RCAIDE.Library.Methods.Mass_Properties.Weight_Buildups.Conventional.BWB.FLOPS.compute_cabin_weight
compute_cabin_weight#
- compute_cabin_weight(cabin_area, TOGW)[source]#
Computes the structural weight of the pressurized cabin section of a BWB aircraft using regression-based methods derived from FEA studies.
- Parameters:
cabin_area (float) – Planform area of pressurized passenger cabin [m²]
TOGW (float) – Takeoff gross weight of aircraft [kg]
- Returns:
W_cabin – Estimated structural weight of BWB pressurized cabin section [kg]
- Return type:
float
Notes
Uses regression equations derived from detailed FEA studies by Bradley to estimate the structural weight required for the non-circular pressure vessel of a BWB cabin [1].
- Major Assumptions
Pressurized sandwich composite structure
Ultimate cabin pressure differential of 18.6 psi
Critical load case is 2.5g maneuver at maximum TOGW
Uniform pressure distribution
Non-buckling design
Structural efficiency similar to baseline FEA model
Theory Weight is computed using: .. math:
W_{cabin} = 5.698865 \cdot 0.316422 \cdot W^{0.166552} \cdot S_{cab}^{1.061158}
- where:
W = takeoff weight
S_cab = cabin planform area
- The equation coefficients account for:
Non-circular pressure vessel penalties
Composite material properties
Combined pressure and flight loads
Minimum gauge requirements
References
[1] Bradley, K. R., “A Sizing Methodology for the Conceptual Design of Blended-Wing-Body Transports,” NASA/CR-2004-213016, 2004.