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Research Papers

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

[+] Author and Article Information
Qinglei Hu

School of Automation Science
and Electrical Engineering,
Beihang University,
Beijing 100191, China

Jian Zhang

Department of Control Science
and Technology,
Harbin Institute of Technology,
Harbin 150001, China

Michael I. Friswell

College of Engineering,
Swansea University,
Singleton Park,
Swansea SA2 8PP, UK

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.

J. Dyn. Sys., Meas., Control 137(6), 061012 (Jun 01, 2015) (14 pages) Paper No: DS-14-1112; doi: 10.1115/1.4029467 History: Received March 11, 2014; Revised December 17, 2014; Online February 04, 2015

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.

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References

Figures

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Fig. 1

Communication topology

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Fig. 3

The angular velocity under controller (8) in the absence of disturbance (α1=0.5)

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Fig. 4

The control torque under controller (8) in the absence of disturbance (α1=0.5)

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Fig. 5

The absolute attitude error under controller (8) in the absence of disturbance (α1=1)

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Fig. 6

The angular velocity under controller (8) in the absence of disturbance (α1=1)

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Fig. 7

The control torque under controller (8) in the absence of disturbance (α1=1)

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Fig. 15

The absolute attitude error under controller (23)/(24) in the presence of disturbance (α1=0.6)

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Fig. 16

The control torque under controller (23)/(24) in the presence of disturbance (α1=0.6)

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Fig. 2

The absolute attitude error under controller (8) in the absence of disturbance (α1=0.5)

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Fig. 8

The absolute attitude error under controller (23)/(24) in the absence of disturbance (α1=0.6)

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Fig. 9

The control torque under controller (23)/(24) in the absence of disturbance (α1=0.6)

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Fig. 10

The absolute attitude error under controller (23)/(24) in the absence of disturbance (α1=1)

Grahic Jump Location
Fig. 11

The control torque under controller (23)/(24) in the absence of disturbance (α1=1)

Grahic Jump Location
Fig. 12

The absolute attitude error under controller (8) in the presence of disturbance (α1=0.5)

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Fig. 13

The angular velocity under controller (8) in the presence of disturbance (α1=0.5)

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Fig. 14

The control torque under controller (8) in the presence of disturbance (α1=0.5)

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