Multiple intercept trajectories
Abstract
Future missions in space will require rendezvous with or intercept of several targets in different orbits by a single vehicle. Such missions should be optimized for some combination of fuel and time parameters. This paper describes a first step in solving this problem: a computer program that attempts to optimize an intercept of two targets in separate orbits. Input to the program is a set of orbital elements for the interceptor and for the targets. Optimization is done with respect to fuel requirements only. The output of the unconstrained optimization can require negative time intervals. An attempt to avoid this unrealistic requirement is described. Tests were run in the vicinity of a known optimal solution. The results presented are a preliminary analysis aimed primarily at verifying the correctness of the code.
 Publication:

AIAA, Astrodynamics Specialist Conference
 Pub Date:
 August 1981
 Bibcode:
 1981aiaa.confX....K
 Keywords:

 Orbit Calculation;
 Rendezvous Trajectories;
 Satellite Interceptors;
 Space Rendezvous;
 Trajectory Optimization;
 Algorithms;
 Computer Programs;
 Computer Techniques;
 Orbital Elements;
 Space Missions;
 Target Acquisition;
 Astrodynamics