Quaternion Based Attitude Control and Suboptimal Rendezvous Guidance on Satellite Proximity Operation

Abstract

This paper introduces a suboptimal rendezvous guidance method and a quaternion based attitude control law for satellite proximity operation. A dynamic model of relative motion between two satellite is expressed as a linear state space model, called the clohessy-wiltshire equation, while the satellite’s attitude is governed by the rigid body kinematic. A solution of a linear quadratic control problem is obtainable with a system of algebraic equations. This paper proposes a suboptimal rendezvous guidance law based on the LQC and to comply the suboptimal command, a quaternion based attitude controller has been designed. Several cases of simulation is conducted to prove that proposed method can meet the terminal condition on a specific time, and attitude control logic is well functioning to comply the guidance command.