org.orekit.forces.maneuvers.propulsion

Interface ThrustPropulsionModel

All Superinterfaces:

PropulsionModel

All Known Implementing Classes:

AbstractConstantThrustPropulsionModel, BasicConstantThrustPropulsionModel, ScaledConstantThrustPropulsionModel

public interface ThrustPropulsionModel
extends PropulsionModel

Interface for a thrust-based propulsion model.

Since:

10.2

Author:

Maxime Journot

Method Summary

Modifier and Type	Method and Description
default <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.
default Vector3D	getAcceleration(SpacecraftState s, Attitude maneuverAttitude, double[] parameters) Get the acceleration of the spacecraft during maneuver and in maneuver frame.
default Vector3D	getDirection(SpacecraftState s) Get the thrust direction in spacecraft frame.
<T extends CalculusFieldElement<T>> T	getFlowRate(FieldSpacecraftState<T> s, T[] parameters) Get the flow rate (kg/s).
double	getFlowRate(SpacecraftState s) Get the flow rate (kg/s).
double	getFlowRate(SpacecraftState s, double[] parameters) Get the flow rate (kg/s).
default double	getIsp(SpacecraftState s) Get the specific impulse (s).
default <T extends CalculusFieldElement<T>> T	getMassDerivatives(FieldSpacecraftState<T> s, T[] parameters) Get the mass derivative (i.e.
default double	getMassDerivatives(SpacecraftState s, double[] parameters) Get the mass derivative (i.e.
default double	getThrust(SpacecraftState s) Get the thrust norm (N).
<T extends CalculusFieldElement<T>> FieldVector3D<T>	getThrustVector(FieldSpacecraftState<T> s, T[] parameters) Get the thrust vector in spacecraft frame (N).
Vector3D	getThrustVector(SpacecraftState s) Get the thrust vector in spacecraft frame (N).
Vector3D	getThrustVector(SpacecraftState s, double[] parameters) Get the thrust vector in spacecraft frame (N).

Methods inherited from interface org.orekit.forces.maneuvers.propulsion.PropulsionModel

getName, getParametersDrivers, init

Method Detail

getIsp

default double getIsp(SpacecraftState s)

Get the specific impulse (s).

Parameters:

s - current spacecraft state

Returns:

specific impulse (s).

getDirection

default Vector3D getDirection(SpacecraftState s)

Get the thrust direction in spacecraft frame.

Parameters:

s - current spacecraft state

Returns:

thrust direction in spacecraft frame

getThrust

default double getThrust(SpacecraftState s)

Get the thrust norm (N).

Parameters:

s - current spacecraft state

Returns:

thrust norm (N)

getThrustVector

Vector3D getThrustVector(SpacecraftState s)

Get the thrust vector in spacecraft frame (N).

Parameters:

s - current spacecraft state

Returns:

thrust vector in spacecraft frame (N)

getFlowRate

double getFlowRate(SpacecraftState s)

Get the flow rate (kg/s).

Parameters:

s - current spacecraft state

Returns:

flow rate (kg/s)

getThrustVector

Vector3D getThrustVector(SpacecraftState s,
                         double[] parameters)

Get the thrust vector in spacecraft frame (N).

Parameters:

s - current spacecraft state

parameters - propulsion model parameters

Returns:

thrust vector in spacecraft frame (N)

getFlowRate

double getFlowRate(SpacecraftState s,
                   double[] parameters)

Get the flow rate (kg/s).

Parameters:

s - current spacecraft state

parameters - propulsion model parameters

Returns:

flow rate (kg/s)

getThrustVector

<T extends CalculusFieldElement<T>> FieldVector3D<T> getThrustVector(FieldSpacecraftState<T> s,
                                                                     T[] parameters)

Get the thrust vector in spacecraft frame (N).

Type Parameters:

T - extends CalculusFieldElement<T>

Parameters:

s - current spacecraft state

parameters - propulsion model parameters

Returns:

thrust vector in spacecraft frame (N)

getFlowRate

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

Get the flow rate (kg/s).

Type Parameters:

T - extends CalculusFieldElement<T>

Parameters:

s - current spacecraft state

parameters - propulsion model parameters

Returns:

flow rate (kg/s)

getAcceleration

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

Get the acceleration of the spacecraft during maneuver and in maneuver frame. Acceleration is computed here using the thrust vector in S/C frame.

Specified by:

getAcceleration in interface PropulsionModel

Parameters:

s - current spacecraft state

maneuverAttitude - current attitude in maneuver

parameters - propulsion model parameters

Returns:

acceleration

getAcceleration

default <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. Acceleration is computed here using the thrust vector in S/C frame.

Specified by:

getAcceleration in interface PropulsionModel

Type Parameters:

T - extends CalculusFieldElement<T>

Parameters:

s - current spacecraft state

maneuverAttitude - current attitude in maneuver

parameters - propulsion model parameters

Returns:

acceleration

getMassDerivatives

default double getMassDerivatives(SpacecraftState s,
                                  double[] parameters)

Get the mass derivative (i.e. flow rate in kg/s) during maneuver. Mass derivatives are directly extracted here from the flow rate value.

Specified by:

getMassDerivatives in interface PropulsionModel

Parameters:

s - current spacecraft state

parameters - propulsion model parameters

Returns:

mass derivative in kg/s

getMassDerivatives

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

Get the mass derivative (i.e. flow rate in kg/s) during maneuver. Mass derivatives are directly extracted here from the flow rate value.

Specified by:

getMassDerivatives in interface PropulsionModel

Type Parameters:

T - extends CalculusFieldElement<T>

Parameters:

s - current spacecraft state

parameters - propulsion model parameters

Returns:

mass derivative in kg/s