THE APPLICATION OF SELF-ORGANIZING CONTROL TECHNIQUES TO A CONTROL MOMENT GYROSCOPE SATELLITE ATTITUDE CONTROL SYSTEM.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
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The basic design for a single-axis satellite attitude control system using control moment gyroscopes and self-organizing controllers is presented. Response curves from an analog simulation show that the response time can be improved by over 600 as compared to a constant gain system. The system is essentially invariant to disturbance torques up to the 375 foot-pound value tested. In addition, the system was found to operate satisfactorily in a noise environemnt. The basic design was expanded to two axes of control using two gyros and two controllers. This design was simulated on the analog computer with comparable results. Author
- Manned Spacecraft