Package org.orekit.forces.maneuvers.propulsion

Class BasicConstantThrustPropulsionModel

java.lang.Object

org.orekit.forces.maneuvers.propulsion.AbstractConstantThrustPropulsionModel

org.orekit.forces.maneuvers.propulsion.BasicConstantThrustPropulsionModel

All Implemented Interfaces:

PropulsionModel, ThrustPropulsionModel, EventDetectorsProvider, ParameterDriversProvider

public class BasicConstantThrustPropulsionModel
extends AbstractConstantThrustPropulsionModel

Constant thrust propulsion model with: - Constant thrust direction in spacecraft frame - Parameter drivers (for estimation) for the thrust norm or the flow rate. Note that both parameters CANNOT be selected at the same time since they depend on one another.

Since:

10.2

Author:

Maxime Journot

Field Summary

Fields

Modifier and Type	Field	Description
static final String	FLOW_RATE	Parameter name for flow rate.
static final double	FLOW_RATE_SCALE	Flow rate scaling factor.
static final String	THRUST	Parameter name for thrust.
static final double	THRUST_SCALE	Thrust scaling factor.

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

DATATION_ACCURACY

Constructor Summary

Constructors

Constructor	Description
BasicConstantThrustPropulsionModel(double thrust, double isp, Vector3D direction, String name)	Simple constructor.
BasicConstantThrustPropulsionModel(double thrust, double isp, Vector3D direction, Control3DVectorCostType control3DVectorCostType, String name)	Generic constructor.

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 Details

THRUST

public static final String THRUST

Parameter name for thrust.

See Also:

• Constant Field Values

FLOW_RATE

public static final String FLOW_RATE

Parameter name for flow rate.

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.

FLOW_RATE_SCALE

public static final double FLOW_RATE_SCALE

Flow rate scaling factor.

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

Constructor Details

BasicConstantThrustPropulsionModel

public BasicConstantThrustPropulsionModel(double thrust,
 double isp,
 Vector3D direction,
 Control3DVectorCostType control3DVectorCostType,
 String name)

Generic constructor.

Parameters:

thrust - thrust (N)

isp - isp (s)

direction - direction in spacecraft frame

control3DVectorCostType - control cost type

name - name of the maneuver

Since:

12.0

BasicConstantThrustPropulsionModel

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

Simple constructor.

Parameters:

thrust - thrust (N)

isp - isp (s)

direction - direction in spacecraft frame

name - name of the maneuver

Method Details

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)