User Manual 4.14 Multi events detection : Différence entre versions

Version actuelle en date du 5 septembre 2024 à 15:26

Introduction

Scope

Here are presented all the multi events detectors that could be used in multi propagation.

Javadoc

Those event detectors are available in the packages :

Links

See :

• [ORB_MPRO_Home Multi propagation chapter]
• [MIS_EVT_Home Events detection introduction chapter]

Useful Documents

None as of now.

Package Overview

None as of now.

Features Description

Multi events detectors

The following events detectors could be used in mono and multi spacecraft propagation :

• ThreeBodiesAngleDetector
• ExtremaThreeBodiesAngleDetector
• SatToSatMutualVisibilityDetector

These three detectors extends AbstractDetector and implements MultiEventDetector.

Using multi numerical propagator, all states concerned by the detection are recovered from the global state vector.
Using one of the mono propagator (analytical or numerical), the main state is recovered from the propagation. The others states concerned by the detection are recovered from a PVCoordinatesProvider.

The meaning of the g switching function for the concerned event detectors, and their particularities are presented in dedicated chapter :

• [MIS_ORB_Home Orbit determination events chapter]for ThreeBodiesAngleDetector and ExtremaThreeBodiesAngleDetector
• [MIS_STASAT_Home Ground stations and satellites events] for SatToSatMutualVisibilityDetector

Getting Started

In multi numerical propagation case, the states concerned by the detection are identified with their ID. Specific constructors should be used in multi numerical propagation case.
These constructors take as parameter the ID of states concerned by the detection.

Here after is presented the instanciation of a SatToSatMutualVisibilityDetectorin multi propagation case :

// Initialize multi numerical propagator
final FirstOrderIntegrator integratorMultiSat = new DormandPrince853Integrator(.1, 60, 1e-9, 1e-9);
MultiNumericalPropagator mainPropagator = new MultiNumericalPropagator(integratorMultiSat);
mainPropagator.addInitialState(mainState, STATE1);
mainPropagator.addInitialState(secondaryState, STATE2);
mainPropagator.setAttitudeProvider(attitudeProv, STATE1);
mainPropagator.setAttitudeProvider(attitudeProv, STATE2);
 
// Note that the NumericalPropagator and the MultiNumericalPropagator do not use anymore the Newtonian gravity model by default. It should now be added manually to the list of the force models before starting the propagation.
mainPropagator.addForceModel(new DirectBodyAttraction(new NewtonianGravityModel(mainState.getMu(), STATE1));
mainPropagator.addForceModel(new DirectBodyAttraction(new NewtonianGravityModel(secondaryState.getMu(), STATE2));
 
// Create SatToSatMultualVisibilityDetector
final MultiEventDetector detector = new SatToSatMutualVisibilityDetector(STATE1, STATE2, mainSpacecraftSensorModel1, secondarySpacecraftSensorModel2, false, 0.01, 10.e-10);
 
// Add detector
mainPropagator.addEventDetector(detector1);
 
// propagate
Map<String, SpacecraftState> endStates = mainPropagator.propagate(date.shiftedBy(duration));

If a wrong constructor is used, i.e a constructor for mono propagation, an exception will be raised during propagation.

Contents

Interfaces

Classes