Package org.orekit.forces.maneuvers.propulsion

Class SphericalConstantThrustPropulsionModel

java.lang.Object

org.orekit.forces.maneuvers.propulsion.AbstractConstantThrustPropulsionModel

org.orekit.forces.maneuvers.propulsion.SphericalConstantThrustPropulsionModel

All Implemented Interfaces:

PropulsionModel, ThrustPropulsionModel, EventDetectorsProvider, ParameterDriversProvider

public class SphericalConstantThrustPropulsionModel
extends AbstractConstantThrustPropulsionModel

Constant thrust propulsion model with: - Constant thrust direction in spacecraft frame - Parameter drivers (for estimation) for the thrust vector in spherical coordinates.

Since:

13.1

Author:

Romain Serra

See Also:

BasicConstantThrustPropulsionModel

Field Summary

Fields

Modifier and Type	Field	Description
static String	THRUST_DECLINATION	Parameter name for thrust declination.
static String	THRUST_MAGNITUDE	Parameter name for thrust magnitude.
static String	THRUST_RIGHT_ASCENSION	Parameter name for thrust right ascension.
static double	THRUST_SCALE	Thrust scaling factor.

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

DATATION_ACCURACY

Constructor Summary

Constructors

Constructor	Description
SphericalConstantThrustPropulsionModel(double isp, double thrustMagnitude, Vector3D thrustDirection, String name)	Generic constructor.
SphericalConstantThrustPropulsionModel(double isp, Vector3D thrustVector, String name)	Constructor with thrust vector.

Method Summary

Modifier and Type	Method	Description
double	getFlowRate()	Get the flow rate (kg/s).
double	getFlowRate(double[] parameters)	Get the flow rate (kg/s).
double	getFlowRate(AbsoluteDate date)	Get the flow rate (kg/s).
<T extends CalculusFieldElement<T>> T	getFlowRate(T[] parameters)	Get the flow rate (kg/s).
List<ParameterDriver>	getParametersDrivers()	Get the drivers for parameters.
Vector3D	getThrustVector()	Get the thrust vector in spacecraft frame (N).
Vector3D	getThrustVector(double[] parameters)	Get the thrust vector in spacecraft frame (N).
Vector3D	getThrustVector(AbsoluteDate date)	Get the thrust vector in spacecraft frame (N).
<T extends CalculusFieldElement<T>> FieldVector3D<T>	getThrustVector(T[] parameters)	Get the thrust vector in spacecraft frame (N).

Methods inherited from class org.orekit.forces.maneuvers.propulsion.AbstractConstantThrustPropulsionModel

getControl3DVectorCostType, getDirection, getDirection, getFlowRate, getFlowRate, getFlowRate, getInitialFlowRate, getInitialThrustVector, getIsp, getIsp, getName, getThrustMagnitude, getThrustMagnitude, getThrustVector, getThrustVector, getThrustVector

Methods inherited from class java.lang.Object

clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait

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, isSupported

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

getEventDetectors, getFieldEventDetectors, init, init

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

getAcceleration, getAcceleration, getDirection, getIsp, getMassDerivatives, getMassDerivatives

Field Detail

THRUST_MAGNITUDE

public static final String THRUST_MAGNITUDE

Parameter name for thrust magnitude.

See Also:

Constant Field Values

THRUST_RIGHT_ASCENSION

public static final String THRUST_RIGHT_ASCENSION

Parameter name for thrust right ascension.

See Also:

Constant Field Values

THRUST_DECLINATION

public static final String THRUST_DECLINATION

Parameter name for thrust declination.

See Also:

Constant Field Values

THRUST_SCALE

public static final double THRUST_SCALE

Thrust scaling factor.

We use a power of 2 to avoid numeric noise introduction in the multiplications/divisions sequences.

Constructor Detail

SphericalConstantThrustPropulsionModel

public SphericalConstantThrustPropulsionModel(double isp,
                                              double thrustMagnitude,
                                              Vector3D thrustDirection,
                                              String name)

Generic constructor.

Parameters:

isp - isp (s)

thrustMagnitude - thrust magnitude (N)

thrustDirection - thrust direction in spacecraft frame

name - name of the maneuver

SphericalConstantThrustPropulsionModel

public SphericalConstantThrustPropulsionModel(double isp,
                                              Vector3D thrustVector,
                                              String name)

Constructor with thrust vector.

Parameters:

isp - isp (s)

thrustVector - thrust vector in spacecraft frame (N)

name - name of the maneuver

Method Detail

getThrustVector

public Vector3D getThrustVector()

Get the thrust vector in spacecraft frame (N). Here it does not depend on current S/C state.

Specified by:

getThrustVector in class AbstractConstantThrustPropulsionModel

Returns:

thrust vector in spacecraft frame (N), will throw an exception if used on driver containing several value spans

getThrustVector

public Vector3D getThrustVector(AbsoluteDate date)

Get the thrust vector in spacecraft frame (N). Here it does not depend on current S/C state.

Specified by:

getThrustVector in class AbstractConstantThrustPropulsionModel

Parameters:

date - date at which the thrust vector wants to be known, often the date parameter will not be important and can be whatever if the thrust parameter driver as only value estimated over the all orbit determination interval

Returns:

thrust vector in spacecraft frame (N)

getFlowRate

public double getFlowRate()

Get the flow rate (kg/s). Here it does not depend on current S/C.

Specified by:

getFlowRate in class AbstractConstantThrustPropulsionModel

Returns:

flow rate (kg/s) will throw an exception if used on driver containing several value spans

getFlowRate

public double getFlowRate(AbsoluteDate date)

Get the flow rate (kg/s). Here it does not depend on current S/C.

Specified by:

getFlowRate in class AbstractConstantThrustPropulsionModel

Parameters:

date - date at which the thrust vector wants to be known, often the date parameter will not be important and can be whatever if the thrust parameter driver as only value estimated over the all orbit determination interval

Returns:

flow rate (kg/s)

getParametersDrivers

public List<ParameterDriver> getParametersDrivers()

Get the drivers for parameters.

Returns:

drivers for parameters

getThrustVector

public Vector3D getThrustVector(double[] parameters)

Get the thrust vector in spacecraft frame (N). Here it does not depend on current S/C state.

Specified by:

getThrustVector in class AbstractConstantThrustPropulsionModel

Parameters:

parameters - propulsion model parameters

Returns:

thrust vector in spacecraft frame (N)

getFlowRate

public double getFlowRate(double[] parameters)

Get the flow rate (kg/s). Here it does not depend on current S/C state.

Specified by:

getFlowRate in class AbstractConstantThrustPropulsionModel

Parameters:

parameters - propulsion model parameters

Returns:

flow rate (kg/s)

getThrustVector

public <T extends CalculusFieldElement<T>> FieldVector3D<T> getThrustVector(T[] parameters)

Get the thrust vector in spacecraft frame (N). Here it does not depend on current S/C state.

Specified by:

getThrustVector in class AbstractConstantThrustPropulsionModel

Type Parameters:

T - extends CalculusFieldElement<T>

Parameters:

parameters - propulsion model parameters

Returns:

thrust vector in spacecraft frame (N)

getFlowRate

public <T extends CalculusFieldElement<T>> T getFlowRate(T[] parameters)

Get the flow rate (kg/s). Here it does not depend on current S/C state.

Specified by:

getFlowRate in class AbstractConstantThrustPropulsionModel

Type Parameters:

T - extends CalculusFieldElement<T>

Parameters:

parameters - propulsion model parameters

Returns:

flow rate (kg/s)