org.orekit.orbits
Class ApsisOrbit

java.lang.Object
  org.orekit.orbits.Orbit
      org.orekit.orbits.ApsisOrbit

All Implemented Interfaces:

Serializable, TimeInterpolable<Orbit>, TimeShiftable<Orbit>, TimeStamped, PVCoordinatesProvider

public final class ApsisOrbit
extends Orbit

This class handles periapsis/apoapsis parameters.

The parameters used internally are the periapsis/apoapsis elements (see ApsisRadiusParameters for more information.

The instance ApsisOrbit is guaranteed to be immutable.

Since:

1.3

Version:

$Id: ApsisOrbit.java 14287 2015-11-02 10:55:02Z rodrigues $

Author:

Denis Claude

See Also:

Orbit, KeplerianOrbit, CartesianOrbit, EquinoctialOrbit, Serialized Form

Concurrency :

immutable

Constructor Summary

ApsisOrbit(double peri, double apo, double i, double pa, double raan, double anomaly, PositionAngle type, Frame frame, AbsoluteDate date, double mu)
Creates a new instance.

ApsisOrbit(IOrbitalParameters parameters, Frame frame, AbsoluteDate date)
Creates a new instance.

ApsisOrbit(Orbit op)
Constructor from any kind of orbital parameters.

ApsisOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu)
Constructor from cartesian parameters.

Method Summary

protected double[][]	computeJacobianEccentricWrtCartesian() Compute the Jacobian of the orbital parameters with eccentric angle with respect to the Cartesian parameters.
protected double[][]	computeJacobianMeanWrtCartesian() Compute the Jacobian of the orbital parameters with mean angle with respect to the Cartesian parameters.
protected double[][]	computeJacobianTrueWrtCartesian() Compute the Jacobian of the orbital parameters with true angle with respect to the Cartesian parameters.
double	getA() Get the semi-major axis.
double	getAnomaly(PositionAngle type) Get the anomaly.
double	getApoapsis() Get the apoapsis.
ApsisRadiusParameters	getApsisParameters() Getter for underlying apsis parameters.
double	getE() Get the eccentricity.
double	getEquinoctialEx() Get the first component of the eccentricity vector.
double	getEquinoctialEy() Get the second component of the eccentricity vector.
double	getHx() Get the first component of the inclination vector.
double	getHy() Get the second component of the inclination vector.
double	getI() Get the inclination.
double	getLE() Get the eccentric latitude argument.
double	getLM() Get the mean latitude argument.
double	getLv() Get the true latitude argument.
IOrbitalParameters	getParameters() Get underlying orbital parameters.
double	getPeriapsis() Get the periapsis.
double	getPerigeeArgument() Get the perigee argument.
double	getRightAscensionOfAscendingNode() Get the right ascension of the ascending node.
OrbitType	getType() Get the orbit type.
protected PVCoordinates	initPVCoordinates() Compute the position/velocity coordinates from the canonical parameters.
ApsisOrbit	interpolate(AbsoluteDate date, Collection<Orbit> sample) Get an interpolated instance.
protected void	orbitAddKeplerContribution(PositionAngle type, double gm, double[] pDot) Add the contribution of the Keplerian motion to parameters derivatives
protected ApsisOrbit	orbitShiftedBy(double dt) Get a time-shifted orbit.
String	toString() Returns a string representation of this Orbit object.

Methods inherited from class org.orekit.orbits.Orbit

addKeplerContribution, createInverseJacobian, fillHalfRow, fillHalfRow, fillHalfRow, fillHalfRow, fillHalfRow, fillHalfRow, getDate, getFrame, getJacobian, getJacobianWrtCartesian, getJacobianWrtParameters, getJacobianWrtParametersEccentric, getJacobianWrtParametersMean, getJacobianWrtParametersTrue, getKeplerianMeanMotion, getKeplerianPeriod, getKeplerianTransitionMatrix, getMu, getPVCoordinates, getPVCoordinates, getPVCoordinates, isPositiveDefinite, setJacobianWrtParametersEccentric, setJacobianWrtParametersMean, setJacobianWrtParametersTrue, shiftedBy

Methods inherited from class java.lang.Object

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

Constructor Detail

ApsisOrbit

public ApsisOrbit(IOrbitalParameters parameters,
                  Frame frame,
                  AbsoluteDate date)

Creates a new instance.

Parameters:

parameters - orbital parameters

frame - the frame in which the parameters are defined

date - date of the orbital parameters

ApsisOrbit

public ApsisOrbit(double peri,
                  double apo,
                  double i,
                  double pa,
                  double raan,
                  double anomaly,
                  PositionAngle type,
                  Frame frame,
                  AbsoluteDate date,
                  double mu)

Creates a new instance.

Parameters:

peri - periapsis distance (m)

apo - apoapsis distance (m)

i - inclination (rad)

pa - perigee argument (ω, rad)

raan - right ascension of ascending node (Ω, rad)

anomaly - mean, eccentric or true anomaly (rad).

type - type of anomaly

frame - the frame in which are defined the parameters

date - date of the orbital parameters

mu - central attraction coefficient (m³/s²)

ApsisOrbit

public ApsisOrbit(PVCoordinates pvCoordinates,
                  Frame frame,
                  AbsoluteDate date,
                  double mu)

Constructor from cartesian parameters.

Parameters:

pvCoordinates - the PVCoordinates in inertial frame

frame - the frame in which are defined the PVCoordinates

date - date of the orbital parameters

mu - central attraction coefficient (m³/s²)

ApsisOrbit

public ApsisOrbit(Orbit op)

Constructor from any kind of orbital parameters.

Parameters:

op - orbital parameters to copy

Method Detail

getParameters

public IOrbitalParameters getParameters()

Get underlying orbital parameters.

Specified by:

getParameters in class Orbit

Returns:

orbital parameters

getApsisParameters

public ApsisRadiusParameters getApsisParameters()

Getter for underlying apsis parameters.

Returns:

apsis parameters

getType

public OrbitType getType()

Get the orbit type.

Specified by:

getType in class Orbit

Returns:

orbit type

getPeriapsis

public double getPeriapsis()

Get the periapsis.

Returns:

periapsis (m)

getApoapsis

public double getApoapsis()

Get the apoapsis.

Returns:

apoapsis (m)

getA

public double getA()

Get the semi-major axis.

Specified by:

getA in class Orbit

Returns:

semi-major axis (m)

getEquinoctialEx

public double getEquinoctialEx()

Get the first component of the eccentricity vector.

Specified by:

getEquinoctialEx in class Orbit

Returns:

first component of the eccentricity vector

getEquinoctialEy

public double getEquinoctialEy()

Get the second component of the eccentricity vector.

Specified by:

getEquinoctialEy in class Orbit

Returns:

second component of the eccentricity vector

getHx

public double getHx()

Get the first component of the inclination vector.

Specified by:

getHx in class Orbit

Returns:

first component of the inclination vector.

getHy

public double getHy()

Get the second component of the inclination vector.

Specified by:

getHy in class Orbit

Returns:

second component of the inclination vector.

getAnomaly

public double getAnomaly(PositionAngle type)

Get the anomaly.

Parameters:

type - type of the angle

Returns:

anomaly (rad)

getE

public double getE()

Get the eccentricity.

Specified by:

getE in class Orbit

Returns:

eccentricity

getI

public double getI()

Get the inclination.

Specified by:

getI in class Orbit

Returns:

inclination (rad)

getPerigeeArgument

public double getPerigeeArgument()

Get the perigee argument.

Returns:

perigee argument (rad)

getRightAscensionOfAscendingNode

public double getRightAscensionOfAscendingNode()

Get the right ascension of the ascending node.

Returns:

right ascension of the ascending node (rad)

getLv

public double getLv()

Get the true latitude argument.

Specified by:

getLv in class Orbit

Returns:

true latitude argument (rad)

getLE

public double getLE()

Get the eccentric latitude argument.

Specified by:

getLE in class Orbit

Returns:

eccentric latitude argument.(rad)

getLM

public double getLM()

Get the mean latitude argument.

Specified by:

getLM in class Orbit

Returns:

mean latitude argument.(rad)

initPVCoordinates

protected PVCoordinates initPVCoordinates()

Compute the position/velocity coordinates from the canonical parameters.

Specified by:

initPVCoordinates in class Orbit

Returns:

computed position/velocity coordinates

orbitShiftedBy

protected ApsisOrbit orbitShiftedBy(double dt)

Get a time-shifted orbit.

The orbit can be slightly shifted to close dates. This shift is based on a simple keplerian model. It is not intended as a replacement for proper orbit and attitude propagation but should be sufficient for small time shifts or coarse accuracy.

Specified by:

orbitShiftedBy in class Orbit

Parameters:

dt - time shift in seconds

Returns:

a new orbit, shifted with respect to the instance (which is immutable)

interpolate

public ApsisOrbit interpolate(AbsoluteDate date,
                              Collection<Orbit> sample)

Get an interpolated instance.

Note that the state of the current instance may not be used in the interpolation process, only its type and non interpolable fields are used (for example central attraction coefficient or frame when interpolating orbits). The interpolable fields taken into account are taken only from the states of the sample points. So if the state of the instance must be used, the instance should be included in the sample points.

The interpolated instance is created by polynomial Hermite interpolation on circular elements, without derivatives (which means the interpolation falls back to Lagrange interpolation only).

Parameters:

date - interpolation date

sample - sample points on which interpolation should be done

Returns:

a new instance, interpolated at specified date

computeJacobianMeanWrtCartesian

protected double[][] computeJacobianMeanWrtCartesian()

Compute the Jacobian of the orbital parameters with mean angle with respect to the Cartesian parameters.

Element jacobian[i][j] is the derivative of parameter i of the orbit with respect to Cartesian coordinate j. This means each row correspond to one orbital parameter whereas columns 0 to 5 correspond to the Cartesian coordinates x, y, z, xDot, yDot and zDot.

Specified by:

computeJacobianMeanWrtCartesian in class Orbit

Returns:

6x6 Jacobian matrix

See Also:

Orbit.computeJacobianEccentricWrtCartesian(), Orbit.computeJacobianTrueWrtCartesian()

computeJacobianEccentricWrtCartesian

protected double[][] computeJacobianEccentricWrtCartesian()

Compute the Jacobian of the orbital parameters with eccentric angle with respect to the Cartesian parameters.

Element jacobian[i][j] is the derivative of parameter i of the orbit with respect to Cartesian coordinate j. This means each row correspond to one orbital parameter whereas columns 0 to 5 correspond to the Cartesian coordinates x, y, z, xDot, yDot and zDot.

Specified by:

computeJacobianEccentricWrtCartesian in class Orbit

Returns:

6x6 Jacobian matrix

See Also:

Orbit.computeJacobianMeanWrtCartesian(), Orbit.computeJacobianTrueWrtCartesian()

computeJacobianTrueWrtCartesian

protected double[][] computeJacobianTrueWrtCartesian()

Compute the Jacobian of the orbital parameters with true angle with respect to the Cartesian parameters.

Element jacobian[i][j] is the derivative of parameter i of the orbit with respect to Cartesian coordinate j. This means each row correspond to one orbital parameter whereas columns 0 to 5 correspond to the Cartesian coordinates x, y, z, xDot, yDot and zDot.

Specified by:

computeJacobianTrueWrtCartesian in class Orbit

Returns:

6x6 Jacobian matrix

See Also:

Orbit.computeJacobianMeanWrtCartesian(), Orbit.computeJacobianEccentricWrtCartesian()

orbitAddKeplerContribution

protected void orbitAddKeplerContribution(PositionAngle type,
                                          double gm,
                                          double[] pDot)

Add the contribution of the Keplerian motion to parameters derivatives

This method is used by numerical propagators to evaluate the part of Keplerrian motion to evolution of the orbital state.

Specified by:

orbitAddKeplerContribution in class Orbit

Parameters:

type - type of the position angle in the state

gm - attraction coefficient to use

pDot - array containing orbital state derivatives to update (the Keplerian part must be added to the array components, as the array may already contain some non-zero elements corresponding to non-Keplerian parts)

toString

public String toString()

Returns a string representation of this Orbit object.

Overrides:

toString in class Object

Returns:

a string representation of this object