RCAIDE.Library.Methods.Mass_Properties.Weight_Buildups.Conventional.BWB.FLOPS.compute_systems_weight

compute_systems_weight#

compute_systems_weight(vehicle)[source]#

Calculate the system weight of the aircraft using the FLOPS methodology. :param vehicle:

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

  • NPEint

    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:

Data

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.

See also

RCAIDE.Library.Methods.Mass_Properties.Weight_Buildups.Conventional.Transport.FLOPS