Package org.orekit.attitudes

Class AlignedAndConstrained

java.lang.Object

org.orekit.attitudes.AlignedAndConstrained

All Implemented Interfaces:

AttitudeProvider

public class AlignedAndConstrained
extends Object
implements AttitudeProvider

Attitude provider with one satellite vector aligned and another one constrained to two targets.

Since:

12.2

Author:

Luc Maisonobe

Constructor Summary

Constructors

Constructor	Description
AlignedAndConstrained(Vector3D primarySat, TargetProvider primaryTarget, Vector3D secondarySat, TargetProvider secondaryTarget, ExtendedPositionProvider sun, OneAxisEllipsoid earth)	Simple constructor.

Method Summary

Modifier and Type	Method	Description
<T extends CalculusFieldElement<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.
<T extends CalculusFieldElement<T>> FieldRotation<T>	getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
Rotation	getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude-related rotation 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

AlignedAndConstrained

public AlignedAndConstrained(Vector3D primarySat,
                             TargetProvider primaryTarget,
                             Vector3D secondarySat,
                             TargetProvider secondaryTarget,
                             ExtendedPositionProvider sun,
                             OneAxisEllipsoid earth)

Simple constructor.

Parameters:

primarySat - satellite vector for primary target

primaryTarget - primary target

secondarySat - satellite vector for secondary target

secondaryTarget - secondary target

sun - Sun model

earth - Earth model

Method Detail

getAttitudeRotation

public Rotation getAttitudeRotation(PVCoordinatesProvider pvProv,
                                    AbsoluteDate date,
                                    Frame frame)

Compute the attitude-related rotation corresponding to an orbital state.

Specified by:

getAttitudeRotation 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-related rotation on the specified date and position-velocity state

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 on the specified date and position-velocity state

getAttitudeRotation

public <T extends CalculusFieldElement<T>> FieldRotation<T> getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv,
                                                                                FieldAbsoluteDate<T> date,
                                                                                Frame frame)

Compute the attitude-related rotation corresponding to an orbital state.

Specified by:

getAttitudeRotation 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:

rotation on the specified date and position-velocity state

getAttitude

public <T extends CalculusFieldElement<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 on the specified date and position-velocity state