Package org.orekit.files.ccsds.ndm.odm.ocm

Class TrajectoryState

java.lang.Object

org.orekit.files.ccsds.ndm.odm.ocm.TrajectoryState

All Implemented Interfaces:

TimeStamped

public class TrajectoryState
extends Object
implements TimeStamped

Trajectory state entry.

Since:

11.0

Author:

Luc Maisonobe

Constructor Summary

Constructors

Constructor	Description
TrajectoryState(OrbitElementsType type, AbsoluteDate date, double[] elements)	Simple constructor.
TrajectoryState(OrbitElementsType type, AbsoluteDate date, String[] fields, int first, List<Unit> units)	Simple constructor.

Method Summary

Modifier and Type	Method	Description
CartesianDerivativesFilter	getAvailableDerivatives()	Get which derivatives of position are available in this state.
AbsoluteDate	getDate()	Get the date.
double[]	getElements()	Get trajectory elements.
OrbitElementsType	getType()	Get the type of the elements.
TimeStampedPVCoordinates	toCartesian(OneAxisEllipsoid body, double mu)	Convert to Cartesian coordinates.

Methods inherited from class java.lang.Object

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

Methods inherited from interface org.orekit.time.TimeStamped

durationFrom

Constructor Details

TrajectoryState

public TrajectoryState(OrbitElementsType type,
 AbsoluteDate date,
 String[] fields,
 int first,
 List<Unit> units)

Simple constructor.

Parameters:

type - type of the elements

date - entry date

fields - trajectory elements

first - index of first field to consider when parsing

units - units to use for parsing

TrajectoryState

public TrajectoryState(OrbitElementsType type,
 AbsoluteDate date,
 double[] elements)

Simple constructor.

Parameters:

type - type of the elements

date - entry date

elements - trajectory elements in SI units

Since:

12.0

Method Details

getDate

public AbsoluteDate getDate()

Get the date.

Specified by:

getDate in interface TimeStamped

Returns:

date attached to the object

getElements

public double[] getElements()

Get trajectory elements.

Returns:

trajectory elements

getType

public OrbitElementsType getType()

Get the type of the elements.

Returns:

type of the elements

getAvailableDerivatives

public CartesianDerivativesFilter getAvailableDerivatives()

Get which derivatives of position are available in this state.

Returns:

a value indicating if the file contains velocity and/or acceleration

toCartesian

public TimeStampedPVCoordinates toCartesian(OneAxisEllipsoid body,
 double mu)

Convert to Cartesian coordinates.

Parameters:

body - central body (may be null if type is not OrbitElementsType.GEODETIC)

mu - gravitational parameter in m³/s²

Returns:

Cartesian coordinates