fr.cnes.sirius.patrius.forces.gravity.tides

Class AbstractTides

java.lang.Object

fr.cnes.sirius.patrius.math.parameter.Parameterizable

fr.cnes.sirius.patrius.math.parameter.JacobiansParameterizable

fr.cnes.sirius.patrius.forces.gravity.tides.AbstractTides

All Implemented Interfaces:

ForceModel, GradientModel, PotentialTimeVariations, IJacobiansParameterizable, IParameterizable, Serializable

Direct Known Subclasses:

OceanTides, TerrestrialTides

public abstract class AbstractTides
extends JacobiansParameterizable
implements ForceModel, GradientModel, PotentialTimeVariations

Common handling of ForceModel methods for tides models.

This abstract class allows to provide easily the full set of ForceModel methods to tides models. Only one method must be implemented by derived classes: updateCoefficientsCandS(fr.cnes.sirius.patrius.time.AbsoluteDate).

Since:

2.3

Version:

$Id: AbstractTides.java 17582 2017-05-10 12:58:16Z bignon $

Author:

Charlotte Maggiorani

See Also:

Serialized Form

Concurrency :

not thread-safe

Concurrency comment :

not thread safe because of the method updateCoefficientsCandS().

Field Summary

Fields

Modifier and Type	Field and Description
protected Frame	bodyFrame Frame for the central body.
protected double[][]	coefficientsC First normalized potential tesseral coefficients array.
protected double[][]	coefficientsCPD First normalized potential tesseral coefficients array for partial derivatives computation.
protected double[][]	coefficientsS Second normalized potential tesseral coefficients array.
protected double[][]	coefficientsSPD Second normalized potential tesseral coefficients array for partial derivatives computation.
static String	MU Parameter name for central attraction coefficient.
protected Parameter	paramAe Equatorial radius parameter.
protected Parameter	paramMu Central attraction coefficient parameter.
static String	RADIUS Parameter name for equatorial radius.

Constructor Summary

Constructors

Modifier	Constructor and Description
protected	AbstractTides(Frame centralBodyFrame, double equatorialRadius, double mu, int degree, int order) Build a new instance.
protected	AbstractTides(Frame centralBodyFrame, double equatorialRadius, double mu, int degree, int order, int degreePD, int orderPD) Build a new instance.
protected	AbstractTides(Frame centralBodyFrame, Parameter equatorialRadius, Parameter mu, int degree, int order) Build a new instance using Parameter.
protected	AbstractTides(Frame centralBodyFrame, Parameter equatorialRadius, Parameter mu, int degree, int order, int degreePD, int orderPD) Build a new instance using Parameter.

Method Summary

Modifier and Type	Method and Description
void	addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	addDAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel) Compute acceleration derivatives with respect to state parameters.
Vector3D	computeAcceleration(PVCoordinates pv, Frame frame, AbsoluteDate date) Method to compute the acceleration, from Balmino algorithm (see BalminoAttractionModel class).
Vector3D	computeAcceleration(SpacecraftState s) Compute the acceleration due to the force.
boolean	computeGradientVelocity() This method returns true if the acceleration partial derivatives with respect to velocity have to be computed.
EventDetector[]	getEventsDetectors() Get the discrete events related to the model.
abstract void	updateCoefficientsCandS(AbsoluteDate date) Update the C and the S coefficients for acceleration computation.
abstract void	updateCoefficientsCandSPD(AbsoluteDate date) Update the C and the S coefficients for partial derivatives computation.

Methods inherited from class fr.cnes.sirius.patrius.math.parameter.JacobiansParameterizable

addJacobiansParameter, addJacobiansParameter, addJacobiansParameter, supportsJacobianParameter

Methods inherited from class fr.cnes.sirius.patrius.math.parameter.Parameterizable

addParameter, getParameters, supportsParameter

Methods inherited from class java.lang.Object

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

Methods inherited from interface fr.cnes.sirius.patrius.math.parameter.IParameterizable

getParameters, supportsParameter

Methods inherited from interface fr.cnes.sirius.patrius.forces.GradientModel

computeGradientPosition

Field Detail

MU

public static final String MU

Parameter name for central attraction coefficient.

See Also:

Constant Field Values

RADIUS

public static final String RADIUS

Parameter name for equatorial radius.

See Also:

Constant Field Values

paramMu

protected Parameter paramMu

Central attraction coefficient parameter.

paramAe

protected Parameter paramAe

Equatorial radius parameter.

coefficientsC

protected double[][] coefficientsC

First normalized potential tesseral coefficients array.

coefficientsS

protected double[][] coefficientsS

Second normalized potential tesseral coefficients array.

coefficientsCPD

protected double[][] coefficientsCPD

First normalized potential tesseral coefficients array for partial derivatives computation.

coefficientsSPD

protected double[][] coefficientsSPD

Second normalized potential tesseral coefficients array for partial derivatives computation.

bodyFrame

protected final Frame bodyFrame

Frame for the central body.

Constructor Detail

AbstractTides

protected AbstractTides(Frame centralBodyFrame,
                        double equatorialRadius,
                        double mu,
                        int degree,
                        int order)

Build a new instance.

Parameters:

centralBodyFrame - rotating central body frame

equatorialRadius - equatorial radius

mu - central body attraction coefficient (m³/s²)

degree - degree

order - order

AbstractTides

protected AbstractTides(Frame centralBodyFrame,
                        double equatorialRadius,
                        double mu,
                        int degree,
                        int order,
                        int degreePD,
                        int orderPD)

Build a new instance.

Parameters:

centralBodyFrame - rotating central body frame

equatorialRadius - equatorial radius

mu - central body attraction coefficient (m³/s²)

degree - degree for acceleration computation

order - order for acceleration computation

degreePD - degree for partial derivatives computation

orderPD - order for partial derivatives computation

AbstractTides

protected AbstractTides(Frame centralBodyFrame,
                        Parameter equatorialRadius,
                        Parameter mu,
                        int degree,
                        int order)

Build a new instance using Parameter.

Parameters:

centralBodyFrame - rotating central body frame

equatorialRadius - equatorial radius parameter

mu - central body attraction coefficient (m³/s²) parameter

degree - degree

order - order

AbstractTides

protected AbstractTides(Frame centralBodyFrame,
                        Parameter equatorialRadius,
                        Parameter mu,
                        int degree,
                        int order,
                        int degreePD,
                        int orderPD)

Build a new instance using Parameter.

Parameters:

centralBodyFrame - rotating central body frame

equatorialRadius - equatorial radius parameter

mu - central body attraction coefficient (m³/s²) parameter

degree - degree for acceleration computation

order - order for acceleration computation

degreePD - degree for partial derivatives computation

orderPD - order for partial derivatives computation

Method Detail

addContribution

public void addContribution(SpacecraftState s,
                            TimeDerivativesEquations adder)
                     throws PatriusException

Compute the contribution of the force model to the perturbing acceleration.

Specified by:

addContribution in interface ForceModel

Parameters:

s - current state information: date, kinematics, attitude

adder - object where the contribution should be added

Throws:

PatriusException - if some specific error occurs

computeAcceleration

public Vector3D computeAcceleration(SpacecraftState s)
                             throws PatriusException

Compute the acceleration due to the force.

Specified by:

computeAcceleration in interface ForceModel

Parameters:

s - current state information: date, kinematics, attitude

Returns:

acceleration in the SpacecraftState frame

Throws:

PatriusException - if some specific error occurs

computeAcceleration

public Vector3D computeAcceleration(PVCoordinates pv,
                                    Frame frame,
                                    AbsoluteDate date)
                             throws PatriusException

Method to compute the acceleration, from Balmino algorithm (see BalminoAttractionModel class). This method has been implemented in order to validate the force model only. The reason is that for the validation context, we do not want to set up an instance of the SpacecraftState object to avoid the inertial frame of the spacecraft orbit.

(see Feature #34 on https://www.orekit.org/forge/issues/34)

Out of the validation context, one must use the method Vector3D computeAcceleration(final SpacecraftState s)

Parameters:

pv - PV coordinates of the spacecraft

frame - frame in which the acceleration is computed

date - date

Returns:

acceleration vector

Throws:

PatriusException - if an Orekit error occurs

getEventsDetectors

public EventDetector[] getEventsDetectors()

Get the discrete events related to the model.

Specified by:

getEventsDetectors in interface ForceModel

Returns:

array of events detectors or null if the model is not related to any discrete events

computeGradientVelocity

public boolean computeGradientVelocity()

This method returns true if the acceleration partial derivatives with respect to velocity have to be computed.

Specified by:

computeGradientVelocity in interface GradientModel

Returns:

true if the derivatives have to be computed, false otherwise

updateCoefficientsCandS

public abstract void updateCoefficientsCandS(AbsoluteDate date)
                                      throws PatriusException

Update the C and the S coefficients for acceleration computation.

Specified by:

updateCoefficientsCandS in interface PotentialTimeVariations

Parameters:

date - : date

Throws:

PatriusException - if position cannot be computed in given frame

updateCoefficientsCandSPD

public abstract void updateCoefficientsCandSPD(AbsoluteDate date)
                                        throws PatriusException

Update the C and the S coefficients for partial derivatives computation.

Specified by:

updateCoefficientsCandSPD in interface PotentialTimeVariations

Parameters:

date - : date

Throws:

PatriusException - if position cannot be computed in given frame

addDAccDState

public final void addDAccDState(SpacecraftState s,
                                double[][] dAccdPos,
                                double[][] dAccdVel)
                         throws PatriusException

Compute acceleration derivatives with respect to state parameters..

Specified by:

addDAccDState in interface IJacobiansParameterizable

Parameters:

s - spacecraft state

dAccdPos - acceleration derivatives with respect to position

dAccdVel - acceleration derivatives with respect to velocity

Throws:

PatriusException - if derivatives cannot be computed

addDAccDParam

public void addDAccDParam(SpacecraftState s,
                          Parameter param,
                          double[] dAccdParam)
                   throws PatriusException

Compute acceleration derivatives with respect to additional parameters.. No parameter is supported by this force model

Specified by:

addDAccDParam in interface IJacobiansParameterizable

Parameters:

s - spacecraft state

param - the parameter with respect to which derivatives are required

dAccdParam - acceleration derivatives with respect to specified parameters

Throws:

PatriusException - if derivatives cannot be computed