User Manual 4.0 Numerical propagation - Historique des versions

Admin : /* Interfaces */

2018-04-03T14:14:41Z

Interfaces

← Version précédente		Version du 3 avril 2018 à 14:14
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	! scope="col"\| Javadoc		! scope="col"\| Javadoc
	\|-		\|-
	\|**AdditionalStateProvider		\|'''AdditionalStateProvider'''
	\|This interface represents providers for additional state data beyond SpacecraftState.		\|This interface represents providers for additional state data beyond SpacecraftState.
	\|[{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/AdditionalStateProvider.html ...]		\|[{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/AdditionalStateProvider.html ...]
	\|-		\|-
	\|**AdditionalEquations		\|'''AdditionalEquations'''
	\|This interface allows users to add their own differential equations to a numerical propagator.		\|This interface allows users to add their own differential equations to a numerical propagator.
	\|[{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/numerical/AdditionalEquations.html ...]		\|[{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/numerical/AdditionalEquations.html ...]
	\|-		\|-
	\|**ModeHandler		\|'''ModeHandler'''
	\|Common interface for all propagator mode handlers initialization.		\|Common interface for all propagator mode handlers initialization.
	\|[{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/numerical/ModeHandler.html ...]		\|[{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/numerical/ModeHandler.html ...]
	\|-		\|-
	\|**TimeDerivativesEquations		\|'''TimeDerivativesEquations'''
	\|Interface summing up the contribution of several forces into orbit and mass derivatives.		\|Interface summing up the contribution of several forces into orbit and mass derivatives.
	\|[{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/numerical/TimeDerivativesEquations.html ...]		\|[{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/numerical/TimeDerivativesEquations.html ...]

Admin le 21 février 2018 à 14:24

2018-02-21T14:24:28Z

Admin : /* Contents */

2018-02-21T10:48:51Z

Contents

@@ Ligne 391 : / Ligne 391 : @@
 == Contents ==
 === Interfaces ===
-|=(% colspan="3" %)Interface|=(% colspan="6" %)Summary|=(% colspan="1" %)Javadoc
+{| class="wikitable"
-|(% colspan="3" %)**AdditionalStateProvider|(% colspan="6" %)This interface represents providers for additional state data beyond SpacecraftState.|(% colspan="1" %)[{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/AdditionalStateProvider.html ...]
+|-
-|(% colspan="3" %)**AdditionalEquations|(% colspan="6" %)This interface allows users to add their own differential equations to a numerical propagator.|(% colspan="1" %)[{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/numerical/AdditionalEquations.html ...]
+! scope="col"| Interface
-|(% colspan="3" %)**ModeHandler|(% colspan="6" %)Common interface for all propagator mode handlers initialization.|(% colspan="1" %)[{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/numerical/ModeHandler.html ...]
+! scope="col"| Summary
-|(% colspan="3" %)**TimeDerivativesEquations|(% colspan="6" %)Interface summing up the contribution of several forces into orbit and mass derivatives.|(% colspan="1" %)[{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/numerical/TimeDerivativesEquations.html ...]
+! scope="col"| Javadoc
 === Classes ===
-|=(% colspan="3" %)Class|=(% colspan="6" %)Summary|=(% colspan="1" %)Javadoc
+{| class="wikitable"
-|(% colspan="3" %)'''NumericalPropagator'''|(% colspan="6" %)This class propagates SpacecraftState using numerical integration.|(% colspan="1" %)[{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/numerical/NumericalPropagator.html ...]
+|-
-|(% colspan="3" %)'''AttitudeEquation'''|(% colspan="6" %)This class represents attitude differential equations.|(% colspan="1" %)[{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/numerical/AttitudeEquation.html ...]
+! scope="col"| Class
-|(% colspan="3" %)'''IntegratedEphemeris'''|(% colspan="6" %)This class stores sequentially generated orbital parameters for later retrieval.|(% colspan="1" %)[{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/precomputed/IntegratedEphemeris.html ...]
+! scope="col"| Summary
-|(% colspan="3" %)'''SimpleAdditionalStateProvider'''|(% colspan="6" %)This class implements AdditionalStateProvider interface. It simply handles a list of dates associated to additional state vectors. For a given date it returns the associated additional state vector or a propagation exception if this date is not found. This class will be basically used with a PVCoordinatePropagator. |(% colspan="1" %)[{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/SimpleAdditionalStateProvider.html ...]
+! scope="col"| Javadoc
 [[Category:User_Manual_4.0_Orbit_Propagation]]

Admin : /* Javadoc */

2018-02-21T10:46:23Z

Javadoc

← Version précédente		Version du 21 février 2018 à 10:46
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	\|-		\|-
	\|Orekit		\|Orekit
	\|[{{~~PathCurrentJavaDoc~~}}/fr/cnes/sirius/patrius/propagation/numerical/package-summary.html Package fr.cnes.sirius.patrius.propagation.numerical]		\|[{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/numerical/package-summary.html Package fr.cnes.sirius.patrius.propagation.numerical]
	\|}		\|}

Admin : /* Javadoc */

2018-02-21T10:46:10Z

Javadoc

← Version précédente		Version du 21 février 2018 à 10:46
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	Some of the numerical propagation packages available are listed here :		Some of the numerical propagation packages available are listed here :

	\|=~~(% colspan~~="3" %)Library~~\|=(% colspan~~="6" %)Javadoc		{\| class="wikitable"
	\|~~(% colspan="3" %)~~Orekit\|~~(% colspan="6" %)~~[{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/numerical/package-summary.html Package fr.cnes.sirius.patrius.propagation.numerical]		\|-
			! scope="col"\| Library
			! scope="col"\| Javadoc
			\|-
			\|Orekit
			\|[{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/numerical/package-summary.html Package fr.cnes.sirius.patrius.propagation.numerical]
			\|}

	=== Links ===		=== Links ===

Admin le 20 février 2018 à 12:12

2018-02-20T12:12:19Z

← Version précédente		Version du 20 février 2018 à 12:12
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	== Introduction ==		== Introduction ==
	=== Scope ===		=== Scope ===
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	\|(% colspan="3" %)'''IntegratedEphemeris'''\|(% colspan="6" %)This class stores sequentially generated orbital parameters for later retrieval.\|(% colspan="1" %)[{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/precomputed/IntegratedEphemeris.html ...]		\|(% colspan="3" %)'''IntegratedEphemeris'''\|(% colspan="6" %)This class stores sequentially generated orbital parameters for later retrieval.\|(% colspan="1" %)[{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/precomputed/IntegratedEphemeris.html ...]
	\|(% colspan="3" %)'''SimpleAdditionalStateProvider'''\|(% colspan="6" %)This class implements AdditionalStateProvider interface. It simply handles a list of dates associated to additional state vectors. For a given date it returns the associated additional state vector or a propagation exception if this date is not found. This class will be basically used with a PVCoordinatePropagator. \|(% colspan="1" %)[{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/SimpleAdditionalStateProvider.html ...]		\|(% colspan="3" %)'''SimpleAdditionalStateProvider'''\|(% colspan="6" %)This class implements AdditionalStateProvider interface. It simply handles a list of dates associated to additional state vectors. For a given date it returns the associated additional state vector or a propagation exception if this date is not found. This class will be basically used with a PVCoordinatePropagator. \|(% colspan="1" %)[{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/SimpleAdditionalStateProvider.html ...]

			[[Category:User_Manual_4.0_Orbit_Propagation]]

Admin : /* Partial derivatives equations = */

2018-02-20T10:37:38Z

Partial derivatives equations =

← Version précédente		Version du 20 février 2018 à 10:37
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	</syntaxhighlight>		</syntaxhighlight>

	=== Partial derivatives equations ====		=== Partial derivatives equations ===

	PATRIUS provides an implementation of the interface "'''''AdditionalEquation'''''". This set of additional equations computes the partial derivatives of the state (orbit) with respect to initial state and force models parameters.		PATRIUS provides an implementation of the interface "'''''AdditionalEquation'''''". This set of additional equations computes the partial derivatives of the state (orbit) with respect to initial state and force models parameters.

Admin : /* Propagation of the attitudes : two possible treatments */

2018-02-20T10:37:28Z

Propagation of the attitudes : two possible treatments

← Version précédente		Version du 20 février 2018 à 10:37
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	To propagate the [{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/attitudes/Attitude.html Attitude], two treatments could be applied :		To propagate the [{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/attitudes/Attitude.html Attitude], two treatments could be applied :
	*compute the attitude with an [{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/attitudes/AttitudeProvider.html AttitudeProvider] :'''''setAttitudeProvider(AttitudeProvider)'''''.		*compute the attitude with an [{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/attitudes/AttitudeProvider.html AttitudeProvider] :'''''setAttitudeProvider(AttitudeProvider)'''''.<br>It is possible to deals with :
	It is possible to deals with :
	**a single attitude by calling '''''setAttitudeProvider(AttitudeProvider)'''''		**a single attitude by calling '''''setAttitudeProvider(AttitudeProvider)'''''
	**two attitudes by calling '''''setAttitudeProviderForces(AttitudeProvider)''''' or '''''setAttitudeProviderEvents(AttitudeProvider)'''''. It is not possible to call '''''setAttitudeProvider(AttitudeProvider)''''' and '''''setAttitudeProviderForces(AttitudeProvider)''''' (or '''''setAttitudeProviderEvents(AttitudeProvider)''''')		**two attitudes by calling '''''setAttitudeProviderForces(AttitudeProvider)''''' or '''''setAttitudeProviderEvents(AttitudeProvider)'''''. It is not possible to call '''''setAttitudeProvider(AttitudeProvider)''''' and '''''setAttitudeProviderForces(AttitudeProvider)''''' (or '''''setAttitudeProviderEvents(AttitudeProvider)''''')
	*propagate the attitude as a 7-dimension additional state :'''''addAttitudeEquation(AttitudeEquation)'''''.<br>In practical terms, the user has to build the additional equation by extending the abstract class [{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/numerical/AttitudeEquation.html AttitudeEquation], call '''''addAttitudeEquation(AttitudeEquation)'''''. The additional state corresponding with the attitude is automatically add to the additional states map of the initial SpacecraftState. An AttitudeEquation is associated with an AttitudeType :		*propagate the attitude as a 7-dimension additional state :'''''addAttitudeEquation(AttitudeEquation)'''''.<br>In practical terms, the user has to build the additional equation by extending the abstract class [{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/numerical/AttitudeEquation.html AttitudeEquation], call '''''addAttitudeEquation(AttitudeEquation)'''''. The additional state corresponding with the attitude is automatically add to the additional states map of the initial SpacecraftState. An AttitudeEquation is associated with an AttitudeType :
	** ATTITUDE : if a single attitude treatment is done. If the user wants to propagate only one attitude.		** ATTITUDE : if a single attitude treatment is done. If the user wants to propagate only one attitude.
	** ATTITUDE_FORCES and ATTITUDE_EVENTS : if a double attitude treatment is done. If the user wants to propagate the attitude for forces computation and the attitude for events computation. See : [FDY_SST_Home SpacecraftState description]		** ATTITUDE_FORCES and ATTITUDE_EVENTS : if a double attitude treatment is done. If the user wants to propagate the attitude for forces computation and the attitude for events computation. See : [FDY_SST_Home SpacecraftState description]<br>It is not possible to add an attitude equation in type ATTITUDE and one in type ATTITUDE_FORCES or ATTITUDE_EVENTS.
	It is not possible to add an attitude equation in type ATTITUDE and one in type ATTITUDE_FORCES or ATTITUDE_EVENTS.

	The following example shows how to propagate a SpacecraftState with an attitude added to the additional states map.		The following example shows how to propagate a SpacecraftState with an attitude added to the additional states map.

Admin : /* Getting Started */

2018-02-20T10:35:45Z

Getting Started

Voir les modifications

Admin : /* Features description */

2018-02-20T09:50:56Z

Features description

← Version précédente		Version du 20 février 2018 à 09:50
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	==== Dormand-Prince integrators ====		==== Dormand-Prince integrators ====

	Adaptive stepsize Dormand-Prince integrators are commonly use in space mechanics. A 5th order and a 8th order Dormand-Prince integrator is available.		Adaptive stepsize Dormand-Prince integrators are commonly use in space mechanics. A 5th order and a 8th order Dormand-Prince integrator is available.<br>
	They have the particularity to have an adaptive step size: during the integration, the integrator tries to keep the integration step as large as possible to save some computation time. The integrator computes the integration step to use by estimating the error made compared to a threshold. The smaller the stepsize, the higher the dynamics of the system.		They have the particularity to have an adaptive step size: during the integration, the integrator tries to keep the integration step as large as possible to save some computation time. The integrator computes the integration step to use by estimating the error made compared to a threshold. The smaller the stepsize, the higher the dynamics of the system.<br>
	As a result, the user is required to provide the following information:		As a result, the user is required to provide the following information:
	* The minimum and maximum allowed step size. The minimum step size should be small enough to handle any integration of the user dynamics. The maximum step size should be high enough to reduce computation times when the dynamics is slow.		* The minimum and maximum allowed step size. The minimum step size should be small enough to handle any integration of the user dynamics. The maximum step size should be high enough to reduce computation times when the dynamics is slow.
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	the propagator (Orbitype.CARTESIAN for cartesian parameters for example).		the propagator (Orbitype.CARTESIAN for cartesian parameters for example).

	Important notice		'''Important notice'''

	Dormand-Prince integrators (as well as Higham-hall integrator) uses only states whose tolerance has been defined to estimate error and deduce integration step.		Dormand-Prince integrators (as well as Higham-hall integrator) uses only states whose tolerance has been defined to estimate error and deduce integration step.<br>
	Tolerance is defined if not set to [absolute tolerance = +inf, relative tolerance = 0].		Tolerance is defined if not set to [absolute tolerance = +inf, relative tolerance = 0].<br>
	By default, tolerances are not set for partial derivatives. As a result, propagation with or without partial dérivatives will return the exact same PV coordinates.		By default, tolerances are not set for partial derivatives. As a result, propagation with or without partial dérivatives will return the exact same PV coordinates.

← Version précédente		Version du 21 février 2018 à 14:24
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	==== Basic propagation ====		==== Basic propagation ====
	Here is presented a basic instanciation of the numerical propagator with an input state built from an [{{~~PathCurrentJavaDoc~~}}/fr/cnes/sirius/patrius/orbits/Orbit.html orbit] and a [{{~~PathCurrentJavaDoc~~}}/fr/cnes/sirius/patrius/propagation/MassProvider.html mass provider].		Here is presented a basic instanciation of the numerical propagator with an input state built from an [{{JavaDoc4.0}}/fr/cnes/sirius/patrius/orbits/Orbit.html orbit] and a [{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/MassProvider.html mass provider].

	See : [SPC_VBU_Home Building assembly]		See : [SPC_VBU_Home Building assembly]
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	* Add mass initial states to state vector:		* Add mass initial states to state vector:

	This is performed by providing a [{{~~PathCurrentJavaDoc~~}}/fr/cnes/sirius/patrius/propagation/MassProvider.html MassProvider] to the initial [{{~~PathCurrentJavaDoc~~}}/fr/cnes/sirius/patrius/propagation/SpacecraftState.html SpacecraftState]. Mass information is automaticaly stored as additional states of the SpacecraftState.		This is performed by providing a [{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/MassProvider.html MassProvider] to the initial [{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/SpacecraftState.html SpacecraftState]. Mass information is automaticaly stored as additional states of the SpacecraftState.

	* Add mass equations to propagator:		* Add mass equations to propagator:

	For each mass additional state associated with the [{{~~PathCurrentJavaDoc~~}}/fr/cnes/sirius/patrius/propagation/SpacecraftState.html SpacecraftState], the corresponding additional equation are added to the [{{~~PathCurrentJavaDoc~~}}/fr/cnes/sirius/patrius/propagation/numerical/NumericalPropagator.html numerical propagator] using '''''setMassProviderEquation(MassProvider)'''''.		For each mass additional state associated with the [{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/SpacecraftState.html SpacecraftState], the corresponding additional equation are added to the [{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/numerical/NumericalPropagator.html numerical propagator] using '''''setMassProviderEquation(MassProvider)'''''.
	Important notice: this method should be called only once and provided mass provider must be mass provider used in force models for global propagation consistency.		Important notice: this method should be called only once and provided mass provider must be mass provider used in force models for global propagation consistency.

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	====Propagation of the attitudes : two possible treatments ====		====Propagation of the attitudes : two possible treatments ====

	To propagate the [{{~~PathCurrentJavaDoc~~}}/fr/cnes/sirius/patrius/attitudes/Attitude.html Attitude], two treatments could be applied :		To propagate the [{{JavaDoc4.0}}/fr/cnes/sirius/patrius/attitudes/Attitude.html Attitude], two treatments could be applied :
	*compute the attitude with an [{{~~PathCurrentJavaDoc~~}}/fr/cnes/sirius/patrius/attitudes/AttitudeProvider.html AttitudeProvider] :'''''setAttitudeProvider(AttitudeProvider)'''''.<br>It is possible to deals with :		*compute the attitude with an [{{JavaDoc4.0}}/fr/cnes/sirius/patrius/attitudes/AttitudeProvider.html AttitudeProvider] :'''''setAttitudeProvider(AttitudeProvider)'''''.<br>It is possible to deals with :
	**a single attitude by calling '''''setAttitudeProvider(AttitudeProvider)'''''		**a single attitude by calling '''''setAttitudeProvider(AttitudeProvider)'''''
	**two attitudes by calling '''''setAttitudeProviderForces(AttitudeProvider)''''' or '''''setAttitudeProviderEvents(AttitudeProvider)'''''. It is not possible to call '''''setAttitudeProvider(AttitudeProvider)''''' and '''''setAttitudeProviderForces(AttitudeProvider)''''' (or '''''setAttitudeProviderEvents(AttitudeProvider)''''')		**two attitudes by calling '''''setAttitudeProviderForces(AttitudeProvider)''''' or '''''setAttitudeProviderEvents(AttitudeProvider)'''''. It is not possible to call '''''setAttitudeProvider(AttitudeProvider)''''' and '''''setAttitudeProviderForces(AttitudeProvider)''''' (or '''''setAttitudeProviderEvents(AttitudeProvider)''''')
	*propagate the attitude as a 7-dimension additional state :'''''addAttitudeEquation(AttitudeEquation)'''''.<br>In practical terms, the user has to build the additional equation by extending the abstract class [{{~~PathCurrentJavaDoc~~}}/fr/cnes/sirius/patrius/propagation/numerical/AttitudeEquation.html AttitudeEquation], call '''''addAttitudeEquation(AttitudeEquation)'''''. The additional state corresponding with the attitude is automatically add to the additional states map of the initial SpacecraftState. An AttitudeEquation is associated with an AttitudeType :		*propagate the attitude as a 7-dimension additional state :'''''addAttitudeEquation(AttitudeEquation)'''''.<br>In practical terms, the user has to build the additional equation by extending the abstract class [{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/numerical/AttitudeEquation.html AttitudeEquation], call '''''addAttitudeEquation(AttitudeEquation)'''''. The additional state corresponding with the attitude is automatically add to the additional states map of the initial SpacecraftState. An AttitudeEquation is associated with an AttitudeType :
	** ATTITUDE : if a single attitude treatment is done. If the user wants to propagate only one attitude.		** ATTITUDE : if a single attitude treatment is done. If the user wants to propagate only one attitude.
	** ATTITUDE_FORCES and ATTITUDE_EVENTS : if a double attitude treatment is done. If the user wants to propagate the attitude for forces computation and the attitude for events computation. See : [FDY_SST_Home SpacecraftState description]<br>It is not possible to add an attitude equation in type ATTITUDE and one in type ATTITUDE_FORCES or ATTITUDE_EVENTS.		** ATTITUDE_FORCES and ATTITUDE_EVENTS : if a double attitude treatment is done. If the user wants to propagate the attitude for forces computation and the attitude for events computation. See : [FDY_SST_Home SpacecraftState description]<br>It is not possible to add an attitude equation in type ATTITUDE and one in type ATTITUDE_FORCES or ATTITUDE_EVENTS.

User Manual 4.0 Numerical propagation - Historique des versions

Admin : /* Interfaces */

Admin le 21 février 2018 à 14:24

Admin : /* Contents */

Admin : /* Javadoc */

Admin : /* Javadoc */

Admin le 20 février 2018 à 12:12

Admin : /* Partial derivatives equations = */

Admin : /* Propagation of the attitudes : two possible treatments */

Admin : /* Getting Started */

Admin : /* Features description */

Admin : /* Interfaces */

Admin : /* Contents */

Admin : /* Javadoc */

Admin : /* Javadoc */

Admin : /* Partial derivatives equations = */

Admin : /* Propagation of the attitudes : two possible treatments */

Admin : /* Getting Started */

Admin : /* Features description */