RCAIDE.Library.Methods.Mass_Properties.Weight_Buildups.Conventional.Transport.Raymer.compute_landing_gear_weight
compute_landing_gear_weight#
- compute_landing_gear_weight(vehicle)[source]#
Calculates the weight of main and nose landing gear for transport aircraft using Raymer’s method.
- Parameters:
vehicle (RCAIDE.Vehicle()) –
- Vehicle data structure containing:
- design_rangefloat
Design range of aircraft [m]
- mass_properties.max_takeofffloat
Maximum takeoff weight [kg]
- systems.accessoriesstr
Aircraft type (‘short-range’, ‘commuter’, ‘medium-range’, ‘long-range’, ‘sst’, ‘cargo’)
- landing_gearslist
- List of landing gear components containing:
- strut_lengthfloat
Length of strut [m]
- wheelsint
Number of wheels per strut
- Returns:
output –
- Landing gear weights:
- mainfloat
Weight of main landing gear [kg]
- nosefloat
Weight of nose landing gear [kg]
- Return type:
Data()
Notes
This method implements Raymer’s empirical correlations for transport aircraft landing gear weight estimation. Separate correlations are used for main and nose gear.
- Major Assumptions
Gear load factor = 3
Number of main gear shock struts = 2
Stall speed assumes max Cl of 2.5, density of 1.225 kg/m^3
All main landing gear is assumed to be of the same type
All nose landing gear is assumed to be of the same type
Theory The landing gear weights are calculated using: .. math:
W_{main} = 0.0106K_{mp}W_{l}^{0.888}N_l^{0.25}L_m^{0.4}N_{mw}^{0.321}N_{mss}^{-0.5}V_{stall}^{0.1}
\[W_{nose} = 0.032K_{np}W_{l}^{0.646}N_l^{0.2}L_n^{0.5}N_{nw}^{0.45}\]- where:
\(W_l\) is landing weight
\(N_l\) is ultimate landing load factor
\(L_m, L_n\) are strut lengths
\(N_{mw}, N_{nw}\) are number of wheels
\(N_{mss}\) is number of main gear shock struts
References
- [1] Raymer, D., “Aircraft Design: A Conceptual Approach”, AIAA
Education Series, 2018.