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			== Introduction ==
			[[File:copernicus.jpg\|center]]

			<center><blockquote>I shall now recall to mind that the motion of the<br>
			heavenly bodies is circular, since the motion<br>
			appropriate to a sphere is rotation in a circle.<br>
			''Mikołaj Kopernik (1473 – 1543)''</blockquote></center>

			This section is a short presentation of the orbital tools implemented in the PATRIUS Library. This part of the PATRIUS library is based on the OREKIT library that offers some of these features. The orbital tools of the PATRIUS library cover the software requirements given in '''[A1]''' §13,17,18,20.

			== Applicable and Reference Documents ==
			=== Applicable Documents ===

			'''[A1]''' ''CDCF - Fonctions de Base du Patrimoine de Dynamique du Vol'', V1.2, SIRIUS-CF-DV-0049-CN, 2011.<br>
			'''[A2]''' ''Dossier de réutilisation Orekit et Commons Math'', V1.0, SIRIUS-DLR-DV-0080-CN, 2010.

			=== Reference Documents ===

			'''[R1]''' ''Apache License'', Version 2.0, January 2004, [http://www.apache.org/licenses/LICENSE-2.0.txt].

			== Glossary ==
			{\| class="wikitable"
			\|-
			\|'''EGM96'''
			\|Earth Gravitational Model 1996
			\|-
			\|'''EIGEN'''
			\|European Improved Gravity model of the Earth by New techniques
			\|-
			\|'''GRACE'''
			\|Gravity Recovery And Climate Experiment
			\|-
			\|'''GRGS'''
			\|Groupe de Recherche de Géodésie Spatiale
			\|-
			\|'''ICGEM'''
			\|International Centre for Global Earth Models
			\|}

			== Overview ==
			The orbital tools of the PATRIUS library are mainly based on the propagation, forces and orbits packages of the OREKIT library. The geometry package of Commons-Math library is also used to deal with the geometrical characteristics of the spacecraft. Some evolutions have been developed to meet the Scope Statement '''[A1]''', for instance, some basic geometrical computations have been implemented (intersections, distances...) (see [MAT_GEO_Home Geometry]).

			The following themes are discussed in this section:

			; Physical models
			: This chapter describes the force models available in the OREKIT library including but not limited to : central body attraction, third body attraction, atmospheric pressure, solar radiation pressure, new atmospheric models, terrestrial and ocean tides, other radiative pressure and interplanetary models. It also includes a description of the model describing the displacements of reference points due to the effect of the solid Earth tides.

			; Propagation
			: This chapter deals with the different propagators that are available in OREKIT to propagate the initial state of a spacecraft. Analytical propagators are implemented (Keplerian, Eckstein-Hechler, 2D, etc.) as well as numerical ones (that are better suited to perform more accurate propagations- it is the most important part of the Orekit library) and STELA semi-analytical propagator.

			; Multi Propagation
			: This chapter deals with the multi propagator that is available in PATRIUS to propagate several initial states. Numerical propagator is implemented.

			; Ephemeris
			: Integrated ephemeris, Ephemeris and Lagrange ephemeris.

			; Measures and data filtering
			: This chapter describes the basic concepts of localisation measures and orbit restitution, measure modelling and data filtering.

			== Package List ==
			The following themes are discussed in this section :

			{{displayChildrenTitlesAsLinks/}}

	[[Catégorie:User Manual 3.3]]		[[Catégorie:User Manual 3.3]]

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