OPTIMAL MOMENTUM MANAGEMENT CONTROLLER FOR THE SPACE STATION

This paper presents a new sequential design procedure for determining an optimal control moment gryo momentum management and attitude control system for the Space Station Freedom. First, the space station equations of motion are linearized and uncoupled, and the associated state space equations are defined. Next, a new sequential procedure is used for the development of a linear quadratic regulator with eigenvalue placement in a specified region of the complex plane. The regional pole assignment method is used since it is best suited for tradeoffs between eigenvalue locations and robustness with respect to parameter variations, sensor failures, implementation accuracies, and gain reduction. The matrix sign function is used for solving the Riccati equations, which appear in the design procedure. Simulation results are given which show that the resultant design provides desired system performance. © 1990 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.