Optimal continuous thrust inplane orbital evasive maneuvers
Abstract
This paper addresses the intercept problem of a target satellite in a geosynchronous orbit which is considered to be threatened by a coasting spacecraft on a collision course. With the maneuvers of the target satellite restricted to the plane of the nominal orbit, two maneuver strategies are considered: (1) maximizing the change in the orbit radius of the target satellite in a specified amount of time and (2) the same strategy but with a constraint that at the end of the evasion maneuver the satellite's radius vector be orthogonal to its velocity vector. These maneuvers are analyzed in the framework of optimal control theory to derive twopoint boundaryvalue problems. Results show that shaping the maneuver with the orthogonality constraint has an adverse effect. The results of the calculations also show that the time required for the target satellite to return to the nominal orbit can significantly exceed the time of the evasive maneuver.
 Publication:

26th AIAA Aerospace Sciences Meeting
 Pub Date:
 January 1988
 Bibcode:
 1988aiaa.meetZ....W
 Keywords:

 Collision Avoidance;
 Evasive Satellites;
 Rocket Thrust;
 Spacecraft Maneuvers;
 Synchronous Satellites;
 Boundary Value Problems;
 Optimal Control;
 Orbital Mechanics;
 Satellite Orbits;
 Astrodynamics