fr.cnes.sirius.patrius.assembly.models

Class InertiaComputedModel

java.lang.Object

fr.cnes.sirius.patrius.assembly.models.InertiaComputedModel

All Implemented Interfaces:

IInertiaModel, MassProvider, Cloneable

public class InertiaComputedModel
extends Object
implements IInertiaModel

This class is an inertia model computed from the inertia properties of each parts of an Assembly object.

Note : when using this model within a propagation, it is necessary to feed the additional equations to the propagator. This has to be done prior to any propagation, to allow this model to account mass variations (i.e. due to maneuvers), using the method NumericalPropagator.setMassProviderEquation() which will register the additional equation and initialize the initial additional state.

Since:

1.2

Version:

$Id$

Author:

Thomas Trapier

See Also:

IInertiaModel

Concurrency :

not thread-safe

Concurrency comment :

the direct use of a not thread-safe Assembly makes this class not thread-safe itself

Field Summary

Fields inherited from interface fr.cnes.sirius.patrius.propagation.MassProvider

MASS

Constructor Summary

Constructors

Constructor and Description
InertiaComputedModel(Assembly assembly) Constructor for the computed inertia model.

Method Summary

Modifier and Type	Method and Description
void	addMassDerivative(String partName, double flowRate) Add the mass derivate of the given part.
AdditionalEquations	getAdditionalEquation(String name) Get the mass equation related to the part.
List<String>	getAllPartsNames() Get the list of the name of the parts.
Matrix3D	getInertiaMatrix(Frame frame, AbsoluteDate date) Getter for the inertia matrix of the spacecraft, expressed with respect to the MASS CENTER in a given frame.
Matrix3D	getInertiaMatrix(Frame frame, AbsoluteDate date, Vector3D inertiaReferencePoint) Getter for the inertia matrix of the spacecraft, once expressed with respect to a point that can be different from the mass center.
double	getMass(String partName) Return the mass of the given part.
Vector3D	getMassCenter(Frame frame, AbsoluteDate date) Getter for the mass center.
double	getTotalMass() Return the mass of the spacecraft.
double	getTotalMass(SpacecraftState state) Return the mass of the spacecraft following the order.
void	setMassDerivativeZero(String partName) Set mass derivative to zero.
void	updateMass(String partName, double mass) Update the mass of the given part.

Methods inherited from class java.lang.Object

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

Constructor Detail

InertiaComputedModel

public InertiaComputedModel(Assembly assembly)

Constructor for the computed inertia model.

Parameters:

assembly - the considered assembly

Method Detail

getMassCenter

public Vector3D getMassCenter(Frame frame,
                              AbsoluteDate date)
                       throws PatriusException

Getter for the mass center.

Specified by:

getMassCenter in interface IInertiaModel

Parameters:

frame - the expression frame of the mass center position

date - the current date (unused for simple the model)

Returns:

the mass center position vector

Throws:

PatriusException - if a problem occurs during frames transformations

getInertiaMatrix

public Matrix3D getInertiaMatrix(Frame frame,
                                 AbsoluteDate date)
                          throws PatriusException

Getter for the inertia matrix of the spacecraft, expressed with respect to the MASS CENTER in a given frame.

Specified by:

getInertiaMatrix in interface IInertiaModel

Parameters:

frame - the expression frame of the inertia matrix

date - the current date (unused for simple the model)

Returns:

the inertia matrix

Throws:

PatriusException - if a problem occurs during frames transformations

getInertiaMatrix

public Matrix3D getInertiaMatrix(Frame frame,
                                 AbsoluteDate date,
                                 Vector3D inertiaReferencePoint)
                          throws PatriusException

Getter for the inertia matrix of the spacecraft, once expressed with respect to a point that can be different from the mass center. This point must be defined in the reference frame of expression of the matrix.

Specified by:

getInertiaMatrix in interface IInertiaModel

Parameters:

frame - the expression frame of the inertia matrix

date - the current date (unused for simple the model)

inertiaReferencePoint - the point with respect to the inertia matrix is expressed (in the reference frame)

Returns:

the inertia matrix

Throws:

PatriusException - if a problem occurs during frames transformations

addMassDerivative

public void addMassDerivative(String partName,
                              double flowRate)

Add the mass derivate of the given part.

Specified by:

addMassDerivative in interface MassProvider

Parameters:

partName - name of part subject to mass variation

flowRate - flow rate of specified part

setMassDerivativeZero

public void setMassDerivativeZero(String partName)

Set mass derivative to zero.

Specified by:

setMassDerivativeZero in interface MassProvider

Parameters:

partName - name of part whose mass derivative is set to zero

updateMass

public void updateMass(String partName,
                       double mass)
                throws PatriusException

Update the mass of the given part.

Specified by:

updateMass in interface MassProvider

Parameters:

partName - given part

mass - mass of the given part

Throws:

PatriusException - thrown if the mass becomes negative (PatriusMessages.SPACECRAFT_MASS_BECOMES_NEGATIVE)

getMass

public double getMass(String partName)

Return the mass of the given part.

Specified by:

getMass in interface MassProvider

Parameters:

partName - given part

Returns:

mass of part

getTotalMass

public double getTotalMass()

Return the mass of the spacecraft.

Specified by:

getTotalMass in interface MassProvider

Returns:

spacecraft mass

getTotalMass

public double getTotalMass(SpacecraftState state)

Return the mass of the spacecraft following the order.

• If mass is in spacecraft state, mass from spacecraft state will be returned
• Otherwise mass from mass provider is returned (same as MassProvider.getTotalMass())

Specified by:

getTotalMass in interface MassProvider

Parameters:

state - spacecraft state

Returns:

spacecraft mass

getAdditionalEquation

public AdditionalEquations getAdditionalEquation(String name)

Get the mass equation related to the part.

Specified by:

getAdditionalEquation in interface MassProvider

Parameters:

name - part name

Returns:

the associated mass equation

getAllPartsNames

public List<String> getAllPartsNames()

Get the list of the name of the parts.

Specified by:

getAllPartsNames in interface MassProvider

Returns:

the list of the spacecraft parts name.