, csdl_alpha.Variable], thickness_to_chord: Union[float, int, csdl_alpha.Variable] = 0.12, nz: Union[float, int, csdl_alpha.Variable] = 3.75, correction_factor: Union[float, int] = 1)
aircraft.models.weights.general_aviation.general_aviation_weights.W_wing_est = 200