Package org.orekit.forces.maneuvers.propulsion

Interface ThrustPropulsionModel

All Superinterfaces:

EventDetectorsProvider, ParameterDriversProvider, PropulsionModel

All Known Implementing Classes:

AbstractConstantThrustPropulsionModel, BasicConstantThrustPropulsionModel, ProfileThrustPropulsionModel, ScaledConstantThrustPropulsionModel

public interface ThrustPropulsionModel
extends PropulsionModel

Interface for a thrust-based propulsion model.

Since:

10.2

Author:

Maxime Journot

Field Summary

Fields inherited from interface org.orekit.propagation.events.EventDetectorsProvider

DATATION_ACCURACY

Method Summary

Modifier and Type	Method	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.
static double	getExhaustVelocity(double isp)	Method computing the effective exhaust velocity from the specific impulse.
<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.
<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.propagation.events.EventDetectorsProvider

getDateDetector, getEventDetectors, getFieldDateDetector, getFieldEventDetectors

Methods inherited from interface org.orekit.utils.ParameterDriversProvider

getNbParametersDriversValue, getParameterDriver, getParameters, getParameters, getParameters, getParameters, getParametersAllValues, getParametersAllValues, getParametersDrivers, isSupported

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

getControl3DVectorCostType, getEventDetectors, getFieldEventDetectors, getName, init, init

Method Detail

getExhaustVelocity

static double getExhaustVelocity(double isp)

Method computing the effective exhaust velocity from the specific impulse.

Parameters:

isp - specific impulse (s)

Returns:

effective exhaust velocity (m/s)

Since:

13.0

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.

Return a zero vector if there is no thrust for given spacecraft state.

Parameters:

s - current spacecraft state

Returns:

thrust direction in spacecraft frame

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