RCAIDE.Library.Methods.Mass_Properties.Weight_Buildups.Conventional.Transport.FLOPS.compute_landing_gear_weight
compute_landing_gear_weight#
- compute_landing_gear_weight(vehicle)[source]#
Computes the landing gear weight using NASA FLOPS weight estimation method. Accounts for aircraft type, size, and operational requirements.
- Parameters:
vehicle (Vehicle) –
- The vehicle instance containing:
- networkslist
Propulsion system data for nacelle dimensions
- design_rangefloat
Design range [nmi]
- systems.accessoriesstr
Aircraft type (‘short-range’, ‘commuter’, ‘medium-range’, ‘long-range’, ‘sst’, ‘cargo’)
- mass_properties.max_takeofffloat
Maximum takeoff weight [kg]
- wings[‘main_wing’].dihedralfloat
Wing dihedral angle [rad]
- fuselages[‘fuselage’]Fuselage
- Primary fuselage with:
- widthfloat
Maximum width [m]
- lengths.totalfloat
Total length [m]
- Returns:
output –
- Container with weight breakdown:
- mainfloat
Main landing gear weight [kg]
- nosefloat
Nose landing gear weight [kg]
- Return type:
Notes
Uses FLOPS correlations developed from transport aircraft database, with adjustments for different aircraft types. Please refer to the FLOPS documentation for more details: https://ntrs.nasa.gov/citations/20170005851
- Major Assumptions
Average landing gear
Not designed for carrier operations (CARBAS = 0)
Not a fighter aircraft (DFTE = 0)
Retractable gear configuration
Theory Main gear weight is computed using: .. math:
W_{MLG} = (0.0117 - 0.0012D_{FTE})W_{L}^{0.95}X_{MLG}^{0.43}
Nose gear weight is computed using: .. math:
W_{NLG} = (0.048 - 0.0080D_{FTE})W_{L}^{0.67}X_{NLG}^{0.43}(1 + 0.8C_{B})
- where:
W_L = landing weight
X_MLG = extended main gear length
X_NLG = extended nose gear length
D_FTE = fighter aircraft flag
C_B = carrier-based flag
References
[1] NASA Flight Optimization System (FLOPS)