org.orekit.orbits.orbitalparameters
Class EquatorialParameters

java.lang.Object
  org.orekit.orbits.orbitalparameters.AbstractOrbitalParameters
      org.orekit.orbits.orbitalparameters.EquatorialParameters

All Implemented Interfaces:

Serializable, IOrbitalParameters

public class EquatorialParameters
extends AbstractOrbitalParameters

This class handles non circular equatorial orbital parameters.

The parameters used internally are the following elements:

     a semi-major axis (m)
     e eccentricity
     pomega = ω + Ω , longitude of the periapsis;
     ix = 2 sin(i/2) cos(Ω), first component of inclination vector
     iy = 2 sin(i/2) sin(Ω), second component of inclination vector
     anomaly (M or E or v);, mean, eccentric or true anomaly (rad)
   

where ω stands for the Periapsis Argument, Ω stands for the Right Ascension of the Ascending Node.

When orbit is either equatorial or circular, some keplerian elements (more precisely ω and Ω) become ambiguous so this class should not be used for such orbits. For this reason, equinoctial parameters is the recommended way to represent orbits.

Since:

3.0

Version:

$Id: EquatorialParameters.java 17602 2017-05-18 08:25:23Z bignon $

Author:

Emmanuel Bignon

See Also:

Serialized Form

Concurrency :

immutable

Constructor Summary

EquatorialParameters(double a, double e, double pomega, double ix, double iy, double anomaly, PositionAngle type, double mu)
Creates a new instance.

Method Summary

double	getA() Get the semi-major axis.
double	getAnomaly(PositionAngle type) Get the anomaly.
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.
double	getE() Get the eccentricity.
double	getEccentricAnomaly() Get the eccentric anomaly.
EquatorialParameters	getEquatorialParameters() Convert current orbital parameters into equatorial parameters.
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	getMeanAnomaly() Get the mean anomaly.
double	getPomega() Get the longitude of the periapsis (ω + Ω).
ReentryParameters	getReentryParameters(double ae, double f) Convert current orbital parameters into reentry parameters.
StelaEquinoctialParameters	getStelaEquinoctialParameters() Convert current orbital parameters into Stela equinoctial parameters.
double	getTrueAnomaly() Get the true anomaly.
String	toString() Returns a string representation of this non circular equatorial orbital parameters object.

Methods inherited from class org.orekit.orbits.orbitalparameters.AbstractOrbitalParameters

getMu

Methods inherited from class java.lang.Object

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

Constructor Detail

EquatorialParameters

public EquatorialParameters(double a,
                            double e,
                            double pomega,
                            double ix,
                            double iy,
                            double anomaly,
                            PositionAngle type,
                            double mu)
                     throws IllegalArgumentException

Creates a new instance.

Parameters:

a - semi-major axis (m)

e - eccentricity

pomega - ω + Ω (rad)

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

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

anomaly - (M or E or v) = anomaly mean, eccentric or true anomaly (rad)

type - type of anomaly

mu - central attraction coefficient (m³/s²)

Throws:

IllegalArgumentException - if orbit is hyperbolic

IllegalArgumentException - if orbit mismatch with conic type

IllegalArgumentException - if inclination vector is not valid, meaning ix^2 + iy^2 > 4

Method Detail

getA

public double getA()

Get the semi-major axis.

Returns:

semi-major axis (m)

getE

public double getE()

Get the eccentricity.

Returns:

eccentricity

getIx

public double getIx()

Get the first component of the inclination vector. ix = 2 sin(i/2) cos(Ω)

Returns:

first component of the inclination vector.

getIy

public double getIy()

Get the second component of the inclination vector. iy = 2 sin(i/2) sin(Ω)

Returns:

second component of the inclination vector.

getPomega

public double getPomega()

Get the longitude of the periapsis (ω + Ω).

Returns:

longitude of the periapsis (rad)

getAnomaly

public double getAnomaly(PositionAngle type)

Get the anomaly.

Parameters:

type - type of the angle

Returns:

anomaly (rad)

getTrueAnomaly

public double getTrueAnomaly()

Get the true anomaly.

Returns:

true anomaly (rad)

getMeanAnomaly

public double getMeanAnomaly()

Get the mean anomaly.

Returns:

mean anomaly (rad)

getEccentricAnomaly

public double getEccentricAnomaly()

Get the eccentric anomaly.

Returns:

eccentric anomaly (rad)

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

toString

public String toString()

Returns a string representation of this non circular equatorial orbital parameters object.

Overrides:

toString in class Object

Returns:

a string representation of this object