Overview
FrançaisABSTRACT
The motion of bodies in space is primarily governed by gravity laws. The basic model is the two-body problem which considers two particles submitted to the universal attraction law. Under these so-called keplerian assumptions, the trajectories are conics satisfying energy and angular momentum conservation properties. These conics are located in space through the orbital parameters which provide a simple description of the motion. The article recalls the main theoretical results and the coordinate change formulae useful for practical applications.
Read this article from a comprehensive knowledge base, updated and supplemented with articles reviewed by scientific committees.
Read the articleAUTHOR
-
Max CERF: Mission Analysis Engineer - ArianeGroup, Les Mureaux, France
INTRODUCTION
The two-body problem is the fundamental model of orbital mechanics. It describes the motion of two point bodies interacting purely gravitationally, to the exclusion of all other forces. These simplifying assumptions lead to an analytical expression of trajectories in the form of conics, verifying the properties of conservation of energy and angular momentum. The nature of the conic (circle, ellipse, parabola or hyperbola) depends solely on the initial conditions of position and velocity. The Keplerian orbit of a satellite around the Earth is represented geometrically by its orbital parameters, which are analytically related to position and velocity as a function of time. The right choice of orbital parameters enables the satellite to be synchronized with the movements of the Earth (geosynchronism) or the Sun (heliosynchronism). These properties are particularly beneficial for telecommunication or observation space applications.
The two-body problem naturally obeys the equations of mechanics, but analytical solutions are only obtained under certain assumptions. In particular, the two bodies are assumed to be spherical and homogeneous, and there is no relativistic effect (remember that the displacement of Mercury's perihelion is one of the first proofs of the validity of the theory of general relativity).
Although simplified, the Keplerian model gives a very good approximation of the real motion of an artificial satellite. To study motion more precisely, we need to take into account disturbing forces, mainly due to the Earth's gravitational potential, atmospheric friction, the attraction of the Moon and Sun, and solar radiation pressure. The effect of these forces on a Keplerian orbit can be studied using analytical perturbation methods or numerical simulations. The subject of this article is Keplerian motion. It recalls the notions and formulas useful to engineers working on space applications.
Exclusive to subscribers. 97% yet to be discovered!
You do not have access to this resource.
Click here to request your free trial access!
Already subscribed? Log in!
The Ultimate Scientific and Technical Reference
KEYWORDS
gravitation | orbital parameters | orbit | conic
This article is included in
Aerospace systems
This offer includes:
Knowledge Base
Updated and enriched with articles validated by our scientific committees
Services
A set of exclusive tools to complement the resources
Practical Path
Operational and didactic, to guarantee the acquisition of transversal skills
Doc & Quiz
Interactive articles with quizzes, for constructive reading
Spatial trajectories
Bibliography
Websites
Jet Propulsion Laboratory (JPL) ephemeris ftp://ssd.jpl.nasa.gov/pub/eph/planets/
Exclusive to subscribers. 97% yet to be discovered!
You do not have access to this resource.
Click here to request your free trial access!
Already subscribed? Log in!
The Ultimate Scientific and Technical Reference