Upper-stage launch vehicle servo controller design considering optimal thruster configuration

Abstract

An attitude control system using reaction thrusters for the upper stage of a launch vehicle is considered. The thruster configuration (position and direction) determines control system response, fuel consumption, effective torque and system fault tolerance. We propose a procedure for finding the optimal thruster configuration with desired control effectiveness over the range of selected torque commands. An optimization technique called Particle Swarm Optimization is used for the numerical experiments. The validity of the solution is checked through computer simulations. © 2003 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.