Space Station attitude control and momentum management - A nonlinearlook
- Additional Document Info
- View All
© 1990, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. Nonlinear design procedures are presented for obtaining attitude and angular momentum control laws for the space station. These are based on Liapunov’s second method for stability analysis. Various forms of attitude control laws are derived using the fully coupled dynamic equations of motion which include gravity gradient torques. Next, the coupled attitude control and momentum management problem is addressed for a station configuration that is gravity gradient stable. Two methods are developed to control gravity unstable configurations. The first method, called the “Successive Stabilization Method, “ stabilizes the attitude first and then combinations of attitude and momentum variables. The second method is based on system decomposition into two connected subsystems, the attitude controller and the momentum manager. The attitude controller is designed using angular momentum as the control variable. The momentum manager is designed to produce the desired momentum required by the attitude controller. Simulation results are presented for the Phase-1 configuration in the presence of constant disturbances. It is shown that the space station can be stabilized about a Torque-Equilibrium-Attitude (TEA) and the momentum of the Control Moment Gyroscopes (CMGs) is bounded in the presence of constant disturbances.
author list (cited authors)