Package org.orekit.propagation.integration

Class StateMapper

java.lang.Object

org.orekit.propagation.integration.StateMapper

public abstract class StateMapper
extends Object

This class maps between raw double elements and SpacecraftState instances.

Since:

6.0

Author:

Luc Maisonobe

Constructor Summary

Constructors

Modifier	Constructor	Description
protected	StateMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngle positionAngleType, AttitudeProvider attitudeProvider, Frame frame)	Simple constructor.

Method Summary

Modifier and Type	Method	Description
AttitudeProvider	getAttitudeProvider()	Get the attitude provider.
Frame	getFrame()	Get the inertial frame.
double	getMu()	Get the central attraction coefficient μ.
OrbitType	getOrbitType()	Get propagation parameter type.
PositionAngle	getPositionAngleType()	Get propagation parameter type.
AbsoluteDate	getReferenceDate()	Get reference date.
SpacecraftState	mapArrayToState(double t, double[] y, double[] yDot, boolean meanOnly)	Map the raw double components to a spacecraft state.
abstract SpacecraftState	mapArrayToState(AbsoluteDate date, double[] y, double[] yDot, boolean meanOnly)	Map the raw double components to a spacecraft state.
double	mapDateToDouble(AbsoluteDate date)	Map a date to a raw double time offset.
AbsoluteDate	mapDoubleToDate(double t)	Map the raw double time offset to a date.
AbsoluteDate	mapDoubleToDate(double t, AbsoluteDate date)	Map the raw double time offset to a date.
abstract void	mapStateToArray(SpacecraftState state, double[] y, double[] yDot)	Map a spacecraft state to raw double components.
void	setPositionAngleType()	Set position angle type.

Methods inherited from class java.lang.Object

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

Constructor Detail

StateMapper

protected StateMapper(AbsoluteDate referenceDate,
                      double mu,
                      OrbitType orbitType,
                      PositionAngle positionAngleType,
                      AttitudeProvider attitudeProvider,
                      Frame frame)

Simple constructor.

The position parameter type is meaningful only if propagation orbit type support it. As an example, it is not meaningful for propagation in Cartesian parameters.

Parameters:

referenceDate - reference date

mu - central attraction coefficient (m³/s²)

orbitType - orbit type to use for mapping

positionAngleType - angle type to use for propagation

attitudeProvider - attitude provider

frame - inertial frame

Method Detail

getReferenceDate

public AbsoluteDate getReferenceDate()

Get reference date.

Returns:

reference date

getOrbitType

public OrbitType getOrbitType()

Get propagation parameter type.

Returns:

orbit type used for propagation

setPositionAngleType

public void setPositionAngleType()

Set position angle type.

getPositionAngleType

public PositionAngle getPositionAngleType()

Get propagation parameter type.

Returns:

angle type to use for propagation

getMu

public double getMu()

Get the central attraction coefficient μ.

Returns:

mu central attraction coefficient (m³/s²)

getFrame

public Frame getFrame()

Get the inertial frame.

Returns:

inertial frame

getAttitudeProvider

public AttitudeProvider getAttitudeProvider()

Get the attitude provider.

Returns:

attitude provider

mapDoubleToDate

public AbsoluteDate mapDoubleToDate(double t)

Map the raw double time offset to a date.

Parameters:

t - date offset

Returns:

date

mapDoubleToDate

public AbsoluteDate mapDoubleToDate(double t,
                                    AbsoluteDate date)

Map the raw double time offset to a date.

Parameters:

t - date offset

date - The expected date.

Returns:

date if it is the same time as t to within the lower precision of the latter. Otherwise a new date is returned that corresponds to time t.

mapDateToDouble

public double mapDateToDouble(AbsoluteDate date)

Map a date to a raw double time offset.

Parameters:

date - date

Returns:

time offset

mapArrayToState

public SpacecraftState mapArrayToState(double t,
                                       double[] y,
                                       double[] yDot,
                                       boolean meanOnly)

Map the raw double components to a spacecraft state.

Parameters:

t - date offset

y - state components

yDot - time derivatives of the state components (null if unknown, in which case Keplerian motion is assumed)

meanOnly - use only the mean elements to build the state

Returns:

spacecraft state

mapArrayToState

public abstract SpacecraftState mapArrayToState(AbsoluteDate date,
                                                double[] y,
                                                double[] yDot,
                                                boolean meanOnly)

Map the raw double components to a spacecraft state.

Parameters:

date - of the state components

y - state components

yDot - time derivatives of the state components (null if unknown, in which case Keplerian motion is assumed)

meanOnly - use only the mean elements to build the state

Returns:

spacecraft state

mapStateToArray

public abstract void mapStateToArray(SpacecraftState state,
                                     double[] y,
                                     double[] yDot)

Map a spacecraft state to raw double components.

Parameters:

state - state to map

y - placeholder where to put the components

yDot - placeholder where to put the components derivatives