agi.foundation.stk

Class StkEphemerisFile.CovarianceTimePosVel

java.lang.Object

agi.foundation.stk.StkEphemerisFile.Covariance

agi.foundation.stk.StkEphemerisFile.CovarianceTimePosVel

Enclosing class:

StkEphemerisFile

public static class StkEphemerisFile.CovarianceTimePosVel
extends StkEphemerisFile.Covariance

A class that holds the covariance data in the ephemeris file when the ephemeris file is in the "CovarianceTimePosVel" format.

Constructor Summary

Constructors

Constructor and Description
CovarianceTimePosVel()

Method Summary

Modifier and Type	Method and Description
Covariance6By6TwoBodyBlender	createBlender(StkEphemerisFile.EphemerisTimePosVel orbitStates) Creates a two-body covariance blender from the orbit states ephemeris and the covariance data.
Covariance6By6TwoBodyBlender	createBlender(StkEphemerisFile.EphemerisTimePosVel orbitStates, ReferenceFrame inertialPropagationFrame, Double gravitationalParameter) Creates a two-body covariance blender from the orbit states ephemeris and the covariance data.
Covariance6By6TwoBodyBlender	getBlender() Gets a two-body covariance blender consistent with this covariance data.
DateMotionCollection1<Matrix6By6Symmetric>	getCovarianceData() Gets the covariance data.
StkEphemerisFile.DistanceUnit	getDistanceUnit() Gets the distance unit of the ephemeris and covariance information.
Covariance3By3SizeAndOrientationInterpolator	getInterpolator() Gets the interpolator to use to interpolate this covariance data.
String	getName() Gets the name of this covariance format.
List<JulianDate>	getSegmentBoundaryTimes() Gets the segment boundary times of the data.
List<JulianDate>	getTimes() Gets the times of the data points.
void	setBlender(Covariance6By6TwoBodyBlender value) Sets a two-body covariance blender consistent with this covariance data.
void	setCovarianceData(DateMotionCollection1<Matrix6By6Symmetric> value) Sets the covariance data.
void	setInterpolator(Covariance3By3SizeAndOrientationInterpolator value) Sets the interpolator to use to interpolate this covariance data.

Methods inherited from class agi.foundation.stk.StkEphemerisFile.Covariance

getCoordinateAxes

Methods inherited from class java.lang.Object

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

Constructor Detail

CovarianceTimePosVel

public CovarianceTimePosVel()

Method Detail

getName

public String getName()

Gets the name of this covariance format.

Specified by:

getName in class StkEphemerisFile.Covariance

getTimes

public List<JulianDate> getTimes()

Gets the times of the data points.

Specified by:

getTimes in class StkEphemerisFile.Covariance

getSegmentBoundaryTimes

public List<JulianDate> getSegmentBoundaryTimes()

Gets the segment boundary times of the data.

Specified by:

getSegmentBoundaryTimes in class StkEphemerisFile.Covariance

getDistanceUnit

@Nonnull
public StkEphemerisFile.DistanceUnit getDistanceUnit()

Description copied from class: StkEphemerisFile.Covariance

Gets the distance unit of the ephemeris and covariance information.

Specified by:

getDistanceUnit in class StkEphemerisFile.Covariance

getCovarianceData

public final DateMotionCollection1<Matrix6By6Symmetric> getCovarianceData()

Gets the covariance data.

setCovarianceData

public final void setCovarianceData(DateMotionCollection1<Matrix6By6Symmetric> value)

Sets the covariance data.

getInterpolator

@Nonnull
public Covariance3By3SizeAndOrientationInterpolator getInterpolator()

Description copied from class: StkEphemerisFile.Covariance

Gets the interpolator to use to interpolate this covariance data.

Specified by:

getInterpolator in class StkEphemerisFile.Covariance

setInterpolator

public void setInterpolator(@Nonnull
                            Covariance3By3SizeAndOrientationInterpolator value)

Description copied from class: StkEphemerisFile.Covariance

Sets the interpolator to use to interpolate this covariance data.

Specified by:

setInterpolator in class StkEphemerisFile.Covariance

getBlender

@Nullable
public final Covariance6By6TwoBodyBlender getBlender()

Gets a two-body covariance blender consistent with this covariance data.

setBlender

public final void setBlender(@Nullable
                             Covariance6By6TwoBodyBlender value)

Sets a two-body covariance blender consistent with this covariance data.

createBlender

@Nonnull
public final Covariance6By6TwoBodyBlender createBlender(@Nonnull
                                                                  StkEphemerisFile.EphemerisTimePosVel orbitStates)

Creates a two-body covariance blender from the orbit states ephemeris and the covariance data. Also, sets the Blender (get / set) property to the created value.

The InertialPropagationFrame (get / set) is set to the inertial frame of the instance of EarthCentralBody in the CentralBodiesFacet of the CalculationContext. The GravitationalParameter (get / set) is set to that of the WorldGeodeticSystem1984.

Parameters:

orbitStates - The orbit states that are used for blending. These must be consistent with a spacecraft in a two-body orbital regime for the results to be correct.

Returns:

The created two-body covariance blender.

createBlender

@Nonnull
public final Covariance6By6TwoBodyBlender createBlender(@Nonnull
                                                                  StkEphemerisFile.EphemerisTimePosVel orbitStates,
                                                                  @Nullable
                                                                  ReferenceFrame inertialPropagationFrame,
                                                                  @Nullable
                                                                  Double gravitationalParameter)

Creates a two-body covariance blender from the orbit states ephemeris and the covariance data. Also, sets the Blender (get / set) property to the created value.

Parameters:

orbitStates - The orbit states that are used for blending. These must be consistent with a spacecraft in a two-body orbital regime for the results to be correct.

inertialPropagationFrame - The inertial propagation frame that is used to propagate the orbitStates and the CovarianceData (get / set).

gravitationalParameter - The gravitational parameter of the central body that the spacecraft described by orbitStates is orbiting.

Returns:

The created two-body covariance blender.