fr.cnes.sirius.patrius.orbits.orbitalparameters

Class StelaEquinoctialParameters

java.lang.Object

fr.cnes.sirius.patrius.orbits.orbitalparameters.AbstractOrbitalParameters

fr.cnes.sirius.patrius.orbits.orbitalparameters.StelaEquinoctialParameters

All Implemented Interfaces:

IOrbitalParameters, Serializable

public class StelaEquinoctialParameters
extends AbstractOrbitalParameters

This class handles the equinoctial orbital parameters used in Stela; it has been created because the equinoctial parameters associated to Stela differ from the EquinoctialParameters parameters.

The parameters used internally are the equinoctial elements which can be related to keplerian elements as follows:

     a
     ex = e cos(ω + Ω)
     ey = e sin(ω + Ω)
     ix = sin(i/2) cos(Ω)
     iy = sin(i/2) sin(Ω)
     lM = M + ω + Ω
 

where ω stands for the Perigee Argument and Ω stands for the Right Ascension of the Ascending Node.

Since:

3.0

Version:

$Id: StelaEquinoctialParameters.java 18071 2017-10-02 16:46:39Z bignon $

Author:

Emmanuel Bignon

See Also:

Serialized Form

Concurrency :

immutable

Field Summary

Fields

Modifier and Type	Field and Description
static double	I_LIM Inclination upper limit.
static double	SIN_I_LIM Sinus of half limit inclination in type 8.

Constructor Summary

Constructors

Constructor and Description
StelaEquinoctialParameters(double aIn, double exIn, double eyIn, double ixIn, double iyIn, double lMIn, double mu, boolean needCorrection) Creates a new instance.

Method Summary

Modifier and Type	Method and Description
double[]	correctInclination(double ixIn, double iyIn) Inclination correction because of inclination singularity in StelaEquinoctial parameters around 180deg.
boolean	equals(Object object) Test for the equality of two orbits.
double	getA() Get the semi-major axis.
AlternateEquinoctialParameters	getAlternateEquinoctialParameters() Convert current orbital parameters into alternate equinoctial parameters.
ApsisAltitudeParameters	getApsisAltitudeParameters(double ae) Convert current orbital parameters into apsis (using altitude) parameters.
ApsisRadiusParameters	getApsisRadiusParameters() Convert current orbital parameters into apsis (using radius) parameters.
CartesianParameters	getCartesianParameters() Convert current orbital parameters into cartesian parameters.
CircularParameters	getCircularParameters() Convert current orbital parameters into circular parameters.
EquatorialParameters	getEquatorialParameters() Convert current orbital parameters into equatorial parameters.
double	getEquinoctialEx() Get the first component of the eccentricity vector.
double	getEquinoctialEy() Get the second component of the eccentricity vector.
EquinoctialParameters	getEquinoctialParameters() Convert current orbital parameters into equinoctial parameters.
double	getIx() Get the first component of the inclination vector.
double	getIy() Get the second component of the inclination vector.
KeplerianParameters	getKeplerianParameters() Convert current orbital parameters into Keplerian parameters.
double	getLM() Get the mean longitude argument.
ReentryParameters	getReentryParameters(double ae, double f) Convert current orbital parameters into reentry parameters.
StelaEquinoctialParameters	getStelaEquinoctialParameters() Convert current orbital parameters into Stela equinoctial parameters.
int	hashCode() Get a hashCode for the orbit.
String	toString() Returns a string representation of this orbit parameters object.

Methods inherited from class fr.cnes.sirius.patrius.orbits.orbitalparameters.AbstractOrbitalParameters

getMu

Methods inherited from class java.lang.Object

clone, finalize, getClass, notify, notifyAll, wait, wait, wait

Field Detail

I_LIM

public static final double I_LIM

Inclination upper limit.

SIN_I_LIM

public static final double SIN_I_LIM

Sinus of half limit inclination in type 8.

Constructor Detail

StelaEquinoctialParameters

public StelaEquinoctialParameters(double aIn,
                                  double exIn,
                                  double eyIn,
                                  double ixIn,
                                  double iyIn,
                                  double lMIn,
                                  double mu,
                                  boolean needCorrection)

Creates a new instance.

Parameters:

aIn - semi-major axis (m)

exIn - e cos(ω + Ω), first component of eccentricity vector

eyIn - e sin(ω + Ω), second component of eccentricity vector

ixIn - sin(i/2) cos(Ω), first component of inclination vector

iyIn - sin(i/2) sin(Ω), second component of inclination vector

lMIn - M + ω + Ω, mean longitude argument (rad)

mu - central attraction coefficient (m³/s²)

needCorrection - true if the inclination correction has to be done

Throws:

IllegalArgumentException - if eccentricity is equal to 1 or larger

Method Detail

getA

public double getA()

Get the semi-major axis.

Returns:

semi-major axis (m)

getEquinoctialEx

public double getEquinoctialEx()

Get the first component of the eccentricity vector.

Returns:

e cos(ω + Ω), first component of the eccentricity vector

getEquinoctialEy

public double getEquinoctialEy()

Get the second component of the eccentricity vector.

Returns:

e sin(ω + Ω), second component of the eccentricity vector

getIx

public double getIx()

Get the first component of the inclination vector.

Returns:

sin(i/2) cos(Ω), first component of the inclination vector

getIy

public double getIy()

Get the second component of the inclination vector.

Returns:

sin(i/2) sin(Ω), second component of the inclination vector

getLM

public double getLM()

Get the mean longitude argument.

Returns:

M + ω + Ω mean longitude argument (rad)

correctInclination

public double[] correctInclination(double ixIn,
                                   double iyIn)

Inclination correction because of inclination singularity in StelaEquinoctial parameters around 180deg.

Parameters:

ixIn - first component of inclination vector

iyIn - second component of inclination vector

Returns:

corrected inclination components

getCartesianParameters

public CartesianParameters getCartesianParameters()

Convert current orbital parameters into cartesian parameters.

Returns:

current orbital parameters converted into cartesian parameters

See Also:

CartesianParameters

getKeplerianParameters

public KeplerianParameters getKeplerianParameters()

Convert current orbital parameters into Keplerian parameters.

Returns:

current orbital parameters converted into Keplerian parameters

See Also:

KeplerianParameters

getCircularParameters

public CircularParameters getCircularParameters()

Convert current orbital parameters into circular parameters.

Returns:

current orbital parameters converted into circular parameters

See Also:

CircularParameters

getEquatorialParameters

public EquatorialParameters getEquatorialParameters()

Convert current orbital parameters into equatorial parameters.

Returns:

current orbital parameters converted into equatorial parameters

See Also:

EquatorialParameters

getEquinoctialParameters

public EquinoctialParameters getEquinoctialParameters()

Convert current orbital parameters into equinoctial parameters.

Returns:

current orbital parameters converted into equinoctial parameters

See Also:

EquinoctialParameters

getApsisAltitudeParameters

public ApsisAltitudeParameters getApsisAltitudeParameters(double ae)

Convert current orbital parameters into apsis (using altitude) parameters.

Parameters:

ae - equatorial radius (m)

Returns:

current orbital parameters converted into apsis (using altitude) parameters

See Also:

ApsisAltitudeParameters

getApsisRadiusParameters

public ApsisRadiusParameters getApsisRadiusParameters()

Convert current orbital parameters into apsis (using radius) parameters.

Returns:

current orbital parameters converted into apsis (using radius) parameters

See Also:

ApsisRadiusParameters

getReentryParameters

public ReentryParameters getReentryParameters(double ae,
                                              double f)

Convert current orbital parameters into reentry parameters.

Parameters:

ae - equatorial radius (m)

f - flattening (f = (a-b)/a)

Returns:

current orbital parameters converted into reentry parameters

See Also:

ReentryParameters

getStelaEquinoctialParameters

public StelaEquinoctialParameters getStelaEquinoctialParameters()

Convert current orbital parameters into Stela equinoctial parameters.

Returns:

current orbital parameters converted into Stela equinoctial parameters

See Also:

StelaEquinoctialParameters

getAlternateEquinoctialParameters

public AlternateEquinoctialParameters getAlternateEquinoctialParameters()

Convert current orbital parameters into alternate equinoctial parameters.

Returns:

current orbital parameters converted into alternate equinoctial parameters

See Also:

AlternateEquinoctialParameters

toString

public String toString()

Returns a string representation of this orbit parameters object.

Overrides:

toString in class Object

Returns:

a string representation of this object

equals

public boolean equals(Object object)

Test for the equality of two orbits.

Orbits are considered equals if they have the same type and all their attributes are equals. In particular, the orbits frame are considered equals if they represent the same instance. If they have the same attributes but are not the same instance, the method will return false.

Specified by:

equals in interface IOrbitalParameters

Overrides:

equals in class Object

Parameters:

object - Object to test for equality to this

Returns:

true if two orbits are equal

hashCode

public int hashCode()

Get a hashCode for the orbit.

Specified by:

hashCode in interface IOrbitalParameters

Overrides:

hashCode in class Object

Returns:

a hash code value for this object