The Study Of The Control Moment Gyroscope With Application To The Satellite Attitude Control System

With the development of aerospace technology in our country. The requirement of the satellite's functions is more and more complex, at the same time, the pointing precision and attitude stabilization of the satellite is demanded higher and higher. Thus the development of large satellites with high precision and stabilization has been one of the key trends currently, especially the satellite attitude control system. And from the comprehensive survey of satellite development in foreign countries, the Control Moment Gyroscope (CMG) is a commonly used controller in the control system of large satellites. The CMG is different from traditional flywheel systems for singularity problems, and therefore the research on CMG is concentrated on the steering law study for avoiding singularity. This paper, aimed at several crucial problems in the application of CMG to large satellites, is studied to afford basis for the application of moment gyroscope in aerospace engineering.1). Aimed at a particular variety of satellites with rigid bodies, the control model of the satellites has been given based on Euler method and quaternion and the control law for zero momentum satellites based on the control model has been studied in this paper. As a result of the study, the PID control law based on successful engineering applications has been introduced and the calculating model for the space disturbance, pneumatic moment is educed in detail.2). The configuration of single gimbal control moment gyroscope has been studied and the performance of each configurations is compared by simulation. According to the simulation results, it is considered synthetically from the configuration benefit, the invalidation benefit, the controllable benefit and the singularity loss rate that CMG with pentagonal pyramid configuration is the most optimized in application to satellite control engineering.3). Strong emphasis has been laid on the study of the steering law based on zero movement additive and the model of the steering law is educed in detail. And with consideration to the dynamic feature of gimbal servo system, the dynamics model and control law of gimbal driving system have been derived.4). The attitude maneuver simulation along the rolling axis of large satellites has beenmade upon the above work. In the simulation, the control of two satellites with different mass (6tons, 9tons) under pentagonal pyramid configuration and tetragonal pyramid configuration has been studied individually by means of zero movement additive. As a result of the simulation, the CMG system under pentagonal pyramid configuration has been proved sufficient to the task requirement with attitude stabilization of 1 X 10"4o/s and pointing precision of 0.1° while the CMG system under tetragonal pyramid configuration, equal to the task for 6tons satellite, has been proved insufficient for the requirement of 9tons satellite for singularity in the second maneuver .5). The simulation technique for CMG system is studied and corresponding physical simulation scheme is introduced, which is very significant in validating the theory based on and the engineering application of CMG.