RCAIDE.Library.Methods.Mass_Properties.Weight_Buildups.Conventional.BWB.FLOPS.compute_operating_empty_weight
compute_operating_empty_weight#
- compute_operating_empty_weight(vehicle, settings=None)[source]#
This is for a BWB aircraft configuration.
- Assumptions:
Calculated aircraft weight from correlations created per component of historical aircraft The wings are made out of aluminum. A wing with the tag ‘main_wing’ exists.
- Source:
N/A
- Inputs:
- engine - a data dictionary with the fields:
thrust_sls - sea level static thrust of a single engine [Newtons]
- Parameters:
vehicle (Vehicle) –
- The vehicle instance containing:
- mass_properties.max_takeofffloat
Maximum takeoff weight [kg]
- fuselageslist
- BWB fuselage segments with:
- aft_centerbody_areafloat
Planform area of aft section [m²]
- aft_centerbody_taperfloat
Taper ratio of aft section
- cabin_areafloat
Pressurized cabin area [m²]
- wingslist
Wing surfaces
- networkslist
Propulsion systems
settings (Data, optional) –
- Configuration settings with:
- use_max_fuel_weightbool
Flag to use maximum fuel capacity
- Returns:
output –
- Container with weight breakdowns:
- emptyData
Structural, propulsion, and systems weights
- payloadData
Passenger, baggage, and cargo weights
- fuelfloat
Total fuel weight [kg]
- zero_fuel_weightfloat
Operating empty weight plus payload [kg]
- totalfloat
Total aircraft weight [kg]
- Return type:
Notes
Computes weights for all major aircraft components and systems using methods specific to BWB configurations.
- Major Assumptions
Calculated aircraft weight from correlations created per component of historical aircraft
The wings are made out of aluminum.
A wing with the tag ‘main_wing’ exists.
References
- [1] Bradley, K. R., “A Sizing Methodology for the Conceptual Design of
Blended-Wing-Body Transports,” NASA/CR-2004-213016, 2004.