Finite-Time Coordinated Attitude Control for Spacecraft Formation Flying under Input Saturation

QL Hu (Beihang University, China), J Zhang (Harbin Institute of Technology, China) & MI Friswell (Swansea University)

Journal of Dynamic Systems, Measurement and Control, Vol. 137, No. 6, June 2015, paper 061012

Abstract

In this paper, finite-time attitude coordinated control for spacecraft formation flying subjected to input saturation is investigated. More specifically, a bounded finite-time state feedback control law is first developed with the assumption that both attitude and angular velocity signals can be measured and transmitted between formation members. Then, a bounded finite-time output feedback controller is designed with the addition of a filter, which removes the requirement of the angular velocity measurements. In both cases, actuator saturation is explicitly taken into account, and the homogeneous system method is employed to demonstrate the finite-time stability of the closed-loop system. Numerical simulation results are presented to illustrate the efficiency of the proposed control schemes.

Paper Availability

This material has been published in the Journal of Dynamic Systems, Measurement and Control, Vol. 137, No. 6, June 2015, paper 061012 the only definitive repository of the content that has been certified and accepted after peer review. Copyright and all rights therein are retained by ASME.


Link to paper using doi: 10.1115/1.4029467

Link to paper on the ASME website

ASME Digital Collection