RCAIDE.Library.Methods.Mass_Properties.Weight_Buildups.Conventional.Transport.Raymer.compute_fuselage_weight
compute_fuselage_weight#
- compute_fuselage_weight(vehicle, fuselage, settings)[source]#
Calculates the weight of the fuselage for transport aircraft using Raymer’s method.
- Parameters:
vehicle (RCAIDE.Vehicle()) –
- Vehicle data structure containing:
- mass_properties.max_takeofffloat
Maximum takeoff weight [kg]
- flight_envelope.ultimate_loadfloat
Ultimate load factor (default: 3.75)
- wings[‘main_wing’]Data()
Main wing properties including taper and sweep
fuselage (RCAIDE.Component()) –
- Fuselage component containing:
- lengths.totalfloat
Total fuselage length [m]
- widthfloat
Maximum fuselage width [m]
- heights.maximumfloat
Maximum fuselage height [m]
settings (Data()) –
- Configuration settings containing:
- Raymer.fuselage_mounted_landing_gear_factorfloat
Factor for fuselage-mounted landing gear
- Raymer.cargo_doors_numberint
Number of cargo doors
- Raymer.cargo_doors_clamshellbool
True if cargo doors are clamshell doors, False otherwise
- Returns:
weight_fuselage – Weight of the fuselage structure [kg]
- Return type:
float
Notes
This method implements Raymer’s semi-empirical correlation for transport aircraft fuselage weight estimation. The correlation accounts for size, loads, and wing-body intersection effects. It also accounts for the number of cargo doors and their type (if present).
- Major Assumptions
No fuselage-mounted landing gear by default
One cargo door (Kdoor = 1.06)
Correlation based on transport category aircraft data
Theory The fuselage weight is calculated using: .. math:
W_{fus} = 0.328K_{door}K_{lg}(W_{dg}N_{ult})^{0.5}L^{0.25}S_f^{0.302}(1+K_{ws})^{0.04}(L/D)^{0.1}
- where:
\(K_{ws}\) accounts for wing-body intersection effects
\(S_f\) is the fuselage wetted area
\(L/D\) is the fuselage fineness ratio
References
- [1] Raymer, D., “Aircraft Design: A Conceptual Approach”, AIAA
Education Series, 2018.