Package org.orekit.propagation.conversion.averaging

Class SGP4OrbitalState

java.lang.Object

org.orekit.propagation.conversion.averaging.AbstractAveragedOrbitalState

org.orekit.propagation.conversion.averaging.SGP4OrbitalState

All Implemented Interfaces:

AveragedOrbitalState, TimeStamped

public class SGP4OrbitalState
extends AbstractAveragedOrbitalState

Class representing an averaged orbital state as in the TLE-related theory. Note it is the averaged mean motion that is written in a Two-Line Element and that, for now, conversions back and forth to averaged semi-major axis are approximated with the osculating ones.

Since:

12.1

Author:

Romain Serra

See Also:

AveragedOrbitalState, TLEPropagator

Constructor Summary

Constructors

Constructor	Description
SGP4OrbitalState(AbsoluteDate date, AveragedKeplerianWithMeanAngle elements)	Constructor with default data context.
SGP4OrbitalState(AbsoluteDate date, AveragedKeplerianWithMeanAngle elements, DataContext dataContext)	Constructor.

Method Summary

Modifier and Type	Method	Description
AveragedKeplerianWithMeanAngle	getAveragedElements()	Getter for the averaged orbital elements.
double	getMu()	Getter for the central body's gravitational constant.
OrbitType	getOrbitType()	Getter for the averaged orbit type.
PositionAngleType	getPositionAngleType()	Getter for the averaged position angle.
static SGP4OrbitalState	of(TLE tle, Frame teme)	Static constructor.
Orbit	toOsculatingOrbit()	Convert instance to an osculating orbit.

Methods inherited from class org.orekit.propagation.conversion.averaging.AbstractAveragedOrbitalState

getDate, getFrame

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 Detail

SGP4OrbitalState

public SGP4OrbitalState(AbsoluteDate date,
                        AveragedKeplerianWithMeanAngle elements,
                        DataContext dataContext)

Constructor.

Parameters:

date - epoch

elements - averaged orbital elements

dataContext - data context

SGP4OrbitalState

@DefaultDataContext
public SGP4OrbitalState(AbsoluteDate date,
                        AveragedKeplerianWithMeanAngle elements)

Constructor with default data context.

Parameters:

date - epoch

elements - averaged orbital elements

Method Detail

of

public static SGP4OrbitalState of(TLE tle,
                                  Frame teme)

Static constructor. Input frame is implicitly assumed to be TEME (it is not checked).

Parameters:

tle - TLE

teme - TEME frame (not checked)

Returns:

TLE-based averaged orbital state

getMu

public double getMu()

Getter for the central body's gravitational constant.

Returns:

gravitational constant

getOrbitType

public OrbitType getOrbitType()

Getter for the averaged orbit type.

Returns:

orbit type

getPositionAngleType

public PositionAngleType getPositionAngleType()

Getter for the averaged position angle.

Returns:

position angle type

getAveragedElements

public AveragedKeplerianWithMeanAngle getAveragedElements()

Getter for the averaged orbital elements.

Returns:

averaged elements

toOsculatingOrbit

public Orbit toOsculatingOrbit()

Convert instance to an osculating orbit.

Returns:

osculating orbit