Spin stabilization of the ORION satellite using a thruster attitude control system with optimal control considerations
By:  Janet L. Cunningham
Publisher: Naval Postgraduate School; Available from the National Technical Information Service
Published: 1989
Place of publication: Monterey, Calif; Springfield, Va
Language: eng
Number of pages: 40
Description: The controlled system is the ORION satellite spinning about its single axis of symmetry. Hydrazine thrusters are used as the control and are modeled by ideal, constant magnitude step functions. The system is normalized and driven from non-zero initial angular velocities of the two axes other than the spin axis to the final condition zero. The control profiles required to do this are determined based on a desired controller duty cycle. Adaption of the duty cycle changes the ratio of the time the thrusters are on (fuel use) and total time to completion of the evolution. A comparison between a single axis and a dual axis controller is presented. Simulation programs for the normalized system using a single axis controller simulation program, with each controller having a duty cycle of no more than 50%, are developed. Operation of the system is optimized using a system cost function. An equation relating the controller duty cycle of the dual system to the fuel/time trade-off parameter of the system cost function is required. A nonlinear feedback control algorithm (function of attitude angle rates) is developed from iterations of the simulation, and a priori knowledge of the form of the control from optimal control theory. This numerical solution will allow system designers to incorporate a closed form state feedback control for minimum fuel/time strategies using the ORION satellite's onboard software.
Notes: Thesis advisor(s): Titus, Harold A.

"March 1989."

Thesis (M.S. in Electrical Engineering) Naval Postgraduate School, March 1989.

Includes bibliographical references.

Approved for public release; distribution unlimited.