org.orekit.attitudes

Class CelestialBodyPointed

java.lang.Object

org.orekit.attitudes.CelestialBodyPointed

All Implemented Interfaces:

AttitudeProvider

public class CelestialBodyPointed
extends Object
implements AttitudeProvider

This class handles a celestial body pointed attitude provider.

The celestial body pointed law is defined by two main elements:

• a celestial body towards which some satellite axis is exactly aimed
• a phasing reference defining the rotation around the pointing axis

The celestial body implicitly defines two of the three degrees of freedom and the phasing reference defines the remaining degree of freedom. This definition can be represented as first aligning exactly the satellite pointing axis to the current direction of the celestial body, and then to find the rotation around this axis such that the satellite phasing axis is in the half-plane defined by a cut line on the pointing axis and containing the celestial phasing reference.

In order for this definition to work, the user must ensure that the phasing reference is never aligned with the pointing reference. Since the pointed body moves as the date changes, this should be ensured regardless of the date. A simple way to do this for Sun, Moon or any planet pointing is to choose a phasing reference far from the ecliptic plane. Using Vector3D.PLUS_K, the equatorial pole, is perfect in these cases.

Instances of this class are guaranteed to be immutable.

Author:

Luc Maisonobe

Constructor Summary

Constructors

Constructor and Description
CelestialBodyPointed(Frame celestialFrame, PVCoordinatesProvider pointedBody, Vector3D phasingCel, Vector3D pointingSat, Vector3D phasingSat) Creates new instance.

Method Summary

Modifier and Type	Method and Description
<T extends RealFieldElement<T>> FieldAttitude<T>	getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.

Methods inherited from class java.lang.Object

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

Constructor Detail

CelestialBodyPointed

public CelestialBodyPointed(Frame celestialFrame,
                            PVCoordinatesProvider pointedBody,
                            Vector3D phasingCel,
                            Vector3D pointingSat,
                            Vector3D phasingSat)

Creates new instance.

Parameters:

celestialFrame - frame in which phasingCel is defined

pointedBody - celestial body to point at

phasingCel - phasing reference, in celestial frame

pointingSat - satellite vector defining the pointing direction

phasingSat - phasing reference, in satellite frame

Method Detail

getAttitude

public Attitude getAttitude(PVCoordinatesProvider pvProv,
                            AbsoluteDate date,
                            Frame frame)

Compute the attitude corresponding to an orbital state.

Specified by:

getAttitude in interface AttitudeProvider

Parameters:

pvProv - local position-velocity provider around current date

date - current date

frame - reference frame from which attitude is computed

Returns:

attitude attitude on the specified date and position-velocity state

getAttitude

public <T extends RealFieldElement<T>> FieldAttitude<T> getAttitude(FieldPVCoordinatesProvider<T> pvProv,
                                                                    FieldAbsoluteDate<T> date,
                                                                    Frame frame)

Compute the attitude corresponding to an orbital state.

Specified by:

getAttitude in interface AttitudeProvider

Type Parameters:

T - type of the field elements

Parameters:

pvProv - local position-velocity provider around current date

date - current date

frame - reference frame from which attitude is computed

Returns:

attitude attitude on the specified date and position-velocity state