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Research Papers

Finite-Time Disturbance Observer Design and Attitude Tracking Control of a Rigid Spacecraft

[+] Author and Article Information
Qixun Lan

School of Automation,
Southeast University,
Nanjing, Jiangsu 210096, China;
School of Mathematics and Physics,
Henan University of Urban Construction,
Pingdingshan, Henan 467036, China
e-mail: q.lan@hncj.edu.cn

Chunjiang Qian

Department of Electrical and
Computer Engineering,
The University of Texas at San Antonio,
San Antonio, TX 78249
e-mail: chunjiang.qian@utsa.edu

Shihua Li

School of Automation,
Southeast University,
Nanjing, Jiangsu 210096, China
e-mail: lsh@seu.edu.cn

1Corresponding author.

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.

J. Dyn. Sys., Meas., Control 139(6), 061010 (Apr 13, 2017) (8 pages) Paper No: DS-15-1617; doi: 10.1115/1.4035457 History: Received December 06, 2015; Revised December 07, 2016

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.

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References

Figures

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Fig. 1

Response curves of disturbance d,d˙ and d¨ (the solid line) and their estimations d̂,d̂˙ and d̂¨ (the dotted line)

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Fig. 2

Response curves of attitude errors under FTC (24) (the dash line) and CFTC (37) (the solid line)

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Fig. 3

Response curves of angular velocity errors under FTC (24) (the dash line) and CFTC (37) (the solid line)

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Fig. 4

The real values (the solid line) and estimated values (the dash line) of disturbances

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Fig. 5

Response curves of control signals of FTC (24) (the dash line) and CFTC (37) (the solid line)

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