Decentralized Finite-time Attitude Synchronization Control of Satellite Formation Flying

JK Zhou, QL Hu (Harbin Institute of Technology, China) & MI Friswell (Swansea University)

Journal of Guidance, Control, and Dynamics, Vol. 36, No. 1, January 2013, pp. 185-195

Abstract

This paper investigates a quaternion-based finite-time attitude synchronization and stabilization problem for satellite formation flying. Sufficient conditions are presented for finite-time boundness and stability of this distributed consensus problem. More specifically, a nonlinear control law based on a finite-time control technique is developed such that the attitude of the rigid spacecraft will coordinate and converge to the attitude of the leader while the angular velocity will converge to zero in finite time. The associated stability proof is constructive and accomplished by adding a power integrator term in the Lyapunov function. Furthermore, to reduce the heavy communication burden, a modified control law is then designed by introducing a finite-time sliding-mode estimator such that only satellite has to communicate with the leader. Simulation results are presented to demonstrate the effectiveness of the designed scheme, especially the potential advantages derived through the inclusion of the continuous finite-time control method, such as the fast convergent rate and the alleviation of chattering.

Paper Availability

This material has been published in the Journal of Guidance, Control, and Dynamics, Vol. 36, No. 1, January 2013, pp. 185-195. Unfortunately the copyright agreement with AIAA does not allow for the PDF file of the paper to be available on this website. However the paper is available from AIAA - see the link below.


Link to paper using doi: 10.2514/1.56740

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