RCAIDE.Library.Methods.Mass_Properties.Weight_Buildups.Conventional.BWB.FLOPS.compute_bwb_wing_weight
compute_bwb_wing_weight#
Functions
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Returns load factor assuming elliptical load distribution |
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Calculate the wing weight based on the flops method. The wing weight consists of: |
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Determine chord at wing and fuselage intersection |
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Finds sweep angle for a certain y-location along the wing |
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Divides half of the wing in integration stations |
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Divides half the wing in sections, using the defined sections |
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Returns EETA for the engine locations along the wing |
Defines wing weight constants as defined by FLOPS Inputs: ac_type - determines type of instruments, electronics, and operating items based on types: "short-range", "medium-range", "long-range", "business", "cargo", "commuter", "sst" Outputs: list of coefficients used in weight estimations |
- compute_wing_weight(vehicle, wing, WPOD, fidelity, settings, num_main_wings)[source]#
- Calculate the wing weight based on the flops method. The wing weight consists of:
Total Wing Shear Material and Control Surface Weight
Total Wing Miscellaneous Items Weight
Total Wing Bending Material Weight
- Assumptions:
Wing is elliptically loaded Gloved wing area is 0 Load between multiple main wings is distributed equally Wing sweep is fixed
- Source:
The Flight Optimization System Weight Estimation Method
- Inputs:
- vehicle - data dictionary with vehicle properties [dimensionless]
-.reference_area: wing surface area [m^2] -.mass_properties.max_takeoff: MTOW [kilograms] -.flight_envelope.ultimate_load: ultimate load factor (default: 3.75) -.systems.accessories: type of aircraft (short-range, commuter
medium-range, long-range, sst, cargo)
-.fuselages.fuselage.width: width of the fuselage [m]
- -wing: data dictionary with wing properties
-.taper: taper ratio -.sweeps.quarter_chord: quarter chord sweep angle [deg] -.thickness_to_chord: thickness to chord -.spans.projected: wing span [m] -.chords.root: root chord [m] -.tip.root: tip chord [m] -.twists.root: twist of wing at root [deg] -.twists.tip: twist of wing at tip [deg] -.flap_ratio: flap surface area over wing surface area
- -.networks: data dictionary containing all propulsion properties
-.number_of_engines: number of engines -.sealevel_static_thrust: thrust at sea level [N]
WPOD - weight of engine pod including the nacelle [kilograms] fidelity - “simple” or “complex” depending on the wing weight method chosen
- Outputs:
WWING - wing weight [kilograms]
- Properties Used:
N/A
- generate_wing_stations(fuselage_width, wing)[source]#
- Divides half the wing in sections, using the defined sections
and adding a section at the intersection of wing and fuselage
Assumptions:
- Source:
The Flight Optimization System Weight Estimation Method
- Inputs:
fuselage_width: fuselage width [m] wing: data dictionary with wing properties
-.taper: taper ration wing -.sweeps.quarter_chord: quarter chord sweep angle [deg] -.thickness_to_chord: thickness to chord -.spans.projected: wing span [m] -.chords.root: root chord [m] -.tip.root: tip chord [m] -.twists.root: twist of wing at root [deg] -.twists.tip: twist of wing at tip [deg] -.Segments: trapezoidal segments of the wing
- Outputs:
ETA: spanwise location of the sections normalized by half span C: chord lengths at every spanwise location in ETA normalized by half span T: thickness to chord ratio at every span wise location in ETA SWP: quarter chord sweep angle at every span wise location in ETA
- Properties Used:
N/A
- generate_int_stations(NSD, ETA)[source]#
Divides half of the wing in integration stations
Assumptions:
- Source:
The Flight Optimization System Weight Estimation Method
- Inputs:
NSD: number of integration stations requested ETA: list of spanwise locations of all sections of the wing
- Outputs:
NS: actual number of integration stations Y: spanwise locations of the integrations stations normalized by half span
- Properties Used:
N/A
- calculate_load(ETA)[source]#
Returns load factor assuming elliptical load distribution
Assumptions:
- Source:
The Flight Optimization System Weight Estimation Method
- Inputs:
ETA: list of spanwise locations of all sections of the wing
- Outputs:
PS: load factor at every location in ETA assuming elliptical load distribution
- Properties Used:
N/A
- find_sweep(y, lst_y, swp)[source]#
Finds sweep angle for a certain y-location along the wing
Assumptions:
- Source:
The Flight Optimization System Weight Estimation Method
- Inputs:
y: spanwise location lst_y: list of spanwise stations where sweep is known (eg sections) swp: list of quarter chord sweep angles at the locations listed in lst_y
- Outputs:
swps: sweep angle at y
- Properties Used:
N/A
- get_spanwise_engine(networks, SEMISPAN)[source]#
Returns EETA for the engine locations along the wing
Assumptions:
- Source:
The Flight Optimization System Weight Estimation Method
- Inputs:
- networks: data dictionary with all the engine properties
-.wing_mounted: list of boolean if engine is mounted to wing -.number_of_engines: number of engines -.origin: origin of the engine
SEMISPAN: half span [m]
- Outputs:
EETA: span wise locations of the engines mounted to the wing normalized by the half span
- Properties Used:
N/A
- wing_weight_constants_FLOPS()[source]#
Defines wing weight constants as defined by FLOPS Inputs: ac_type - determines type of instruments, electronics, and operating items based on types:
“short-range”, “medium-range”, “long-range”, “business”, “cargo”, “commuter”, “sst”
Outputs: list of coefficients used in weight estimations
- determine_fuselage_chord(fuselage_width, wing)[source]#
Determine chord at wing and fuselage intersection
- Assumptions:
Fuselage side of body is between first and second wing segments.
- Source:
The Flight Optimization System Weight Estimation Method
- Inputs:
fuselage_width: width of fuselage [m] wing: data dictionary with wing properties
-.taper: taper ratio -.sweeps.quarter_chord: quarter chord sweep angle [deg] -.thickness_to_chord: thickness to chord -.spans.projected: wing span [m] -.chords.root: root chord [m]
-.fuselages.fuselage.width: fuselage width [m]
- Outputs:
chord: chord length of wing where wing intersects the fuselage wall [ft]
- Properties Used:
N/A