Control moment gyros (CMGs) are effective torque generator for attitude control of satellites. The model used in this study is a rigid satellite with four CMGs arranged like a pyramid. Almost all steering laws of CMGs are developed based on the pseudoinverse steering law. This study focuses on the steering law that is not based on the pseudoinverse steering law by using receding horizon control. The Minimum Energy (ME) steering law utilizes the characteristic of gimbal rate in the proximity of singularity to avoid singularity. Numerical simulations are conducted to illustrate the advantages of the ME steering law with a comparison with the pseudoinverse steering law.
展开▼
