org.orekit.forces.maneuvers.propulsion

Class AbstractConstantThrustPropulsionModel

java.lang.Object

org.orekit.forces.maneuvers.propulsion.AbstractConstantThrustPropulsionModel

All Implemented Interfaces:

PropulsionModel, ThrustPropulsionModel

Direct Known Subclasses:

BasicConstantThrustPropulsionModel, ScaledConstantThrustPropulsionModel

public abstract class AbstractConstantThrustPropulsionModel
extends Object
implements ThrustPropulsionModel

This abstract class simply serve as a container for a constant thrust maneuver. It re-writes all spacecraft dependent methods from ThrustPropulsionModel and removes their dependencies to current spacecraft state. Indeed since the thrust is constant (i.e. not variable during the maneuver), most of the calculated parameters (thrust vector, flow rate etc.) do not depend on current spacecraft state.

Since:

10.2

Author:

Maxime Journot

Constructor Summary

Constructors

Constructor and Description
AbstractConstantThrustPropulsionModel(double thrust, double isp, Vector3D direction, String name) Generic constructor.

Method Summary

Modifier and Type	Method and Description
Vector3D	getDirection() Get the thrust direction in S/C frame.
abstract double	getFlowRate() Get the flow rate (kg/s).
abstract double	getFlowRate(double[] parameters) Get the flow rate (kg/s).
<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).
abstract <T extends CalculusFieldElement<T>> T	getFlowRate(T[] parameters) Get the flow rate (kg/s).
protected double	getInitialFlowrate()
protected Vector3D	getInitialThrustVector()
double	getIsp() Get the specific impulse.
String	getName() Get the maneuver name.
double	getThrust() Get the thrust value (N).
abstract Vector3D	getThrustVector() Get the thrust vector in spacecraft frame (N).
abstract Vector3D	getThrustVector(double[] parameters) Get the thrust vector in spacecraft frame (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).
abstract <T extends CalculusFieldElement<T>> FieldVector3D<T>	getThrustVector(T[] parameters) Get the thrust vector in spacecraft frame (N).

Methods inherited from class java.lang.Object

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

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

getAcceleration, getAcceleration, getDirection, getIsp, getMassDerivatives, getMassDerivatives, getThrust

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

getParametersDrivers, init

Constructor Detail

AbstractConstantThrustPropulsionModel

public AbstractConstantThrustPropulsionModel(double thrust,
                                             double isp,
                                             Vector3D direction,
                                             String name)

Generic constructor.

Parameters:

thrust - initial thrust value (N)

isp - initial isp value (s)

direction - initial thrust direction in S/C frame

name - name of the maneuver

Method Detail

getInitialThrustVector

protected Vector3D getInitialThrustVector()

getInitialFlowrate

protected double getInitialFlowrate()

getName

public String getName()

Get the maneuver name.

Specified by:

getName in interface PropulsionModel

Returns:

the maneuver name

getIsp

public double getIsp()

Get the specific impulse.

Returns:

specific impulse (s).

getDirection

public Vector3D getDirection()

Get the thrust direction in S/C frame.

Returns:

the thrust direction in S/C frame

getThrust

public double getThrust()

Get the thrust value (N).

Returns:

the thrust value (N)

getThrustVector

public Vector3D getThrustVector(SpacecraftState s)

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

Specified by:

getThrustVector in interface ThrustPropulsionModel

Parameters:

s - current spacecraft state

Returns:

thrust vector in spacecraft frame (N)

getFlowRate

public double getFlowRate(SpacecraftState s)

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

Specified by:

getFlowRate in interface ThrustPropulsionModel

Parameters:

s - current spacecraft state

Returns:

flow rate (kg/s)

getThrustVector

public Vector3D getThrustVector(SpacecraftState s,
                                double[] parameters)

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

Specified by:

getThrustVector in interface ThrustPropulsionModel

Parameters:

s - current spacecraft state

parameters - propulsion model parameters

Returns:

thrust vector in spacecraft frame (N)

getFlowRate

public double getFlowRate(SpacecraftState s,
                          double[] parameters)

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

Specified by:

getFlowRate in interface ThrustPropulsionModel

Parameters:

s - current spacecraft state

parameters - propulsion model parameters

Returns:

flow rate (kg/s)

getThrustVector

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

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

Specified by:

getThrustVector in interface ThrustPropulsionModel

Type Parameters:

T - extends CalculusFieldElement<T>

Parameters:

s - current spacecraft state

parameters - propulsion model parameters

Returns:

thrust vector in spacecraft frame (N)

getFlowRate

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

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

Specified by:

getFlowRate in interface ThrustPropulsionModel

Type Parameters:

T - extends CalculusFieldElement<T>

Parameters:

s - current spacecraft state

parameters - propulsion model parameters

Returns:

flow rate (kg/s)

getThrustVector

public abstract Vector3D getThrustVector()

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

Returns:

thrust vector in spacecraft frame (N)

getFlowRate

public abstract double getFlowRate()

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

Returns:

flow rate (kg/s)

getThrustVector

public abstract Vector3D getThrustVector(double[] parameters)

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

Parameters:

parameters - propulsion model parameters

Returns:

thrust vector in spacecraft frame (N)

getFlowRate

public abstract double getFlowRate(double[] parameters)

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

Parameters:

parameters - propulsion model parameters

Returns:

flow rate (kg/s)

getThrustVector

public abstract <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.

Type Parameters:

T - extends CalculusFieldElement<T>

Parameters:

parameters - propulsion model parameters

Returns:

thrust vector in spacecraft frame (N)

getFlowRate

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

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

Type Parameters:

T - extends CalculusFieldElement<T>

Parameters:

parameters - propulsion model parameters

Returns:

flow rate (kg/s)