Relative motion between two spacecraft around a central body is an important problem of space guidance and navigation. The equations of relative motion in orbit can be approximated by a set of linear differential equations called the Hill‐Clohessy‐Wiltshire equations. In this chapter, these approximate, linearized equations are derived and solved for special problems, such as interception and rendezvous of spacecraft around a spherical, central body. An unforced response is the relative trajectory between any two instances where impulsive inputs are applied on spacecraft. A zero‐thrust (or null‐thrust) trajectory can be used to devise an impulsive control strategy for achieving a desired objective for a given set of initial and final conditions. The exact relative motion of spacecraft relative to the target around a spherical body is described by separately solving the equations of Keplerian motion for the two spacecraft, and then finding the difference in their position and inertial velocity vectors.
Relative Motion in Orbit
Foundations of Space Dynamics ; 145-159
2021-02-01
15 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
Satellite Relative Motion in Elliptical Orbit Using Relative Orbit Elements (AAS 11-497)
British Library Conference Proceedings | 2012
|British Library Conference Proceedings | 2012
|Geometrical Relative Orbit Modeling of Satellite Relative Motion (AAS 08-266)
British Library Conference Proceedings | 2008
|