RCAIDE.Library.Methods.Mass_Properties.Weight_Buildups.Conventional.General_Aviation.FLOPS.compute_landing_gear_weight

compute_landing_gear_weight#

compute_landing_gear_weight(vehicle)[source]#

Calculates the weight of a general aviation aircraft’s landing gear system using FLOPS methodology.

Parameters:

vehicle (RCAIDE.Vehicle()) –

Vehicle data structure containing:

  • mass_properties.max_takeoff

  • landing_gear.nose_wheels

  • landing_gear.main_wheels

  • landing_gear.configuration_type

  • flight_envelope.design_range

  • wings.main_wing.dihedral

  • fuselages.fuselage.width

  • fuselages.fuselage.lengths.total

Returns:

output –

Data structure containing:

  • output.main: weight of the main landing gear in kilograms

  • output.nose: weight of the nose landing gear in kilograms

Return type:

Data()

Notes

The function uses FLOPS (Flight Optimization System) statistical regression models based on historical aircraft data to estimate landing gear weight. The calculation includes the weight of struts, wheels, tires, brakes, and actuation systems. This method is common between general aviation and transport aircraft in FLOPS. Of note, FLOPS does not use user defined landing gear lengths and tire sizes.

Major Assumptions

  • Landing gear is not for a fighter jet, carrier based aircraft, or supersonic transport

  • Landing gear length is based on the wingspan and fuselage length

  • Brake system, retraction mechanism, and other components are baked into the weight

Theory

The FLOPS weight estimation follows the relationship:

\[W_{LGM} = (0.0117) * (W_{LDG})^{0.95} * (X_{MLG})^{0.43} W_{LGN} = (0.048) * (W_{LDG})^{0.67} * (X_{NLG})^{0.43}\]
Where:

  • W_{LGM} is landing gear weight for the main landing gear

  • W_{LGN} is landing gear weight for the nose landing gear

  • W_{LDG} is landing weight for the entire aircraft

  • X_{MLG} is the length of the main landing gear

  • X_{NLG} is the length of the nose landing gear

Reference: