org.orekit.forces.maneuvers.propulsion

Class AbstractConstantThrustPropulsionModel

java.lang.Object

org.orekit.forces.maneuvers.propulsion.AbstractConstantThrustPropulsionModel

All Implemented Interfaces:

PropulsionModel, ThrustPropulsionModel, EventDetectorsProvider, ParameterDriversProvider

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

Field Summary

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

DATATION_ACCURACY

Constructor Summary

Constructors

Constructor and Description
AbstractConstantThrustPropulsionModel(double thrust, double isp, org.hipparchus.geometry.euclidean.threed.Vector3D direction, Control3DVectorCostType control3DVectorCostType, String name) Generic constructor.
AbstractConstantThrustPropulsionModel(double thrust, double isp, org.hipparchus.geometry.euclidean.threed.Vector3D direction, String name) Constructor with default control cost type.

Method Summary

Modifier and Type	Method and Description
Control3DVectorCostType	getControl3DVectorCostType() Get the control vector's cost type.
org.hipparchus.geometry.euclidean.threed.Vector3D	getDirection() Get the thrust direction in S/C frame.
org.hipparchus.geometry.euclidean.threed.Vector3D	getDirection(AbsoluteDate date) Get the thrust direction in S/C frame.
abstract double	getFlowRate() Get the flow rate (kg/s).
abstract double	getFlowRate(AbsoluteDate date) Get the flow rate (kg/s).
abstract double	getFlowRate(double[] parameters) Get the flow rate (kg/s).
<T extends org.hipparchus.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 org.hipparchus.CalculusFieldElement<T>> T	getFlowRate(T[] parameters) Get the flow rate (kg/s).
protected double	getInitialFlowRate() Get the initial flow rate.
protected org.hipparchus.geometry.euclidean.threed.Vector3D	getInitialThrustVector() Get the initial thrust vector.
double	getIsp() Get the specific impulse.
double	getIsp(AbsoluteDate date) Get the specific impulse at given date.
String	getName() Get the maneuver name.
double	getThrustMagnitude() Get the thrust magnitude (N).
double	getThrustMagnitude(AbsoluteDate date) Get the thrust magnitude (N) at given date.
abstract org.hipparchus.geometry.euclidean.threed.Vector3D	getThrustVector() Get the thrust vector in spacecraft frame (N).
abstract org.hipparchus.geometry.euclidean.threed.Vector3D	getThrustVector(AbsoluteDate date) Get the thrust vector in spacecraft frame (N).
abstract org.hipparchus.geometry.euclidean.threed.Vector3D	getThrustVector(double[] parameters) Get the thrust vector in spacecraft frame (N).
<T extends org.hipparchus.CalculusFieldElement<T>> org.hipparchus.geometry.euclidean.threed.FieldVector3D<T>	getThrustVector(FieldSpacecraftState<T> s, T[] parameters) Get the thrust vector in spacecraft frame (N).
org.hipparchus.geometry.euclidean.threed.Vector3D	getThrustVector(SpacecraftState s) Get the thrust vector in spacecraft frame (N).
org.hipparchus.geometry.euclidean.threed.Vector3D	getThrustVector(SpacecraftState s, double[] parameters) Get the thrust vector in spacecraft frame (N).
abstract <T extends org.hipparchus.CalculusFieldElement<T>> org.hipparchus.geometry.euclidean.threed.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

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

getEventDetectors, getFieldEventDetectors, init, init

Methods inherited from interface org.orekit.utils.ParameterDriversProvider

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

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

getEventDetectors, getFieldEventDetectors

Constructor Detail

AbstractConstantThrustPropulsionModel

public AbstractConstantThrustPropulsionModel(double thrust,
                                             double isp,
                                             org.hipparchus.geometry.euclidean.threed.Vector3D direction,
                                             Control3DVectorCostType control3DVectorCostType,
                                             String name)

Generic constructor.

Parameters:

thrust - initial thrust value (N)

isp - initial isp value (s)

direction - initial thrust direction in S/C frame

control3DVectorCostType - control cost type

name - name of the maneuver

Since:

12.0

AbstractConstantThrustPropulsionModel

public AbstractConstantThrustPropulsionModel(double thrust,
                                             double isp,
                                             org.hipparchus.geometry.euclidean.threed.Vector3D direction,
                                             String name)

Constructor with default control cost type.

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 org.hipparchus.geometry.euclidean.threed.Vector3D getInitialThrustVector()

Get the initial thrust vector.

Returns:

the initial thrust vector

getInitialFlowRate

protected double getInitialFlowRate()

Get the initial flow rate.

Returns:

the initial flow rate

getName

public String getName()

Get the maneuver name.

Specified by:

getName in interface PropulsionModel

Returns:

the maneuver name

getControl3DVectorCostType

public Control3DVectorCostType getControl3DVectorCostType()

Get the control vector's cost type.

Specified by:

getControl3DVectorCostType in interface PropulsionModel

Returns:

control cost type

getIsp

public double getIsp()

Get the specific impulse.

Returns:

specific impulse (s), will throw exception if used on PDriver having several driven values, because in this case a date is needed.

getIsp

public double getIsp(AbsoluteDate date)

Get the specific impulse at given date.

Parameters:

date - date at which the Isp wants to be known

Returns:

specific impulse (s).

getDirection

public org.hipparchus.geometry.euclidean.threed.Vector3D getDirection(AbsoluteDate date)

Get the thrust direction in S/C frame.

Parameters:

date - date at which the direction wants to be known

Returns:

the thrust direction in S/C frame

getDirection

public org.hipparchus.geometry.euclidean.threed.Vector3D getDirection()

Get the thrust direction in S/C frame.

Returns:

the thrust direction in S/C frame, will throw exception if used on PDriver having several driven values, because in this case a date is needed.

getThrustMagnitude

public double getThrustMagnitude()

Get the thrust magnitude (N).

Returns:

the thrust value (N), will throw an exception if called of a driver having several values driven

getThrustMagnitude

public double getThrustMagnitude(AbsoluteDate date)

Get the thrust magnitude (N) at given date.

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:

the thrust value (N)

getThrustVector

public org.hipparchus.geometry.euclidean.threed.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 org.hipparchus.geometry.euclidean.threed.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 org.hipparchus.CalculusFieldElement<T>> org.hipparchus.geometry.euclidean.threed.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 org.hipparchus.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 org.hipparchus.geometry.euclidean.threed.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), will throw an exception if used on driver containing several value spans

getThrustVector

public abstract org.hipparchus.geometry.euclidean.threed.Vector3D getThrustVector(AbsoluteDate date)

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

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 abstract double getFlowRate()

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

Returns:

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

getFlowRate

public abstract double getFlowRate(AbsoluteDate date)

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

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)

getThrustVector

public abstract org.hipparchus.geometry.euclidean.threed.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 org.hipparchus.CalculusFieldElement<T>> org.hipparchus.geometry.euclidean.threed.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 org.hipparchus.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)