93-144
Stable Orbit Rendezvous For A Small Radius Translunar Halo Orbit
Brian L. Jones*, Robert H. Bishop**
Abstract
A two spacecraft terminal phase rendezvous targeting law, which is valid for the three-body problem, is given, The relevant equations of motion are derived and the targeting law developed assuming the traditional target/chaser vehicle relationship. The targeting law is demonstrated using a small radius translunar halo orbit. Nonlinear simulation results verify that acceptable performance is obtained, Using these results, the three-body terminal phase rendezvous problem is further characterized and contrasted with the two-body problem.
*Graduate Student, Department of Aerospace Engineering and Engineering Mechanics, The University of Texas, Austin, Texas 78712-1085. Major U.S. Air Force; Senior Member AIAA
**Assistant Professor,Department of Aerospace Engineering and Engineering Mechanics, The University of Texas, Austin, Texas 78712-1085. Major U.S. Air Force; Senior Member AIAA