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Research Papers

A Composite Robust Fault-Tolerant Control Scheme for Limited-Thrust Spacecraft Rendezvous in Near-Circular Orbits

[+] Author and Article Information
Neng Wan

Department of Mathematics and Statistics,
University of Minnesota Duluth,
Duluth, MN 55812
e-mail: wanxx179@d.umn.edu

Weiran Yao

School of Astronautics,
Harbin Institute of Technology,
Harbin 150001, China
e-mail: yaoweiran@hit.edu.cn

Mingming Shi

Faculty of Mathematics and Natural Sciences,
University of Groningen,
Groningen 9747 AG, The Netherlands
e-mail: m.shi@rug.nl

Contributed by the Dynamic Systems Division of ASME for publication in the JOURNAL OF DYNAMIC SYSTEMS, MEASUREMENT, AND CONTROL. Manuscript received June 16, 2016; final manuscript received May 31, 2017; published online August 28, 2017. Assoc. Editor: Ming Xin.

J. Dyn. Sys., Meas., Control 139(12), 121009 (Aug 28, 2017) (12 pages) Paper No: DS-16-1319; doi: 10.1115/1.4037211 History: Received June 16, 2016; Revised May 31, 2017

External perturbations and actuator faults are two practical and significant issues that deserve designers' considerations when synthesizing the controllers for spacecraft rendezvous. A composite robust fault-tolerant control (FTC) scheme that does not require the fault information is proposed in this paper for limited-thrust rendezvous in near-circular orbits. Within the control scheme, a reliable integral sliding mode (ISM) auxiliary controller and a modified guaranteed cost FTC are, respectively, developed to attenuate the external disturbances and to stabilize the nominal rendezvous system with actuator faults. Comparisons with previous works as well as a more practical and challenging simulation example are presented to verify the advantages of this composite control scheme.

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References

Figures

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Fig. 1

Relative Cartesian coordinate system for spacecraft rendezvous

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Fig. 2

Hierarchy of the composite control scheme

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Fig. 3

Actuator efficiencies ni(t) along each axis

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Fig. 4

Spatial trajectories of different rendezvouses in the first 30,000 s: (a) fault-free rendezvous with composite controllers, (b) fault-free rendezvous with single fault-tolerant controller, and (c) faulty rendezvous with composite controllers

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Fig. 5

Relative distances between spacecrafts

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Fig. 6

Switching function S(t)

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Fig. 7

ACO and CCS of fault-tolerant controller along each axis: (a) ACO and CCS of fault-tolerant controller along x-axis, (b) ACO and CCS of fault-tolerant controller along y-axis, and (c) ACO and CCS of fault-tolerant controller along z-axis

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Fig. 8

ACO of reliable ISM auxiliary controller along each axis

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Fig. 9

Total velocity changes Δv of faulty and fault-free rendezvouses

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Fig. 10

Performance indices J of faulty and fault-free rendezvouses

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