RCAIDE.Library.Methods.Mass_Properties.Weight_Buildups.Conventional.Transport.FLOPS.compute_fuselage_weight
compute_fuselage_weight#
- compute_fuselage_weight(vehicle)[source]#
Computes the fuselage weight using NASA FLOPS weight estimation method. Accounts for aircraft type.
- Parameters:
vehicle (Vehicle) –
- The vehicle instance containing:
- networkslist
Propulsion system data for engine count and mounting
- fuselages[‘fuselage’]Fuselage
- Primary fuselage with:
- lengths.totalfloat
Total fuselage length [m]
- widthfloat
Maximum fuselage width [m]
- heights.maximumfloat
Maximum fuselage height [m]
- flight_envelope.ultimate_loadfloat
Ultimate load factor (default: 3.75)
- systems.accessoriesstr
Aircraft type (‘short-range’, ‘commuter’, ‘medium-range’, ‘long-range’, ‘sst’, ‘cargo’)
- mass_properties.max_takeofffloat
Maximum takeoff weight [kg]
- design_mach_numberfloat
Design cruise Mach number
- Returns:
WFUSE – Fuselage structural weight [kg]
- Return type:
float
Notes
Uses FLOPS correlations developed from transport aircraft database. For more details, please refer to the FLOPS documentation: https://ntrs.nasa.gov/citations/20170005851
- Major Assumptions
Single fuselage configuration (NFUSE = 1). If there are multiple fuselages, these are calcualted separately.
Fuselage is tagged as ‘fuselage’
Theory For transport aircraft: .. math:
W_{fuse} = 1.35(L_{f}D_{eq})^{1.28}(1 + 0.05*N_{ef})(1 + 0.38*F_{cargo})
- where:
L_f = fuselage length
D_eq = equivalent diameter
N_ef = number of fuselage-mounted engines
F_cargo = cargo aircraft flag
References
[1] NASA Flight Optimization System (FLOPS)