Attitude Control Technology Study Based on Zero Momentum Reaction Wheels of a Certain Satellite

The research object in this paper is the observation satellite to the ground with big flexible accessory, such as the solar panel and antenna. The attitude control is based on zero moment reaction wheels. Multiple loops compound control project is presented in the research. This kind of project contains three obvious differences from traditional satellite attitude determination and control method: adopt high accuracy velocity feedback flywheel, the differential calculus signal from the flywheel rotate speed output of the fast stable loop, use error correct big loop with narrow bandwidth to suppress the gyroscope drift and various fixing error. Applying the design result to object model and considering all error resource, the simulation is performed. The system design results reach the given target and have much margin.