org.orekit.forces.maneuvers.propulsion

Interface PropulsionModel

All Known Subinterfaces:

ThrustPropulsionModel

All Known Implementing Classes:

AbstractConstantThrustPropulsionModel, BasicConstantThrustPropulsionModel, ScaledConstantThrustPropulsionModel

public interface PropulsionModel

Generic interface for a propulsion model used in a Maneuver.

Since:

10.2

Author:

Maxime Journot

Method Summary

Modifier and Type	Method and Description
<T extends CalculusFieldElement<T>> FieldVector3D<T>	getAcceleration(FieldSpacecraftState<T> s, FieldAttitude<T> maneuverAttitude, T[] parameters) Get the acceleration of the spacecraft during maneuver and in maneuver frame.
Vector3D	getAcceleration(SpacecraftState s, Attitude maneuverAttitude, double[] parameters) Get the acceleration of the spacecraft during maneuver and in maneuver frame.
<T extends CalculusFieldElement<T>> T	getMassDerivatives(FieldSpacecraftState<T> s, T[] parameters) Get the mass derivative (i.e.
double	getMassDerivatives(SpacecraftState s, double[] parameters) Get the mass derivative (i.e.
default String	getName() Get the maneuver name.
default List<ParameterDriver>	getParametersDrivers() Get the propulsion model parameter drivers.
default <T extends CalculusFieldElement<T>> void	init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target) Initialization method.
default void	init(SpacecraftState initialState, AbsoluteDate target) Initialization method.

Method Detail

init

default void init(SpacecraftState initialState,
                  AbsoluteDate target)

Initialization method. Called in when Maneuver.init(...) is called (from ForceModel.init(...))

Parameters:

initialState - initial spacecraft state (at the start of propagation).

target - date of propagation. Not equal to initialState.getDate().

init

default <T extends CalculusFieldElement<T>> void init(FieldSpacecraftState<T> initialState,
                                                      FieldAbsoluteDate<T> target)

Initialization method. Called in when Maneuver.init(...) is called (from ForceModel.init(...))

Type Parameters:

T - type of the elements

Parameters:

initialState - initial spacecraft state (at the start of propagation).

target - date of propagation. Not equal to initialState.getDate().

Since:

11.1

getAcceleration

Vector3D getAcceleration(SpacecraftState s,
                         Attitude maneuverAttitude,
                         double[] parameters)

Get the acceleration of the spacecraft during maneuver and in maneuver frame.

Parameters:

s - current spacecraft state

maneuverAttitude - current attitude in maneuver

parameters - propulsion model parameters

Returns:

acceleration

getAcceleration

<T extends CalculusFieldElement<T>> FieldVector3D<T> getAcceleration(FieldSpacecraftState<T> s,
                                                                     FieldAttitude<T> maneuverAttitude,
                                                                     T[] parameters)

Get the acceleration of the spacecraft during maneuver and in maneuver frame.

Type Parameters:

T - extends CalculusFieldElement<T>

Parameters:

s - current spacecraft state

maneuverAttitude - current attitude in maneuver

parameters - propulsion model parameters

Returns:

acceleration

getMassDerivatives

double getMassDerivatives(SpacecraftState s,
                          double[] parameters)

Get the mass derivative (i.e. flow rate in kg/s) during maneuver.

Parameters:

s - current spacecraft state

parameters - propulsion model parameters

Returns:

mass derivative in kg/s

getMassDerivatives

<T extends CalculusFieldElement<T>> T getMassDerivatives(FieldSpacecraftState<T> s,
                                                         T[] parameters)

Get the mass derivative (i.e. flow rate in kg/s) during maneuver.

Type Parameters:

T - extends CalculusFieldElement<T>

Parameters:

s - current spacecraft state

parameters - propulsion model parameters

Returns:

mass derivative in kg/s

getParametersDrivers

default List<ParameterDriver> getParametersDrivers()

Get the propulsion model parameter drivers.

Returns:

propulsion model parameter drivers

getName

default String getName()

Get the maneuver name.

Returns:

the maneuver name