RCAIDE.Library.Methods.Mass_Properties.Weight_Buildups.Conventional.Transport.FLOPS.compute_systems_weight
compute_systems_weight#
- compute_systems_weight(vehicle)[source]#
Calculate the system weight of the aircraft using the FLOPS methodology.
- Parameters:
vehicle (Data) –
- Data dictionary with vehicle properties
- networkslist
List of network objects containing propulsion properties - propulsors : list
List of propulsor objects - wing_mounted : bool
Flag indicating if propulsor is wing-mounted
- nacelleData, optional
Nacelle properties - diameter : float
Nacelle diameter [m]
- wingslist
List of wing objects - areas.reference : float
Wing reference area [m²]
- flap_ratiofloat
Flap surface area over wing surface area
- spans.projectedfloat
Projected span of wing [m]
- sweeps.quarter_chordfloat
Quarter chord sweep [deg]
- fuselageslist
List of fuselage objects - lengths.total : float
Fuselage total length [m]
- widthfloat
Fuselage width [m]
- heights.maximumfloat
Fuselage maximum height [m]
- mass_properties.max_takeofffloat
Maximum takeoff weight [kg]
- flight_envelope.design_mach_numberfloat
Design mach number for cruise flight
- flight_envelope.design_rangefloat
Design range of aircraft [nmi]
- passengersint
Number of passengers in aircraft
- NPFint
Number of first class passengers
- NPBint
Number of business class passengers
- NPTint
Number of tourist/economy class passengers
- reference_areafloat
Aircraft reference area [m²]
- Returns:
output – Data dictionary containing system weight components - W_flight_control : float
Weight of the flight control system [kg]
- W_apufloat
Weight of the auxiliary power unit [kg]
- W_hyd_pnufloat
Weight of the hydraulics and pneumatics [kg]
- W_instrumentsfloat
Weight of the instruments and navigational equipment [kg]
- W_avionicsfloat
Weight of the avionics [kg]
- W_electricalfloat
Weight of the electrical items [kg]
- W_acfloat
Weight of the air conditioning system [kg]
- W_furnishfloat
Weight of the furnishings in the fuselage [kg]
- W_anti_icefloat
Weight of anti-ice system [kg]
- W_systemsfloat
Total systems weight [kg]
- Return type:
Notes
This function implements the Flight Optimization System (FLOPS) weight estimation methodology for aircraft systems. The calculations are performed in imperial units and converted to metric for output.
- Major Assumptions
No variable sweep (VARSWP = 0)
Hydraulic pressure is 3000 psf (HYDR)
Flight crew is 2 for aircraft with less than 150 passengers, 3 otherwise
References
[1] McCullers, L. A. (1984). “Aircraft Configuration Optimization Including Optimized Flight Profiles”, NASA Symposium on Recent Experiences in Multidisciplinary Analysis and Optimization. [2] Ardema, M. D., Chambers, M. C., Patron, A. P., Hahn, A. S., Miura, H., & Moore, M. D. (1996). “Analytical Fuselage and Wing Weight Estimation of Transport Aircraft”, NASA Technical Memorandum 110392.