RCAIDE.Library.Methods.Powertrain.Converters.Engine.compute_throttle_from_power
compute_throttle_from_power#
- compute_throttle_from_power(engine, conditions)[source]#
Computes engine throttle setting and fuel consumption based on required power output.
- Parameters:
engine (RCAIDE.Library.Components.Propulsors) –
- Engine instance with the following attributes:
- sea_level_powerfloat
Maximum power output at sea level [W]
- flat_rate_altitudefloat
Altitude below which power remains constant [m]
- power_specific_fuel_consumptionfloat
Power specific fuel consumption [kg/(W·s)]
engine_conditions (RCAIDE.Framework.Mission.Common.Conditions) –
- Engine operating conditions with:
- powernumpy.ndarray
Required power output [W]
conditions (RCAIDE.Framework.Mission.Common.Conditions) –
- Flight conditions with:
- freestream.altitudenumpy.ndarray
Current altitude [m]
- freestream.delta_ISAnumpy.ndarray
Temperature offset from standard atmosphere [K]
- Return type:
None
Notes
This function is the inverse of compute_power_from_throttle, calculating the required throttle setting to achieve a desired power output considering atmospheric conditions.
- Major Assumptions
Power varies linearly with density ratio above flat-rate altitude
Power remains constant below flat-rate altitude
Standard atmosphere conditions apply except for ISA temperature offset
Minimum power output is zero (negative values are clipped)
Theory
The power available is computed using:
\[P_{available} = P_{SL} \frac{\sigma - 0.117}{0.883}\]Then throttle is determined by:
\[\text{throttle} = \frac{P_{required}}{P_{available}}\]- where:
\(P_{SL}\) is sea-level power
\(\sigma\) is the density ratio
\(P_{required}\) is the requested power output
References
[1] Gudmundsson, S. (2014). General Aviation Aircraft Design: Applied Methods and Procedures. Butterworth-Heinemann. [2] Gagg and Ferrar