RCAIDE.Library.Methods.Mass_Properties.Weight_Buildups.Cryogenic.Common.compute_propulsion_system_weight

compute_propulsion_system_weight#

compute_propulsion_system_weight(vehicle, ref_propulsor, settings)[source]#

Calculate the weight of propulsion system, including: - dry engine weight - fuel system weight - thurst reversers weight - electrical system weight - starter engine weight - nacelle weight - cargo containers

Assumptions:

  1. Rated thrust per scaled engine and rated thurst for baseline are the same

  2. Engine weight scaling parameter is 1.15

  3. Enginge inlet weight scaling exponent is 1

  4. Baseline inlet weight is 0 lbs as in example files FLOPS

  5. Baseline nozzle weight is 0 lbs as in example files FLOPS

Source:

The Flight Optimization System Weight Estimation Method

Inputs:
vehicle - data dictionary with vehicle properties [dimensionless]

-.design_mach_number: design mach number for cruise flight -.systems.accessories: type of aircraft (short-range, commuter

medium-range, long-range, sst, cargo)

nacelle - data dictionary with propulsion system properties

-.diameter: diameter of nacelle [meters] -.length: length of complete engine assembly [meters]

ref_propulsor.

-.sealevel_static_thrust: thrust at sea level [N]

Outputs:
output - data dictionary with weights [kilograms]

  • output.W_prop: total propulsive system weight

  • output.W_thrust_reverser: thurst reverser weight

  • output.starter: starter engine weight

  • output.W_engine_controls: engine controls weight

  • output.fuel_system: fuel system weight

  • output.nacelle: nacelle weight

  • output.W_engine: dry engine weight

Properties Used:

N/A

compute_fuel_system_weight(vehicle, NENG, settings)[source]#

Calculates the weight of the fuel system based on Wess ****update l Source:

The Flight Optimization System Weight Estimation Method

Inputs:
vehicle - data dictionary with vehicle properties [dimensionless]

-.design_mach_number: design mach number - [kg]

Outputs:

WFSYS: Fuel system weight [kg]

Properties Used:

N/A

compute_nacelle_weight(ref_propulsor, ref_nacelle, NENG)[source]#

Calculates the nacelle weight based on the FLOPS method

Assumptions:

  1. All nacelles are identical

  2. The number of nacelles is the same as the number of engines

Source:

The Flight Optimization System Weight Estimation Method

Inputs:
ref_propulsor - data dictionary for the specific network that is being estimated [dimensionless]

-.number_of_engines: number of engines -.engine_lenght: total length of engine [m] -.sealevel_static_thrust: sealevel static thrust of engine [N]

nacelle.

-.diameter: diameter of nacelle [m]

WENG - dry engine weight [kg]

Outputs:

WNAC: nacelle weight [kg]

Properties Used:

N/A

compute_thrust_reverser_weight(ref_propulsor, NENG)[source]#

Calculates the weight of the thrust reversers of the aircraft

Assumptions:

Source:

The Flight Optimization System Weight Estimation Method

Inputs:
ref_propulsor - data dictionary for the specific network that is being estimated [dimensionless]

-.number_of_engines: number of engines -.sealevel_static_thrust: sealevel static thrust of engine [N]

Outputs:

WTHR: Thrust reversers weight [kg]

Properties Used:

N/A

compute_misc_propulsion_system_weight(vehicle, ref_propulsor, ref_nacelle, NENG)[source]#

Calculates the miscellaneous engine weight based on the FLOPS method, electrical control system weight and starter engine weight

Assumptions:

  1. All nacelles are identical

  2. The number of nacelles is the same as the number of engines

Source:

The Flight Optimization System Weight Estimation Method

Inputs:
vehicle - data dictionary with vehicle properties [dimensionless]

-.design_mach_number: design mach number

ref_propulsor - data dictionary for the specific network that is being estimated [dimensionless]

-.number_of_engines: number of engines -.sealevel_static_thrust: sealevel static thrust of engine [N]

nacelle

-.diameter: diameter of nacelle [m]

Outputs:

WEC: electrical engine control system weight [kg] WSTART: starter engine weight [kg]

Properties Used:

N/A

compute_engine_weight(vehicle, ref_propulsor)[source]#

Calculates the dry engine weight based on the FLOPS method Assumptions:

Rated thrust per scaled engine and rated thurst for baseline are the same Engine weight scaling parameter is 1.15 Enginge inlet weight scaling exponent is 1 Baseline inlet weight is 0 lbs as in example files FLOPS Baseline nozzle weight is 0 lbs as in example files FLOPS

Source:

The Flight Optimization System Weight Estimation Method

Inputs:
vehicle - data dictionary with vehicle properties [dimensionless]
-.systems.accessories: type of aircraft (short-range, commuter

medium-range, long-range, sst, cargo)

ref_propulsor - data dictionary for the specific network that is being estimated [dimensionless]

-.sealevel_static_thrust: sealevel static thrust of engine [N]

Outputs:

WENG: dry engine weight [kg]

Properties Used:

N/A