fr.cnes.sirius.patrius.guidance

Class QuaternionHarmonicProfile

java.lang.Object

fr.cnes.sirius.patrius.guidance.GuidanceProfile

fr.cnes.sirius.patrius.guidance.QuaternionHarmonicProfile

All Implemented Interfaces:

AttitudeLeg, AttitudeProvider, Serializable

public final class QuaternionHarmonicProfile
extends GuidanceProfile

Represents a quaternion guidance profile, calculated with Fourier series.

Since:

1.3

Version:

$Id: QuaternionHarmonicProfile.java 18397 2017-11-20 08:11:35Z bignon $

Author:

Tiziana Sabatini

See Also:

Serialized Form

Concurrency :

conditionally thread-safe

Concurrency comment :

thread-safe if the Frame attribute is thread-safe.

Constructor Summary

Constructors

Constructor and Description
QuaternionHarmonicProfile(AbsoluteDate origin, Frame frame, FourierSeries q0, FourierSeries q1, FourierSeries q2, FourierSeries q3, AbsoluteDateInterval timeInterval) Create a harmonic, quaternion guidance profile.

Method Summary

Methods

Modifier and Type	Method and Description
double[]	getAngularFrequencies()
Attitude	getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
double[]	getConstants()
double[][]	getCosArrays()
FourierSeries	getQ0FourierSeries()
FourierSeries	getQ1FourierSeries()
FourierSeries	getQ2FourierSeries()
FourierSeries	getQ3FourierSeries()
double[][]	getSinArrays()
void	setSpinDerivativesComputation(boolean computeSpinDerivatives) Method to activate spin derivative computation.

Methods inherited from class fr.cnes.sirius.patrius.guidance.GuidanceProfile

checkDate, getAttitude, getTimeInterval

Methods inherited from class java.lang.Object

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

Constructor Detail

QuaternionHarmonicProfile

public QuaternionHarmonicProfile(AbsoluteDate origin,
                         Frame frame,
                         FourierSeries q0,
                         FourierSeries q1,
                         FourierSeries q2,
                         FourierSeries q3,
                         AbsoluteDateInterval timeInterval)

Create a harmonic, quaternion guidance profile.

Parameters:

origin - origin of date

frame - the reference frame of the Fourier series

q0 - q0 quaternion component Fourier decomposition

q1 - q1 quaternion component Fourier decomposition

q2 - q2 quaternion component Fourier decomposition

q3 - q3 quaternion component Fourier decomposition

timeInterval - interval of validity of the guidance profile

Method Detail

getQ0FourierSeries

public FourierSeries getQ0FourierSeries()

Returns:

the Fourier series representing the q0 quaternion component.

getQ1FourierSeries

public FourierSeries getQ1FourierSeries()

Returns:

the Fourier series representing the q1 quaternion component.

getQ2FourierSeries

public FourierSeries getQ2FourierSeries()

Returns:

the Fourier series representing the q2 quaternion component.

getQ3FourierSeries

public FourierSeries getQ3FourierSeries()

Returns:

the Fourier series representing the q3 quaternion component.

getAngularFrequencies

public double[] getAngularFrequencies()

Returns:

the angular frequencies of the four Fourier series representing q0, q1, q2 qnd q3.

getConstants

public double[] getConstants()

Returns:

the a0 coefficients of the four Fourier series representing q0, q1, q2 qnd q3.

getCosArrays

public double[][] getCosArrays()

Returns:

the a coefficients of the four Fourier series representing q0, q1, q2 qnd q3.

getSinArrays

public double[][] getSinArrays()

Returns:

the b coefficients of the four Fourier series representing q0, q1, q2 qnd q3.

getAttitude

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

Compute the attitude corresponding to an orbital state.

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

Throws:

PatriusException - if attitude cannot be computed

setSpinDerivativesComputation

public void setSpinDerivativesComputation(boolean computeSpinDerivatives)
                                   throws PatriusException

Method to activate spin derivative computation.

Parameters:

computeSpinDerivatives - true if spin derivatives should be computed

Throws:

PatriusException - if spin derivatives can not be computed