2入力による衛星の3 軸姿勢制御

摘要

This paper deals with three dimensional attitude control of a rigid body satellite by two control torques. It is assumed that two control torques act about the satellite's principal axes. This paper describes the kinematics of attitude motions of the satellite by using WZ parameters. First, we consider the satellite's angular velocity controlled by virtual inputs and derive a feedback control law which is not depend on moment of inertia. Then, the virtual inputs are realized via the dynamic equation of motion of the satellite. The validity of the proposed control law is verified by numerical simulations.