User Manual 4.14 Ephemeris : Différence entre versions

Version actuelle en date du 2 septembre 2024 à 09:01

Introduction

Scope

This section describes the propagation of spacecraftstates based on interpolation of position velocity ephemeris.

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The concerned classes are avalaible in the following packages :

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Package Overview

See the [ORB_PRO_PkgOverview Propagator ] page for more generic information about propagators.

Propagation based on interpolation of position velocity ephemeris has been design to be very simple to use:

• Ephemeris propagators extend AbstractPropagator class. As a result all propagators features (event detection, etc.) are available.

• Ephemeris propagators are based on a PVCoordinateProvider to retrieve the orbital parameters at required date.

• Implementation of PVCoordinateProvider based on ephemeris interpolation (Hermite, or Lagrange).

• Implementation of AdditionalStatesProvider based on an ephemeris of additional states.

Features Description

PVCoordinatesPropagator

The PV coordinate propagator extends AbstractPropagator and provides a simple way to propagate an initial spacecraft state coherent with the provided PVCoordinatesProvider and the eventual attitude and additional states provider.

The propagation of position velocity is based on the getPVCoordinates of the given PVCoordinatesProvider.
The propagation of attitude is based on the given AttitudeProvider.
The propagation of the additional states is based on the given AdditionalStatesProvider.

A classical simple use case is :

• PVCoordinatesProvider : One of the provider based on ephemeris interpolation (Lagrange or Hermite)

• AttitudeProvider : Null. The attitude of the propagated spacecraft state is null.

• AdditionalStatesProvider : Null. The additional states of the propagated spacecraft state is null.

A classical advanced use case is to add an attitude provider and the SimpleAdditionalStateProvider described in next paragraph.

Warning: Events detector with Action.RESET_STATE should not be used with this propagator fed with a "precomputed" PV coordinate provider (such as an ephemeris or an orbit object). In particular, impulse maneuvers cannot be used. Otherwise propagation will fail.
This is due to the fact that the provided PV coordinate provider is not valid any more after the Action.RESET_STATE action.

SimpleAdditionalStateProvider

The SimpleAdditionalStateProvider is an implementation of AdditionalStateProvider based on additional states ephemeris.

The computation of an additional state for a given date is the following:

• If the given date is found in the ephemeris, the associated additional state vector is returned

• Otherwise a linera interpolation is performed.

PVCoordinateProvider Ephemeris

Two classes provide PVCoordinates at a given date from an ephemeris interpolation :

• EphemerisPvLagrange : Computes the PVCoordinates using a Hermite interpolation (HermiteInterpolator) of the ephemeris without providing any derivatives on points to be interpolated (this allows to improve the computation performance with respect to a classical Lagrange approach - PolynomialFunctionLagrangeForm - by a factor 4).

• EphemerisPvHermite : Computes the PVCoordinates using a Hermite interpolation of the ephemeris

Both can be built from a list of spacecraftstates or from list of dates- positions - velocities expressed in a given frame.

Lagrange interpolation

Intermediate states are computed with a Lagrange interpolator (order 8 by default) which :

• expects that spacecraft states are chronologically sorted (duplicates are allowed). If not sorted, no exception will be thrown and result might be wrong.

• is based on an instance of PolynomialFunctionLagrangeForm, which is stored at each interpolation to be reused for same interpolation interval, and updated if the interpolation is not in the same interval [math]t \in [t_{i}, t_{i+1}[[/math], where [math]i \in \left\{0, ..., N \right\}[/math] and [math]N[/math] is the size of the handled ephemeris.

The interpolation order [math]n[/math] for LagrangeEphemeris should be an even number, and the interpolation date should correspond to an index that belongs in [math]n/2- 1 \leq i \leq N-1-n/2[/math].

Hermite interpolation

Intermediate states are computed with a Hermite interpolator which :

• expects the spacecraft states to be chronologically sorted (duplicates are allowed). If not sorted, no exception will be thrown and result might be wrong.

• is based on an instance of HermiteInterpolator, which is stored at each interpolation to be reused for same interpolation interval, and updated if the interpolation is not in the same interval [math]t \in [t_{i}, t_{i+1}[[/math], where [math]i \in \left\{0, ..., N \right\}[/math] and [math]N[/math] is the size of the handled ephemeris (in closed-open convention).

For HermiteEphemeris, the interpolation can use the acceleration array if it is available.

PVCoordinateProvider AlmanacPVCoordinates

The class AlmanacPVCoordinates extends the PVCoordinateProvider.
It provides PVCoordinates (position and velocity) of GNSS almanacs.
Almanacs can be provided using the AlmanacGNSSParameters class.
The classes CNAVGNSSParameters and LNAVGNSSParameters are simple containers for broadcast model CNAV and LNAV ephemeris description parameters of GNSS satellites (GPS and BeiDou for CNAV and GPS, BeiDou and Galileo for LNAV).

Getting Started

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