In this paper, finite-time attitude coordinated control for spacecraft formation flying (SFF) 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.
Finite-Time Coordinated Attitude Control for Spacecraft Formation Flying Under Input Saturation
and Electrical Engineering,
Contributed by the Dynamic Systems Division of ASME for publication in the JOURNAL OF DYNAMIC SYSTEMS, MEASUREMENT, AND CONTROL. Manuscript received March 11, 2014; final manuscript received December 17, 2014; published online February 4, 2015. Assoc. Editor: Umesh Vaidya.
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Hu, Q., Zhang, J., and Friswell, M. I. (June 1, 2015). "Finite-Time Coordinated Attitude Control for Spacecraft Formation Flying Under Input Saturation." ASME. J. Dyn. Sys., Meas., Control. June 2015; 137(6): 061012. https://doi.org/10.1115/1.4029467
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