Package org.orekit.propagation.semianalytical.dsst.utilities

Class AuxiliaryElements

java.lang.Object

org.orekit.propagation.semianalytical.dsst.utilities.AuxiliaryElements

public class AuxiliaryElements
extends Object

Container class for common parameters used by all DSST forces.

Most of them are defined in Danielson paper at § 2.1.

Author:

Pascal Parraud

Constructor Summary

Constructors

Constructor	Description
AuxiliaryElements(Orbit orbit, int retrogradeFactor)	Simple constructor.

Method Summary

Modifier and Type	Method	Description
double	getB()	Get B = sqrt(1 - e²).
double	getC()	Get C = 1 + p² + q².
AbsoluteDate	getDate()	Get the date of the orbit.
double	getEcc()	Get the eccentricity.
Frame	getFrame()	Get the definition frame of the orbit.
double	getH()	Get the y component of eccentricity vector.
double	getK()	Get the x component of eccentricity vector.
double	getKeplerianPeriod()	Get the Keplerian period.
double	getLf()	Get the eccentric longitude.
double	getLM()	Get the mean longitude.
double	getLv()	Get the true longitude.
double	getMeanMotion()	Get the Keplerian mean motion.
Orbit	getOrbit()	Get the orbit.
double	getP()	Get the y component of inclination vector.
double	getQ()	Get the x component of inclination vector.
int	getRetrogradeFactor()	Get the retrograde factor.
double	getSma()	Get the semi-major axis.
Vector3D	getVectorF()	Get equinoctial frame vector f.
Vector3D	getVectorG()	Get equinoctial frame vector g.
Vector3D	getVectorW()	Get equinoctial frame vector w.

Methods inherited from class java.lang.Object

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

Constructor Detail

AuxiliaryElements

public AuxiliaryElements(Orbit orbit,
                         int retrogradeFactor)

Simple constructor.

Parameters:

orbit - related mean orbit for auxiliary elements

retrogradeFactor - retrograde factor I [Eq. 2.1.2-(2)]

Method Detail

getOrbit

public Orbit getOrbit()

Get the orbit.

Returns:

the orbit

getDate

public AbsoluteDate getDate()

Get the date of the orbit.

Returns:

the date

getFrame

public Frame getFrame()

Get the definition frame of the orbit.

Returns:

the definition frame

getEcc

public double getEcc()

Get the eccentricity.

Returns:

ecc

getMeanMotion

public double getMeanMotion()

Get the Keplerian mean motion.

Returns:

n

getKeplerianPeriod

public double getKeplerianPeriod()

Get the Keplerian period.

Returns:

period

getSma

public double getSma()

Get the semi-major axis.

Returns:

the semi-major axis a

getK

public double getK()

Get the x component of eccentricity vector.

This element called k in DSST corresponds to ex for the EquinoctialOrbit

Returns:

k

getH

public double getH()

Get the y component of eccentricity vector.

This element called h in DSST corresponds to ey for the EquinoctialOrbit

Returns:

h

getQ

public double getQ()

Get the x component of inclination vector.

This element called q in DSST corresponds to hx for the EquinoctialOrbit

Returns:

q

getP

public double getP()

Get the y component of inclination vector.

This element called p in DSST corresponds to hy for the EquinoctialOrbit

Returns:

p

getLM

public double getLM()

Get the mean longitude.

Returns:

lm

getLv

public double getLv()

Get the true longitude.

Returns:

lv

getLf

public double getLf()

Get the eccentric longitude.

Returns:

lf

getRetrogradeFactor

public int getRetrogradeFactor()

Get the retrograde factor.

Returns:

the retrograde factor I

getB

public double getB()

Get B = sqrt(1 - e²).

Returns:

B

getC

public double getC()

Get C = 1 + p² + q².

Returns:

C

getVectorF

public Vector3D getVectorF()

Get equinoctial frame vector f.

Returns:

f vector

getVectorG

public Vector3D getVectorG()

Get equinoctial frame vector g.

Returns:

g vector

getVectorW

public Vector3D getVectorW()

Get equinoctial frame vector w.

Returns:

w vector