Contains some methods for calculating different propulsion system weights.
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| def | SUAVE.Methods.Weights.Correlations.Propulsion.air_cooled_motor.air_cooled_motor (max_power, kwt2=1.96, xwt=.8897) |
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| def | SUAVE.Methods.Weights.Correlations.Propulsion.engine_jet.engine_jet (thrust_sls) |
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| def | SUAVE.Methods.Weights.Correlations.Propulsion.engine_piston.engine_piston (max_power, kwt2=5.22, xwt=.780) |
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| def | SUAVE.Methods.Weights.Correlations.Propulsion.hts_motor.hts_motor (max_power) |
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| def | SUAVE.Methods.Weights.Correlations.Propulsion.integrated_propulsion.integrated_propulsion (engine_jet, num_eng, engine_wt_factor=1.6) |
| | integrated_propulsion.py More...
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| def | SUAVE.Methods.Weights.Correlations.Propulsion.integrated_propulsion_general_aviation.integrated_propulsion_general_aviation (engine_piston, num_eng, engine_wt_factor=2.575, engine_wt_exp=.922) |
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| def | SUAVE.Methods.Weights.Correlations.Propulsion.nasa_motor.nasa_motor (torque, kwt2=.3928, xwt=.8587) |
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Contains some methods for calculating different propulsion system weights.
◆ air_cooled_motor()
| def SUAVE.Methods.Weights.Correlations.Propulsion.air_cooled_motor.air_cooled_motor |
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max_power, |
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kwt2 = 1.96, |
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xwt = .8897 |
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Calculate the weight of an air-cooled motor
weight correlation; weight=kwt2*(max_power**xwt)
Assumptions:
calculated from fit of commercial available motors
Source: Sinsay, J.D., Tracey, B., Alonso, J.J., Kontinos, D.K., Melton, J.E., Grabbe, S.,
"Air Vehicle Design and Technology Considerations for an Electric VTOL Metro-Regional Public Transportation System,"
12th AIAA Aviation Technology, Integration, and Operations (ATIO) Conference and 14th AIAA/ISSMO Multidisciplinary
Analysis and Optimization Conference, Indianapolis, IN, Sept.2012
Inputs:
max_power- maximum power the motor can deliver safely [Watts]
kwt2
xwt
Outputs:
mass- weight of the motor [kilograms]
Properties Used:
N/A
◆ engine_jet()
| def SUAVE.Methods.Weights.Correlations.Propulsion.engine_jet.engine_jet |
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thrust_sls | ) |
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Calculate the weight of the dry engine
Assumptions:
calculated engine weight from a correlation of engines
Source:
N/A
Inputs:
thrust_sls - sea level static thrust of a single engine [Newtons]
Outputs:
weight - weight of the dry engine [kilograms]
Properties Used:
N/A
◆ engine_piston()
| def SUAVE.Methods.Weights.Correlations.Propulsion.engine_piston.engine_piston |
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max_power, |
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kwt2 = 5.22, |
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xwt = .780 |
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weight = SUAVE.Methods.Correlations.Propulsion.air_cooled_motor(max_power)
Calculate the weight of an piston engine
weight correlation; weight=kwt2*(max_power**xwt)
Inputs:
max_power- maximum power the motor can deliver safely [Watts]
kwt2
xwt
Outputs:
weight- weight of the motor [kilograms]
Source: Raymer, Aircraft Design, a Conceptual Approach
◆ hts_motor()
| def SUAVE.Methods.Weights.Correlations.Propulsion.hts_motor.hts_motor |
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max_power | ) |
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Calculate the weight of a high temperature superconducting motor
Assumptions:
calculated from fit of commercial available motors
Source: [10] Snyder, C., Berton, J., Brown, G. et all
'Propulsion Investigation for Zero and Near-Zero Emissions Aircraft,' NASA STI Program,
NASA Glenn, 2009.012. page 12
Inputs:
max_power- maximum power the motor can deliver safely [Watts]
Outputs:
weight- weight of the motor [kilograms]
Properties Used:
N/A
◆ integrated_propulsion()
| def SUAVE.Methods.Weights.Correlations.Propulsion.integrated_propulsion.integrated_propulsion |
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engine_jet, |
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num_eng, |
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engine_wt_factor = 1.6 |
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integrated_propulsion.py
Created: Jan 2014, M. A. Wendorff Modified: Feb 2014, A. Wendorff Feb 2016, E. Botero
Calculate the weight of the entire propulsion system
Assumptions:
The propulsion system is a fixed 60% greater than the dry engine alone.
The propulsion system includes the engines, engine exhaust, reverser, starting,
controls, lubricating, and fuel systems. The nacelle and pylon weight are also
part of this calculation.
Source:
N/A
Inputs:
engine_jet - dry weight of the engine [kilograms]
num_eng - total number of engines on the aircraft [dimensionless]
engine_wt_factor - weight increase factor for entire integrated propulsion system [dimensionless]
Outputs:
weight - weight of the full propulsion system [kilograms]
Properties Used:
N/A
◆ integrated_propulsion_general_aviation()
| def SUAVE.Methods.Weights.Correlations.Propulsion.integrated_propulsion_general_aviation.integrated_propulsion_general_aviation |
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engine_piston, |
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num_eng, |
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engine_wt_factor = 2.575, |
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engine_wt_exp = .922 |
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) |
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Calculate the weight of the entire propulsion system
Source:
Source: Raymer, Aircraft Design, a Conceptual Approach
Inputs:
engine_piston - dry weight of a single engine [kilograms]
num_eng - total number of engines on the aircraft [dimensionless]
engine_wt_factor - weight increase factor for entire integrated propulsion system [dimensionless]
Outputs:
weight - weight of the full propulsion system [kilograms]
◆ nasa_motor()
| def SUAVE.Methods.Weights.Correlations.Propulsion.nasa_motor.nasa_motor |
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torque, |
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kwt2 = .3928, |
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xwt = .8587 |
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) |
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Calculate the weight of an air-cooled motor
weight correlation; weight=kwt2*(max_power**xwt)
Assumptions:
calculated from fit of high power-to-weight motors
Source: NDARC Theory Manual, Page 213
https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20170011656.pdf
Inputs:
torque- maximum torque the motor can deliver safely [N-m]
kwt2
xwt
Outputs:
mass- mass of the motor [kilograms]
Properties Used:
N/A
1.8.15