A New Steering Law of a Single-Gimbal CMG System of Pyramid Configuration

Abstract

A steering law is proposed for a pyramid type configuration single gimbal Control Moment Gyro system for attitude control of spacecrafts. Pyramid type CMG systems have the serious problem of complicated singular states. For the steering law, a function (gain) is introduced to the system. Gistribution of the gain, escapability from singular states, and symmetric characteristics of the system are discussed. The proposed steering law maximizes the gain of the system and avoids singular states by referring to the table which is obtained by off-line calculation and reduced to reasonably small size by using symmetric characteristics of the system.