This paper considers the problem of finite-time disturbance observer (FTDO) design and the problem of FTDO based finite-time control for systems subject to nonvanishing disturbances. First of all, based on the homogeneous systems theory and saturation technique, a continuous FTDO design approach is proposed. Then, by using the proposed FTDO design approach, a FTDO is constructed to estimate the disturbances that exist in a rigid spacecraft system. Furthermore, based on a baseline finite-time control law and a feedforward compensation term produced by the FTDO, a composite controller is constructed for the rigid spacecraft system. It is shown that the proposed composite controller will render the rigid spacecraft track the desired attitude trajectory in a finite-time. Simulation results are included to demonstrate the effectiveness of the proposed control approach.
Finite-Time Disturbance Observer Design and Attitude Tracking Control of a Rigid Spacecraft
Nanjing, Jiangsu 210096, China;
Henan University of Urban Construction,
Pingdingshan, Henan 467036, China
Contributed by the Dynamic Systems Division of ASME for publication in the JOURNAL OF DYNAMIC SYSTEMS, MEASUREMENT, AND CONTROL. Manuscript received December 6, 2015; final manuscript received December 7, 2016; published online April 13, 2017. Assoc. Editor: Mazen Farhood.
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Lan, Q., Qian, C., and Li, S. (April 13, 2017). "Finite-Time Disturbance Observer Design and Attitude Tracking Control of a Rigid Spacecraft." ASME. J. Dyn. Sys., Meas., Control. June 2017; 139(6): 061010. https://doi.org/10.1115/1.4035457
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