抄録
This paper is a continuation of a previous study whereby the planar attitude control of a deputy satellite encircling a central satellite body is discussed. In this extension, however, the inclusion of sensor and actuator noise is made. In reality the sensitivity of both the positional measurement and charge induction system will limit the performance of the satellite formation. Attitude and positional control are achieved by exploiting the spacecraft charges, a Lyapunov based control law, a switching control logic and a temporary guidance ellipse method. The desired attitude is defined as the deputy satellite body fixed y-axis pointing towards the composite satellite centre of mass. In translational terms the target path (nominal reference motion) is a Clohessy Wiltshire bounded solution relative to the central satellite body. The influence of actuator noise into the feedback system is hereby investigated.
