Provides structural weight correlations for aircraft components based on the Raymer method.
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| def | SUAVE.Methods.Weights.Correlations.Raymer.fuselage.fuselage_weight_Raymer (vehicle, fuse, settings) |
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| def | SUAVE.Methods.Weights.Correlations.Raymer.landing_gear.landing_gear_Raymer (vehicle) |
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| def | SUAVE.Methods.Weights.Correlations.Raymer.prop_system.total_prop_Raymer (vehicle, prop) |
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| def | SUAVE.Methods.Weights.Correlations.Raymer.prop_system.nacelle_Raymer (vehicle, WENG) |
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| def | SUAVE.Methods.Weights.Correlations.Raymer.prop_system.misc_engine_Raymer (vehicle, prop, WENG) |
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| def | SUAVE.Methods.Weights.Correlations.Raymer.prop_system.fuel_system_Raymer (vehicle, NENG) |
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| def | SUAVE.Methods.Weights.Correlations.Raymer.systems.systems_Raymer (vehicle) |
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| def | SUAVE.Methods.Weights.Correlations.Raymer.tail.tail_vertical_Raymer (vehicle, wing) |
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| def | SUAVE.Methods.Weights.Correlations.Raymer.tail.tail_horizontal_Raymer (vehicle, wing, elevator_fraction=0.4) |
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| def | SUAVE.Methods.Weights.Correlations.Raymer.wing_main_raymer.wing_main_raymer (vehicle, wing) |
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Provides structural weight correlations for aircraft components based on the Raymer method.
◆ fuel_system_Raymer()
| def SUAVE.Methods.Weights.Correlations.Raymer.prop_system.fuel_system_Raymer |
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vehicle, |
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NENG |
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) |
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Calculates the weight of the fuel system based on the Raymer method
Assumptions:
Source:
Aircraft Design: A Conceptual Approach
Inputs:
vehicle - data dictionary with vehicle properties [dimensionless]
-.design_mach_number: design mach number
-.mass_properties.max_zero_fuel: maximum zero fuel weight [kg]
Outputs:
WFSYS: Fuel system weight [kg]
Properties Used:
N/A
◆ fuselage_weight_Raymer()
| def SUAVE.Methods.Weights.Correlations.Raymer.fuselage.fuselage_weight_Raymer |
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vehicle, |
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fuse, |
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settings |
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) |
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Calculate the weight of the fuselage of a transport aircraft based on the Raymer method
Assumptions:
No fuselage mounted landing gear
1 cargo door
Source:
Aircraft Design: A Conceptual Approach (2nd edition)
Inputs:
vehicle - data dictionary with vehicle properties [dimensionless]
-.mass_properties.max_takeoff: MTOW [kg]
-.envelope.ultimate_load: ultimate load factor (default: 3.75)
-.wings['main_wing']: data dictionary with main wing properties
-.taper: wing taper ratio
-.sweeps.quarter_chord: quarter chord sweep [rad]
fuse - data dictionary with specific fuselage properties [dimensionless]
-.lenghts.total: total length [m]
-.width: fuselage width [m]
-.heights.maximum: maximum height of the fuselage [m]
Outputs:
weight_fuse - weight of the fuselage [kilograms]
Properties Used:
N/A
◆ landing_gear_Raymer()
| def SUAVE.Methods.Weights.Correlations.Raymer.landing_gear.landing_gear_Raymer |
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vehicle | ) |
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Calculate the weight of the landing gear of a transport aircraft based on the Raymer method
Assumptions:
No fuselage mounted landing gear
1 cargo door
gear load factor = 3
number of main gear shock struts = 2
stall speed = 51 kts as defined by FAA
Not a reciprocating engine
Source:
Aircraft Design: A Conceptual Approach (2nd edition)
Inputs:
vehicle - data dictionary with vehicle properties [dimensionless]
-.design_range: design range of aircraft [m]
-.mass_properties.max_takeoff: MTOW [kg]
-.systems.accessories: type of aircraft (short-range, commuter
medium-range, long-range,
sst, cargo)
-.landing_gear.main_strut_length: main strut length [m]
-.landing_gear.main_wheels: number of wheels on main landing gear
-.landing_gear.nose_strut_length: nose strut length [m]
-.landing_gear.nose_wheels: number of wheels on nose landing gear
fuse - data dictionary with specific fuselage properties [dimensionless]
Outputs:
weight_fuse - weight of the fuselage [kilograms]
Properties Used:
N/A
◆ misc_engine_Raymer()
| def SUAVE.Methods.Weights.Correlations.Raymer.prop_system.misc_engine_Raymer |
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vehicle, |
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prop, |
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WENG |
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) |
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Calculates the miscellaneous engine weight based on the Raymer method, electrical control system weight
and starter engine weight
Assumptions:
Source:
Aircraft Design: A Conceptual Approach
Inputs:
vehicle - data dictionary with vehicle properties [dimensionless]
-.fuselages['fuselage'].lengths.total: length of fuselage [m]
prop - data dictionary for the specific network that is being estimated [dimensionless]
-.number_of_engines: number of engines
Outputs:
WEC: electrical engine control system weight [kg]
WSTART: starter engine weight [kg]
Properties Used:
N/A
◆ nacelle_Raymer()
| def SUAVE.Methods.Weights.Correlations.Raymer.prop_system.nacelle_Raymer |
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vehicle, |
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WENG |
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) |
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Calculates the nacelle weight based on the Raymer method
Assumptions:
1) All nacelles are identical
2) The number of nacelles is the same as the number of engines
Source:
Aircraft Design: A Conceptual Approach (2nd edition)
Inputs:
vehicle - data dictionary with vehicle properties [dimensionless]
-.ultimate_load: ultimate load factor of aircraft
nacelle - data dictionary for the specific nacelle that is being estimated [dimensionless]
-lenght: total length of engine [m]
-diameter: diameter of nacelle [m]
WENG - dry engine weight [kg]
Outputs:
WNAC: nacelle weight [kg]
Properties Used:
N/A
◆ systems_Raymer()
| def SUAVE.Methods.Weights.Correlations.Raymer.systems.systems_Raymer |
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vehicle | ) |
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Calculates the system weight based on the Raymer method
Assumptions:
Number of flight control systems = 4
Max APU weight = 70 lbs
Assuming not a reciprocating engine and not a turboprop
System Electrical Rating: 60 kv ยท A (typically 40-60 for transports, 110-160 for fighters & bombers)
Uninstalled Avionics weight: 1400 lb (typically= 800-1400 lb)
Source:
Aircraft Design: A Conceptual Approach (2nd edition)
Inputs:
vehicle - data dictionary with vehicle properties [dimensionless]
-.networks: data dictionary containing all propulsion properties
-.number_of_engines: number of engines
-.sealevel_static_thrust: thrust at sea level [N]
-.fuselages['fuselage'].lengths.total: fuselage total length [meters]
-.fuselages['fuselage'].width: fuselage width [meters]
-.fuselages['fuselage'].heights.maximum: fuselage maximum height[meters]
-.mass_properties.max_takeoff: MTOW [kilograms]
-.design_mach_number: design mach number for cruise flight
-.design_range: design range of aircraft [nmi]
-.passengers: number of passengers in aircraft
-.wings['main_wing']: data dictionary with main wing properties
-.sweeps.quarter_chord: quarter chord sweep [deg]
-.areas.reference: wing surface area [m^2]
-.spans.projected: projected span of wing [m]
-.flap_ratio: flap surface area over wing surface area
-.payload: payload weight of aircraft [kg]
Outputs:
output - a data dictionary with fields:
wt_flt_ctrl - weight of the flight control system [kilograms]
wt_apu - weight of the apu [kilograms]
wt_hyd_pnu - weight of the hydraulics and pneumatics [kilograms]
wt_instruments - weight of the instruments and navigational equipment [kilograms]
wt_avionics - weight of the avionics [kilograms]
wt_elec - weight of the electrical items [kilograms]
wt_ac - weight of the air conditioning and anti-ice system [kilograms]
wt_furnish - weight of the furnishings in the fuselage [kilograms]
wt_anti_ice - weight of anti-ice system [kilograms]
Properties Used:
N/A
◆ tail_horizontal_Raymer()
| def SUAVE.Methods.Weights.Correlations.Raymer.tail.tail_horizontal_Raymer |
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vehicle, |
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wing, |
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elevator_fraction = 0.4 |
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) |
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Calculates horizontal tail weight based on Raymer method
Assumptions:
If all-moving horizontal tail, change Kuht to 1.143
Source:
Aircraft Design: A Conceptual Approach
Inputs:
vehicle - data dictionary with vehicle properties [dimensionless]
-.mass_properties.max_takeoff: MTOW [kilograms]
-.envelope.ultimate_load: ultimate load factor (default: 3.75)
-.wings['main_wing']: data dictionary with properties of main wing
-.aerodynamic_center: aerodynamic center as measured from root leading edge
-.origin: root of main wing as measured from nose of aircraft
-.fuselages['fuselage'].width: width of the fuselage
wing - data dictionary with specific tail properties [dimensionless]
-.areas.reference: tail surface area [m^2}
-.origin: location of tail measured from nose
-.aerodynamic_center: location of ac measured from leading edge
-.sweeps.quarter_chord: quarter chord sweep of tail [rad]
-.thickness_to_chord: t/c of tail
-.span.projected: project span of tail [m]
-.aspect_ratio: aspect ratio of wing
elevator_fraction - fraction of horizontal tail for elevator = 0.4
Outputs:
tail_weight: horizontal tail weight [kilograms]
Properties Used:
N/A
◆ tail_vertical_Raymer()
| def SUAVE.Methods.Weights.Correlations.Raymer.tail.tail_vertical_Raymer |
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vehicle, |
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wing |
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Calculates vertical tail weight based on Raymer method
Assumptions:
Source:
Aircraft Design: A Conceptual Approach (2nd edition)
Inputs:
vehicle - data dictionary with vehicle properties [dimensionless]
-.mass_properties.max_takeoff: MTOW [kilograms]
-.envelope.ultimate_load: ultimate load factor (default: 3.75)
-.wings['main_wing']: data dictionary with properties of main wing
-.aerodynamic_center: aerodynamic center as measured from root leading edge
-.origin: root of main wing as measured from nose of aircraft
wing - data dictionary with specific tail properties [dimensionless]
-.areas.reference: tail surface area [m^2}
-.origin: location of tail measured from nose
-.aerodynamic_center: location of ac measured from leading edge
-.sweeps.quarter_chord: quarter chord sweep of tail [rad]
-.thickness_to_chord: t/c of tail
Outputs:
tail_weight: vertical tail weight [kilograms]
Properties Used:
N/A
◆ total_prop_Raymer()
| def SUAVE.Methods.Weights.Correlations.Raymer.prop_system.total_prop_Raymer |
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vehicle, |
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prop |
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Calculate the weight of propulsion system using Raymer method, including:
- fuel system weight
- thurst reversers weight
- electrical system weight
- starter engine weight
- nacelle weight
- cargo containers
The dry engine weight comes from the FLOPS relations since it is not listed in Raymer
Assumptions:
Source:
Aircraft Design: A Conceptual Approach
Inputs:
vehicle - data dictionary with vehicle properties [dimensionless]
prop - data dictionary for the specific network that is being estimated [dimensionless]
Outputs:
output - data dictionary with weights [kilograms]
- output.wt_prop: total propulsive system weight
- output.wt_thrust_reverser: thurst reverser weight
- output.starter: starter engine weight
- output.wt_engine_controls: engine controls weight
- output.fuel_system: fuel system weight
- output.nacelle: nacelle weight
- output.wt_eng: dry engine weight
Properties Used:
N/A
◆ wing_main_raymer()
| def SUAVE.Methods.Weights.Correlations.Raymer.wing_main_raymer.wing_main_raymer |
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vehicle, |
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wing |
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Calculate the wing weight of the aircraft based the Raymer method
Assumptions:
Source:
Aircraft Design: A Conceptual Approach (2nd edition)
Inputs:
vehicle - data dictionary with vehicle properties [dimensionless]
-.mass_properties.max_takeoff: MTOW [kg]
-.envelope.ultimate_load: ultimate loading factor
-.systems.accessories: type of aircraft (short-range, commuter
medium-range, long-range,
sst, cargo)
wing - data dictionary with specific wing properties [dimensionless]
-.taper: taper ratio
-.sweeps.quarter_chord: quarter chord sweep angle [deg]
-.thickness_to_chord: thickness to chord
-.aspect_ratio: aspect ratio of wing
-.areas.reference: wing surface area [m^2]
Outputs:
weight - weight of the wing [kilograms]
Properties Used:
N/A
1.8.15