User Manual 3.3 Numerical propagation - Historique des versions

Admin : /* Propagation mode */

2018-04-03T14:16:41Z

Propagation mode

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 See : {{siteLink label="propagation mode description" jd="OR" suffix="architecture/propagation.html"/}}. Note : Two errors are in that tutorial : getITRF2005() was replaced by getITRF(). VisibilityDetector was replaced by VisibilityFromStationDetector
-|=(% colspan="3" %)Use case|=(% colspan="6" %)without dense output|=(% colspan="9" %)with dense output|=(% colspan="12" %)with event detection|=(% colspan="15" %)with step handler
+{| class="wikitable"
-|(% colspan="3" %)slave|(% colspan="6" %)+ faster than the others since it has no step handler|(% colspan="9" %)- not adapted when it comes to generate a dense output|(% colspan="12" %)+ adapted|(% colspan="15" %)- not adapted
+|-
-|(% colspan="3" %)master|(% colspan="6" %)- not really adapted|(% colspan="9" %)- not really adapted (could be adapted with a specific step handler)|(% colspan="12" %)+ adapted|(% colspan="15" %)+ adapted
+! scope="col"| Use case
-|(% colspan="3" %)ephemeris generation|(% colspan="6" %)- not really adapted|(% colspan="9" %)+ adapted|(% colspan="12" %)+ adapted|(% colspan="15" %)- not adapted
+! scope="col"| without dense output

Admin le 3 avril 2018 à 13:57

2018-04-03T13:57:41Z

← Version précédente		Version du 3 avril 2018 à 13:57
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	The PATRIUS library offers different propagators :		The PATRIUS library offers different propagators :
	* Numerical propagator		* Numerical propagator
	* Analytical propagators (Keplerian, Eckstein-Hechler, J2 secular, Lyddane secular and long period) (see [~~ORB_ANA_Home~~ dedicated User Manual])		* Analytical propagators (Keplerian, Eckstein-Hechler, J2 secular, Lyddane secular and long period) (see [[User Manual 3.3 Analytical propagation\|dedicated User Manual]].)
	* Analytical 2D propagator (see [[User Manual 3.3 Analytical propagation\|dedicated User Manual]])		* Analytical 2D propagator (see [[User Manual 3.3 Analytical propagation\|dedicated User Manual]])
	* TLE propagator (Two Line Element) (see [[User Manual 3.3 Analytical propagation\|dedicated User Manual]])		* TLE propagator (Two Line Element) (see [[User Manual 3.3 Analytical propagation\|dedicated User Manual]])

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

2018-03-06T10:06:10Z

Propagation of the attitudes : two possible treatments

← Version précédente		Version du 6 mars 2018 à 10:06
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	===== Propagation of the attitudes : two possible treatments =====		===== Propagation of the attitudes : two possible treatments =====
	To propagate the [{{JavaDoc3.3}}/org/orekit/attitudes/Attitude.html Attitude], two treatments could be applied :		To propagate the [{{JavaDoc3.3}}/org/orekit/attitudes/Attitude.html Attitude], two treatments could be applied :
	* compute the attitude with an [{{JavaDoc3.3}}/org/orekit/attitudes/AttitudeProvider.html AttitudeProvider] : '''''setAttitudeProvider(AttitudeProvider)'''''.		* compute the attitude with an [{{JavaDoc3.3}}/org/orekit/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 [{{JavaDoc3.3}}/org/orekit/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)'''''.
	In practical terms, the user has to build the additional equation by extending the abstract class [{{JavaDoc3.3}}/org/orekit/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 : [[User Manual 3.3 SpacecraftState\|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 : [[User Manual 3.3 SpacecraftState\|SpacecraftState description]]

Admin : /* Classes */

2018-03-06T09:51:38Z

Classes

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	\|[{{JavaDoc3.3}}/org/orekit/propagation/precomputed/IntegratedEphemeris.html ...]		\|[{{JavaDoc3.3}}/org/orekit/propagation/precomputed/IntegratedEphemeris.html ...]
	\|-		\|-
	~~ropagator.html"/}}~~
	\|'''SimpleAdditionalStateProvider'''		\|'''SimpleAdditionalStateProvider'''
	\|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.		\|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.

Admin : /* Partial derivatives equations = */

2018-03-01T14:13:16Z

Partial derivatives equations =

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	</syntaxhighlight>		</syntaxhighlight>

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

	OREKIT 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.		OREKIT 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.
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	Note : the dYdY0 terms are given according to the orbit type known to the propagator. If one wants to compute the partial derivatives with equinoctial parameters, then one should specify it to the propagator first, using the method NumericalPropagator.setOrbitType(OrbitType). Additionally, it is also important to specify the correct orbit position angle type (true, mean or eccentric- if the orbit requires it), using the methods NumericalPropagator.setPositionAngleType(PositionAngle).		Note : the dYdY0 terms are given according to the orbit type known to the propagator. If one wants to compute the partial derivatives with equinoctial parameters, then one should specify it to the propagator first, using the method NumericalPropagator.setOrbitType(OrbitType). Additionally, it is also important to specify the correct orbit position angle type (true, mean or eccentric- if the orbit requires it), using the methods NumericalPropagator.setPositionAngleType(PositionAngle).


	== Tutorials ==		== Tutorials ==

Admin : /* Propagation */

2018-03-01T14:12:44Z

Propagation

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	==== Propagation ====		==== Propagation ====

	See : [~~FDY_SST_Home~~ SpacecraftState description]		See : [[User Manual 3.3 SpacecraftState\|SpacecraftState description]]

	Numerical propagation can be executed in cartesian, equinoctial, keplerian and circular parameters. By default, equinoctial parameters are used.		Numerical propagation can be executed in cartesian, equinoctial, keplerian and circular parameters. By default, equinoctial parameters are used.
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	Here is presented a basic instanciation of the numerical propagator with an input state built from an [{{JavaDoc3.3}}/org/orekit/orbits/Orbit.html orbit] and a [{{JavaDoc3.3}}/org/orekit/propagation/MassProvider.html mass provider].		Here is presented a basic instanciation of the numerical propagator with an input state built from an [{{JavaDoc3.3}}/org/orekit/orbits/Orbit.html orbit] and a [{{JavaDoc3.3}}/org/orekit/propagation/MassProvider.html mass provider].

	See : [~~SPC_VBU_Home~~ Building assembly]		See : [[User Manual 3.3 Assemblies in PATRIUS: Building and using an assembly\|Building assembly]]

	<syntaxhighlight lang="java">		<syntaxhighlight lang="java">
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	In practical terms, the user has to build the additional equation by extending the abstract class [{{JavaDoc3.3}}/org/orekit/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 :		In practical terms, the user has to build the additional equation by extending the abstract class [{{JavaDoc3.3}}/org/orekit/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 : [[User Manual 3.3 SpacecraftState\|SpacecraftState description]]
	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.

Admin : /* Features Description */

2018-03-01T14:09:14Z

Features Description

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	* Numerical propagator		* Numerical propagator
	* Analytical propagators (Keplerian, Eckstein-Hechler, J2 secular, Lyddane secular and long period) (see [ORB_ANA_Home dedicated User Manual])		* Analytical propagators (Keplerian, Eckstein-Hechler, J2 secular, Lyddane secular and long period) (see [ORB_ANA_Home dedicated User Manual])
	* Analytical 2D propagator (see [~~ORB_ANA_Home~~ dedicated User Manual])		* Analytical 2D propagator (see [[User Manual 3.3 Analytical propagation\|dedicated User Manual]])
	* TLE propagator (Two Line Element) (see [~~ORB_ANA_Home~~ dedicated User Manual])		* TLE propagator (Two Line Element) (see [[User Manual 3.3 Analytical propagation\|dedicated User Manual]])
	* Precomputed ephemeris propagator (see [~~ORB_ANA_Home~~ dedicated User Manual])		* Precomputed ephemeris propagator (see [[User Manual 3.3 Analytical propagation\|dedicated User Manual]])
	* The STELA propagator (see [~~ORB_GTO_Home~~ dedicated User Manual])		* The STELA propagator (see [[User Manual 3.3 Semi-analytical propagation\|dedicated User Manual]])

	=== Partial Derivatives===		=== Partial Derivatives===

Admin : /* Introduction */

2018-03-01T14:07:18Z

Introduction

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	=== Scope ===		=== Scope ===
	This section describes the numerical propagator provided by the Orekit Library: basic orbit propagation, mass, partial derivatives and additional equations.		This section describes the numerical propagator provided by the Orekit Library: basic orbit propagation, mass, partial derivatives and additional equations.
	Analytical propagators are détails in [~~ORB_ANA_Home~~ Analytical propagation].		Analytical propagators are détails in [[User Manual 3.3 Analytical propagation\|Analytical propagation]].

	=== Javadoc ===		=== Javadoc ===

Admin : /* Interfaces */

2018-02-28T10:34:25Z

Interfaces

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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.
	\|[{{JavaDoc3.3}}/org/orekit/propagation/AdditionalStateProvider.html ...]		\|[{{JavaDoc3.3}}/org/orekit/propagation/AdditionalStateProvider.html ...]
	\|-		\|-
	\|**BoundedPropagator		\|'''BoundedPropagator'''
	\|This interface is intended for ephemerides valid only during a time range.		\|This interface is intended for ephemerides valid only during a time range.
	\|[{{JavaDoc3.3}}/org/orekit/propagation/BoundedPropagator.html ...]		\|[{{JavaDoc3.3}}/org/orekit/propagation/BoundedPropagator.html ...]
	\|-		\|-
	\|**Propagator		\|'''Propagator'''
	\|This interface provides a way to propagate an orbit at any time.		\|This interface provides a way to propagate an orbit at any time.
	\|[{{JavaDoc3.3}}/org/orekit/propagation/Propagator.html ...]		\|[{{JavaDoc3.3}}/org/orekit/propagation/Propagator.html ...]
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	! scope="col"\| Javadoc		! scope="col"\| Javadoc
	\|-		\|-
	\|**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.
	\|[{{JavaDoc3.3}}/org/orekit/propagation/numerical/AdditionalEquations.html ...]		\|[{{JavaDoc3.3}}/org/orekit/propagation/numerical/AdditionalEquations.html ...]
	\|-		\|-
	\|**ModeHandler		\|'''ModeHandler'''
	\|Common interface for all propagator mode handlers initialization.		\|Common interface for all propagator mode handlers initialization.
	\|[{{JavaDoc3.3}}/org/orekit/propagation/numerical/ModeHandler.html ...]		\|[{{JavaDoc3.3}}/org/orekit/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.
	\|[{{JavaDoc3.3}}/org/orekit/propagation/numerical/TimeDerivativesEquations.html ...]		\|[{{JavaDoc3.3}}/org/orekit/propagation/numerical/TimeDerivativesEquations.html ...]

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

2018-02-28T10:32:42Z

Propagation of the attitudes : two possible treatments

← Version précédente		Version du 28 février 2018 à 10:32
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	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)'''''.		* propagate the attitude as a 7-dimension additional state : '''''addAttitudeEquation(AttitudeEquation)'''''.
	In practical terms, the user has to build the additional equation by extending the abstract class [{{JavaDoc3.3}}/org/orekit/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 :		In practical terms, the user has to build the additional equation by extending the abstract class [{{JavaDoc3.3}}/org/orekit/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 :
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	final SpacecraftState finalState = p.propagate(date.shiftedBy(propagationDuration));		final SpacecraftState finalState = p.propagate(date.shiftedBy(propagationDuration));
	</syntaxhighlight>		</syntaxhighlight>


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

User Manual 3.3 Numerical propagation - Historique des versions

Admin : /* Propagation mode */

Admin le 3 avril 2018 à 13:57

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

Admin : /* Classes */

Admin : /* Partial derivatives equations = */

Admin : /* Propagation */

Admin : /* Features Description */

Admin : /* Introduction */

Admin : /* Interfaces */

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

Admin : /* Propagation mode */

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

Admin : /* Classes */

Admin : /* Partial derivatives equations = */

Admin : /* Propagation */

Admin : /* Features Description */

Admin : /* Introduction */

Admin : /* Interfaces */

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