fastga.models.propulsion.fuel_propulsion.base module

Base classes for fuel-consuming propulsion models.

class fastga.models.propulsion.fuel_propulsion.base.AbstractFuelPropulsion[source]

Bases: fastga.models.propulsion.propulsion.IPropulsionCS23, abc.ABC

Propulsion model that consume any fuel should inherit from this one.

In inheritors, compute_flight_points() is expected to define “sfc” and “thrust” in computed FlightPoint instances.

get_consumed_mass(flight_point: fastoad.model_base.flight_point.FlightPoint, time_step: float) → float[source]

Computes consumed mass for provided flight point and time step.

This method should rely on FlightPoint fields that are generated by :meth: compute_flight_points.

Parameters

  • flight_point –

  • time_step –

Returns

the consumed mass in kg

abstract compute_dimensions()[source]

Computes propulsion sub-components dimensions.

class fastga.models.propulsion.fuel_propulsion.base.FuelEngineSet(engine: fastga.models.propulsion.propulsion.IPropulsionCS23, engine_count)[source]

Bases: fastga.models.propulsion.fuel_propulsion.base.AbstractFuelPropulsion

Class for modelling an assembly of identical fuel engines.

Thrust is supposed equally distributed among them.

Parameters

  • engine – the engine model

  • engine_count –

compute_flight_points(flight_points: Union[fastoad.model_base.flight_point.FlightPoint, pandas.core.frame.DataFrame])[source]

Computes Specific Fuel Consumption according to provided conditions.

See FlightPoint for available fields that may be used for computation. If a DataFrame instance is provided, it is expected that its columns match field names of FlightPoint (actually, the DataFrame instance should be generated from a list of FlightPoint instances).

Note

About thrust_is_regulated, thrust_rate and thrust

thrust_is_regulated tells if a flight point should be computed using thrust_rate (when False) or thrust (when True) as input. This way, the method can be used in a vectorized mode, where each point can be set to respect a thrust order or a thrust rate order.

  • if thrust_is_regulated is not defined, the considered input will be the defined one between thrust_rate and thrust (if both are provided, thrust_rate will be used)

  • if thrust_is_regulated is True or False (i.e., not a sequence), the considered input will be taken accordingly, and should of course be defined.

  • if there are several flight points, thrust_is_regulated is a sequence or array, thrust_rate and thrust should be provided and have the same shape as thrust_is_regulated:code:. The method will consider for each element which input will be used according to thrust_is_regulated.

Parameters

flight_points – FlightPoint or DataFram instance

Returns

None (inputs are updated in-place)

compute_max_power(flight_points: Union[fastoad.model_base.flight_point.FlightPoint, pandas.core.frame.DataFrame])[source]

Computes max available power on one engine.

Returns

the maximum available power in W

compute_weight()[source]

Computes total propulsion mass.

Returns

the total uninstalled mass in kg

compute_dimensions()[source]

Computes propulsion sub-components dimensions.

compute_drag(mach, unit_reynolds, wing_mac)[source]

Computes nacelle drag force for out of fuselage engine.

Parameters

  • mach – mach at which drag should be calculated

  • unit_reynolds – unitary Reynolds for calculation

  • wing_mac – wing MAC length in m

Returns

drag force cd0*wing_area