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== Introduction ==
 
== Introduction ==
 
=== Scope ===
 
=== Scope ===
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All the classes related to numerical propagation are in the <code>fr.cnes.sirius.patrius.propagation.numerical.multi</code> package of the Patrius library. The classes related to events detection are in the package <code>fr.cnes.sirius.patrius.propagation.events.multi</code> of the Patrius library.  But the interface for multi event detectors is in <code>fr.cnes.sirius.patrius.propagation.events.multi</code> package of the Patrius library.
 
All the classes related to numerical propagation are in the <code>fr.cnes.sirius.patrius.propagation.numerical.multi</code> package of the Patrius library. The classes related to events detection are in the package <code>fr.cnes.sirius.patrius.propagation.events.multi</code> of the Patrius library.  But the interface for multi event detectors is in <code>fr.cnes.sirius.patrius.propagation.events.multi</code> package of the Patrius library.
  
|=(% colspan="3" %)Library|=(% colspan="6" %)Javadoc
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|(% colspan="3" %)Patrius |(% colspan="6" %)[{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/events/multi/package-summary.html Package fr.cnes.sirius.patrius.propagation.events.multi]
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=== Links ===
 
=== Links ===
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==== Multi Numerical Propagator ====
 
==== Multi Numerical Propagator ====
  
The multi propagator architecture is copied from [{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/Propagator.html Propagator] interface and [{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/numerical/NumericalPropagator.html NumericalPropagator] class, and added to PATRIUS library.
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The multi propagator architecture is copied from [{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/Propagator.html Propagator] interface and [{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/numerical/NumericalPropagator.html NumericalPropagator] class, and added to PATRIUS library.
  
 
[[File:MultiNumericalPropagator.png|center|600px]]
 
[[File:MultiNumericalPropagator.png|center|600px]]
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== Features Description ==
 
== Features Description ==
The PATRIUS library offers a [{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/numerical/multi/MultiNumericalPropagator.html multi numerical propagator]. It aims at propagating several [{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/SpacecraftState.html SpacecraftState] at the same time using numerical propagation. The N [{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/SpacecraftState.html SpacecraftState] are propagated during the same time interval using the same [{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/math/ode/FirstOrderIntegrator.html FirstOrderIntegrator].
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The PATRIUS library offers a [{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/numerical/multi/MultiNumericalPropagator.html multi numerical propagator]. It aims at propagating several [{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/SpacecraftState.html SpacecraftState] at the same time using numerical propagation. The N [{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/SpacecraftState.html SpacecraftState] are propagated during the same time interval using the same [{{JavaDoc4.0}}/fr/cnes/sirius/patrius/math/ode/FirstOrderIntegrator.html FirstOrderIntegrator].
  
 
Each state is identified with an ID of type String. All states can be completely different but they should have the same internal date.
 
Each state is identified with an ID of type String. All states can be completely different but they should have the same internal date.
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=== Create propagator from FirstOrderIntegrator ===
 
=== Create propagator from FirstOrderIntegrator ===
  
The [{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/numerical/multi/MultiNumericalPropagator.html MultiNumericalPropagator] should be created by giving a [{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/math/ode/FirstOrderIntegrator.html FirstOrderIntegrator].
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The [{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/numerical/multi/MultiNumericalPropagator.html MultiNumericalPropagator] should be created by giving a [{{JavaDoc4.0}}/fr/cnes/sirius/patrius/math/ode/FirstOrderIntegrator.html FirstOrderIntegrator].
  
 
<code>final MultiNumericalPropagator propagator = new MultiNumericalPropagator(integrator);</code>
 
<code>final MultiNumericalPropagator propagator = new MultiNumericalPropagator(integrator);</code>
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=== Add additional equations ===
 
=== Add additional equations ===
As for the [{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/numerical/NumericalPropagator.html NumericalPropagator], additional equations corresponding to the additional states of each states should be added to the propagator.
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As for the [{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/numerical/NumericalPropagator.html NumericalPropagator], additional equations corresponding to the additional states of each states should be added to the propagator.
  
 
These additional equations are given to the multi numerical propagator for a specific state thanks to the following methods :
 
These additional equations are given to the multi numerical propagator for a specific state thanks to the following methods :
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=== Propagate the attitude ===
 
=== Propagate the attitude ===
  
As for the [{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/numerical/NumericalPropagator.html NumericalPropagator], to propagate the [{{PathCurrentJavaDoc}}//fr/cnes/sirius/patrius/attitudes/Attitude.html Attitude] of a specific state, two treatments could be applied :  
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As for the [{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/numerical/NumericalPropagator.html NumericalPropagator], to propagate the [{{JavaDoc4.0}}/fr/cnes/sirius/patrius/attitudes/Attitude.html Attitude] of a specific state, two treatments could be applied :
*compute the attitude with an [{{PathCurrentJavaDoc}}''fr/cnes/sirius/patrius/attitudes/AttitudeProvider.html AttitudeProvider] :'''''setAttitudeProvider(AttitudeProvider, String)//'''.
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It is possible to deals with :  
+
*compute the attitude with an [{{JavaDoc4.0}}/fr/cnes/sirius/patrius/attitudes/AttitudeProvider.html AttitudeProvider] : '''''setAttitudeProvider(AttitudeProvider, String)'''''.<br>It is possible to deals with :  
**a single attitude by calling'''''setAttitudeProvider(AttitudeProvider, String)'''''
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**a single attitude by calling '''''setAttitudeProvider(AttitudeProvider, String)'''''
'''two attitudes by calling'''''setAttitudeProviderForces(AttitudeProvider, String)''''' or '''''setAttitudeProviderEvents(AttitudeProvider, String)''**. It is not possible to call **''setAttitudeProvider(AttitudeProvider, String)''** and **''setAttitudeProviderForces(AttitudeProvider, String)''** (or **''setAttitudeProviderEvents(AttitudeProvider, String)''**)
+
**two attitudes by calling '''''setAttitudeProviderForces(AttitudeProvider, String)''''' or '''''setAttitudeProviderEvents(AttitudeProvider, String)'''''. It is not possible to call '''''setAttitudeProvider(AttitudeProvider, String)''''' and '''''setAttitudeProviderForces(AttitudeProvider, String)''''' (or '''''setAttitudeProviderEvents(AttitudeProvider, String)''''')
*propagate the attitude as a 7-dimension additional state :'''''addAttitudeEquation(AttitudeEquation, String)'''''.
+
*propagate the attitude as a 7-dimension additional state : '''''addAttitudeEquation(AttitudeEquation, String)'''''.<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, String)'''''.
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, String)//'''.
+
  
 
See [ORB_PRO_UseP mono numerical propagation] chapter for more details.
 
See [ORB_PRO_UseP mono numerical propagation] chapter for more details.
  
 
=== Set the central attraction coefficient ===
 
=== Set the central attraction coefficient ===
For each state, the central attraction coefficient used in the integration process could be defined with the method'''''setMu(double, String)'''''.
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For each state, the central attraction coefficient used in the integration process could be defined with the method '''''setMu(double, String)'''''.
If for a specific state, this method was not called, the central attraction coefficient of the orbit is used in the integration process.
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If for a specific state, this method was not called, the central attraction coefficient of the orbit is used in the integration process.<br>
T and '''''getFrame(String)'''''.  
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The central attraction coefficient and the frame used in the integration process could be retrieved for a specific state using '''''getMu(String)''''' and '''''getFrame(String)'''''.  
  
 
<syntaxhighlight lang="java">
 
<syntaxhighlight lang="java">
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=== Add event detector ===
 
=== Add event detector ===
 
The user could add :  
 
The user could add :  
*an [{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/events/EventDetector.html EventDetector] associated with a specific state using'''''addEventDetector(EventDetector, String)'''''
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*an [{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/events/EventDetector.html EventDetector] associated with a specific state using '''''addEventDetector(EventDetector, String)'''''
*a [{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/events/multi/MultiEventDetector.html MultiEventDetector] associated with several states added to the propagator using'''''addEventDetector(MultiEventDetector)'''''
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*a [{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/events/multi/MultiEventDetector.html MultiEventDetector] associated with several states added to the propagator using '''''addEventDetector(MultiEventDetector)'''''
  
See [MIS_EVT_Home events presentation ] and [MIS_MEVEN_Home multi events presentation ] chapters for more details.
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See [MIS_EVT_Home events presentation] and [MIS_MEVEN_Home multi events presentation] chapters for more details.
  
 
== Contents ==
 
== Contents ==
 
=== Interfaces ===
 
=== Interfaces ===
|=(% colspan="3" %)Interface|=(% colspan="6" %)Summary|=(% colspan="1" %)Javadoc
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{| class="wikitable"
|(% colspan="3" %)**MultiPropagator|(% colspan="6" %)This interface provides a way to propagate several states at any time.|(% colspan="1" %)[{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/MultiPropagator.html ...]
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|-
|(% colspan="3" %)**MultiModeHandler|(% colspan="6" %)Common interface for all multi propagator mode handlers initialization.|(% colspan="1" %)[{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/numerical/multi/MultiModeHandler.html ...]
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! scope="col"| Interface
 +
! scope="col"| Summary
 +
! scope="col"| Javadoc
 +
|-
 +
|**MultiPropagator
 +
|This interface provides a way to propagate several states at any time.
 +
|[{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/MultiPropagator.html ...]
 +
|-
 +
|**MultiModeHandler
 +
|Common interface for all multi propagator mode handlers initialization.
 +
|[{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/numerical/multi/MultiModeHandler.html ...]
 +
|}
  
 
=== Classes ===
 
=== Classes ===
|=(% colspan="3" %)Class|=(% colspan="6" %)Summary|=(% colspan="1" %)Javadoc
+
{| class="wikitable"
|(% colspan="3" %)'''SpacecraftState'''|(% colspan="6" %)This class is the representation of a complete state holding orbit, attitude for forces and for events computation and additional states at a given date.|(% colspan="1" %){{JDLink label="..." jd="OR" suffix="fr/cnes/sirius/patrius/propagation
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|-
/SpacecraftState.html"/}}
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! scope="col"| Class
|(% colspan="3" %)'''MultiNumericalPropagator'''|(% colspan="6" %)This class propagates several SpacecraftState using numerical integration.|(% colspan="1" %)[{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/numerical/multi/MultiNumericalPropagator.html ...]
+
! scope="col"| Summary
|(% colspan="3" %)'''AttitudeEquation'''|(% colspan="6" %)This class represents attitude differential equations.|(% colspan="1" %){{JDLink label="..." jd="OR" suffix="fr/cnes/sirius/patrius/propagation
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! scope="col"| Javadoc
/numerical/AttitudeEquation.html"/}}
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|-
|(% colspan="3" %)'''MultiIntegratedEphemeris'''|(% colspan="6" %)This class stores sequentially generated orbital parameters for later retrieval.|(% colspan="1" %)[{{PathCurrentJavaDoc}}/fr/cnes/sirius/patrius/propagation/precomputed/multi/MultiIntegratedEphemeris.html ...]
+
|'''SpacecraftState'''
 +
|This class is the representation of a complete state holding orbit, attitude for forces and for events computation and additional states at a given date.
 +
|[{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/SpacecraftState.html ...]
 +
|-
 +
|'''MultiNumericalPropagator'''
 +
|This class propagates several SpacecraftState using numerical integration.
 +
|[{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/numerical/multi/MultiNumericalPropagator.html ...]
 +
|-
 +
|'''AttitudeEquation'''
 +
|This class represents attitude differential equations.
 +
|[{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/numerical/AttitudeEquation.html ...]
 +
|-
 +
|'''MultiIntegratedEphemeris'''
 +
|This class stores sequentially generated orbital parameters for later retrieval.
 +
|[{{JavaDoc4.0}}/fr/cnes/sirius/patrius/propagation/precomputed/multi/MultiIntegratedEphemeris.html ...]
 +
|}
 +
 
 +
[[Category:User_Manual_4.0_Orbit_Propagation]]

Version actuelle en date du 21 février 2018 à 14:24

Introduction

Scope

This section describes the multi propagator provided by the Patrius library. At this time, only numerical propagator is available for multi spacecraft propagation. Generic features about propagators as well as other type of propagators are detailed [ORB_PGEN_Home here].

Javadoc

All the classes related to numerical propagation are in the fr.cnes.sirius.patrius.propagation.numerical.multi package of the Patrius library. The classes related to events detection are in the package fr.cnes.sirius.patrius.propagation.events.multi of the Patrius library. But the interface for multi event detectors is in fr.cnes.sirius.patrius.propagation.events.multi package of the Patrius library.


Library Javadoc
Patrius Package fr.cnes.sirius.patrius.propagation.events.multi
Patrius Package fr.cnes.sirius.patrius.events.multi
Patrius Package fr.cnes.sirius.patrius.propagation.events.multi
Patrius Package fr.cnes.sirius.patrius.propagation.numerical.multi
Patrius Package fr.cnes.sirius.patrius.propagation.precomputed.multi
Patrius Package fr.cnes.sirius.patrius.propagation.sampling.multi

Links

Other useful links can be found here :

  • [ORB_PRO_Home Classical propagation chapter]
  • [FDY_SST_Home SpacecraftState chapter]

Useful Documents

None as of now.

Package Overview

Multi Numerical Propagator

The multi propagator architecture is copied from Propagator interface and NumericalPropagator class, and added to PATRIUS library.

MultiNumericalPropagator.png

Three propagation modes

Like single spacecraft propagation, the multi spacecraft propagation can be performed in different propagation modes : slave, master and ephemeris generation. The architecture of the classes responsible for theses propagation modes are presented below :

MultiPropagationModes.png

Features Description

The PATRIUS library offers a multi numerical propagator. It aims at propagating several SpacecraftState at the same time using numerical propagation. The N SpacecraftState are propagated during the same time interval using the same FirstOrderIntegrator.

Each state is identified with an ID of type String. All states can be completely different but they should have the same internal date.

As for the mono-satellite numerical propagation, it is possible to define the following global propagation parameters:

  • The type of orbital parameters and position angle
  • The propagation mode

For each state, it is possible to configure the following elements:

  • The central attraction coefficient
  • The force models
  • The tolerances used for orbital parameters and the tolerances applied on additional states.
  • The additional states equations associated with the additional states
  • The attitude providers

It is possible to define event detectors applied on a specific state or global event detectors applied on several states.

Getting started

Here is presented a basic instanciation of the multi numerical propagator.

Create propagator from FirstOrderIntegrator

The MultiNumericalPropagator should be created by giving a FirstOrderIntegrator.

final MultiNumericalPropagator propagator = new MultiNumericalPropagator(integrator);

The integrator could be declared using absolute and relative tolerances represented by  :

  • a scalar value
final double abstolScal = 1.0e-10;
final double reltolScal = 1.0e-10;
final FirstOrderIntegrator integratorScal = new DormandPrince853Integrator(0.001, 200, abstolScal, reltolScal);
  • a vector
final double[] abstolVec = { 1e-5, 1e-5, 1e-5, 1e-8, 1e-8, 1e-8};
final double[] reltolVec = { 1e-10, 1e-10, 1e-10, 1e-10, 1e-10, 1e-10};
final FirstOrderIntegrator integratorVec = new DormandPrince853Integrator(0.1, 60., abstolVec, reltolVec);

The orbit tolerances (vector or scalar tolerances) given to the integrator are used as default tolerances. The orbit tolerances could be defined in vector type using the method setOrbitTolerance.

The integrator could be changed by using the method setIntegrator(final FirstOrderIntegrator integrator).

Add initial states

Initial states could be added to the propagator using the method addInitialState(SpacecraftState, String). Each added state is defined by a unique ID. An error is raised if :

  • the input spacecraft ID is empty or null.
  • a state with the same ID was already added to the propagator.
  • the date associated with the added state is different from the date associated with the states previously added. (All states are propagated from the same date).

Note that, the initial state should be added before adding an additional equation, an attitude provider, a force model, an event ... etc ... associated with this state. Otherwise, the input spacecraft Id will not be recognized.

The map of the added states could be retrieved with getInitialStates()

Add additional equations

As for the NumericalPropagator, additional equations corresponding to the additional states of each states should be added to the propagator.

These additional equations are given to the multi numerical propagator for a specific state thanks to the following methods :

  • addAdditionalEquation(AdditionalEquation, String)
  • addAttitudeEquation(AttitudeEquation, String)
  • setMassProviderEquation(MassProvider, String) (This method should be called only once, mass provider must be mass provider used in force models)

The method setAdditionalStateTolerance(String, double[], double[]) may be used to add variation tolerance values (absolute and relative) to a specific additional state.

For each state, the additional states should correspond with the added additional equations (same name, same size).

See [ORB_PRO_UseP mono numerical propagation] chapter for more details.

The following example shows how to propagate two basic SpacecraftState :

// Initial date
final AbsoluteDate date = AbsoluteDate.J2000_EPOCH;
 
// Constants
final double mu = Constants.EGM96_EARTH_MU;
final Frame gcrf = FramesFactory.getGCRF();
final String STATE1 = "STATE1";
final String STATE2 = "STATE2";
final String BODY = "body";
 
// First initial state
final Orbit orbit1 = new KeplerianOrbit(7500000, 0.001, 0.40, 0, 0, 0,PositionAngle.MEAN, gcrf, date, mu);
final MassProvider massModel = new SimpleMassModel(1000., BODY);
final SpacecraftState state1 = new SpacecraftState(orbit1, massModel);
 
// Second initial state
final Vector3D position = new Vector3D(7.0e6, 1.0e6, 4.0e6);
final Vector3D velocity = new Vector3D(-500.0, 8000.0, 1000.0);
final Orbit orbit2 = new EquinoctialOrbit(new PVCoordinates(position, velocity), gcrf, date, mu);
final AttitudeProvider law = new ConstantAttitudeLaw(FramesFactory.getEME2000(), Rotation.IDENTITY);
final Attitude attitude = law.getAttitude(orbit2, date, gcrf);
final SpacecraftState state2 = new SpacecraftState(orbit2, attitude);
 
// Add initial states to the propagator
propagator.addInitialState(state1, STATE1);
propagator.addInitialState(state2, STATE2);
 
// Add additional equation associated with the mass model of the first state
// Mass provider must be mass provider used in force models.
propagator.setMassProviderEquation(massModel, STATE1);
propagator.setAdditionalStateTolerance("MASS_" + BODY, new double[]{1e-7}, new double[]{1e-7}, STATE1);
 
// Set attitude provider associated with the second state
propagator.setAttitudeProvider(law, STATE2);
 
// propagation
final Map<String, SpacecraftState> finalStates = propagator.propagate(date.shiftedBy(propagationDuration));

Propagate the attitude

As for the NumericalPropagator, to propagate the Attitude of a specific state, two treatments could be applied :

  • compute the attitude with an AttitudeProvider : setAttitudeProvider(AttitudeProvider, String).
    It is possible to deals with :
    • a single attitude by calling setAttitudeProvider(AttitudeProvider, String)
    • two attitudes by calling setAttitudeProviderForces(AttitudeProvider, String) or setAttitudeProviderEvents(AttitudeProvider, String). It is not possible to call setAttitudeProvider(AttitudeProvider, String) and setAttitudeProviderForces(AttitudeProvider, String) (or setAttitudeProviderEvents(AttitudeProvider, String))
  • propagate the attitude as a 7-dimension additional state : addAttitudeEquation(AttitudeEquation, String).
    In practical terms, the user has to build the additional equation by extending the abstract class AttitudeEquation, call addAttitudeEquation(AttitudeEquation, String).

See [ORB_PRO_UseP mono numerical propagation] chapter for more details.

Set the central attraction coefficient

For each state, the central attraction coefficient used in the integration process could be defined with the method setMu(double, String). If for a specific state, this method was not called, the central attraction coefficient of the orbit is used in the integration process.
The central attraction coefficient and the frame used in the integration process could be retrieved for a specific state using getMu(String) and getFrame(String).

propagator.setMu(mu, STATE1);
final double muState1 = propagator.getMu(STATE1);
final Frame frameState1 = propagator.getFrame(STATE1);

Add force model

For each state, a force model could be added to the list of forces used at each step by the propagator.

propagator.addForceModel(model, STATE1);

See [ORB_PHY_Home force model] chapter for more details.

Add event detector

The user could add :

  • an EventDetector associated with a specific state using addEventDetector(EventDetector, String)
  • a MultiEventDetector associated with several states added to the propagator using addEventDetector(MultiEventDetector)

See [MIS_EVT_Home events presentation] and [MIS_MEVEN_Home multi events presentation] chapters for more details.

Contents

Interfaces

Interface Summary Javadoc
**MultiPropagator This interface provides a way to propagate several states at any time. ...
**MultiModeHandler Common interface for all multi propagator mode handlers initialization. ...

Classes

Class Summary Javadoc
SpacecraftState This class is the representation of a complete state holding orbit, attitude for forces and for events computation and additional states at a given date. ...
MultiNumericalPropagator This class propagates several SpacecraftState using numerical integration. ...
AttitudeEquation This class represents attitude differential equations. ...
MultiIntegratedEphemeris This class stores sequentially generated orbital parameters for later retrieval. ...