RCAIDE.Library.Methods.Mass_Properties.Weight_Buildups.Cryogenic.Common.compute_landing_gear_weight

compute_landing_gear_weight

compute_landing_gear_weight(vehicle)

Calculate the weight of the main and nose landing gear of a hydrogen transport aircraft. Assumes max landing weight is equal to MTOW

Assumptions:

No fighter jet, change DFTE to 1 for a fighter jet Aircraft is not meant for carrier operations, change CARBAS to 1 for carrier-based aircraft

Source:

The Flight Optimization System Weight Estimation Method

Inputs:

vehicle - data dictionary with vehicle properties [dimensionless]

-.networks: data dictionary containing all propulsion properties -.design_range: design range of aircraft [nmi] -.systems.accessories: type of aircraft (short-range, commuter

medium-range, long-range, sst, cargo)

-.mass_properties.max_takeoff: MTOW [kilograms] -.nacelles[‘nacelle’] [meters] -.wings[‘main_wing’].dihedral [radians] -.fuselages[‘fuselage’].width: fuselage width [meters] -.fuselages[‘fuselage’].lengths.total: fuselage total length [meters]

Outputs:

output - data dictionary with main and nose landing gear weights [kilograms]

output.main, output.nose

Properties Used:

N/A