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Modeling and Attitude Control of a Spinning Spacecraft with Internal Moving Mass

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Abstract:

An attitude control system of a spinning spacecraft with internal moving mass is presented in this paper. This system consists of a rigid body and two internal radial moving masses. The mathematical model, including attitude kinematics and nonlinear dynamics equations, is established based on Newtonian mechanics. The control law is designed based on the linear-quadratic-regulator (LQR) theory. The performance of the controller is demonstrated in numerical simulation, and the response shows that the attitude control system is stable and effective.

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Periodical:

Advanced Materials Research (Volumes 760-762)

Pages:

1216-1220

DOI:

https://doi.org/10.4028/www.scientific.net/AMR.760-762.1216

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Online since:

September 2013

Authors:

Peng Fei Guo, Liang Yu Zhao

Keywords:

Attitude Control, LQR, Moving Mass, Spinning Spacecraft

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© 2013 Trans Tech Publications Ltd. All Rights Reserved

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References

[1] Regan F J, Kavetsky R A. Add-on controller for ballistic reentry vehicles [J]. IEEE Transactions on Automatic Control, 1984, 12(6): 869-880.

Google Scholar

[2] Robinett R D, Rainwater B A, Kerr S A. Moving mass trim controd for aerospace vehicles [J]. Journal of Guidance, Control, and Dynamics, 1996, 19(05): 1064-1070.

DOI: 10.2514/3.21746

Google Scholar

[3] Petsopoulos T, Regan F J, Barlow J. Moving-mass roll control system for fixed-trim re-entry vehicle [J]. Journal of Spacecraft and Rockets, 1996, 33(1): 54-60.

DOI: 10.2514/3.55707

Google Scholar

[4] LIN Yuguang, YAO Xiaoxian, ZHANG Yan. Sliding mode control of Moving-Mass-Center system for terminal guidance of ballistic missile [J]. Control Technology of Tactical Missile, 2006(1): 11-14.

Google Scholar

[5] ZHANG Xiaoyu, WANG Zicai. Dynamic inversion control for mass moment interception missile based on fuzzy neural network [J]. Journal of Astronautics, 2007, 28(3): 551-556.

Google Scholar

[6] ZHANG Xiaoyu, HE Youzhi, WANG ZI Cai. Robust control of mass moment interception missile based on h_∞ performance characteristics [J]. ACTA Aeronautica ET Astronautica Sinica, 2007, 28(3): 634-640.

Google Scholar

[7] WANG S, YANG M, WANG Z. Moving-mass control system for spinning vehicle guidance based on GA [C]. Systems and Control in Aerospace and Astronautics, IEEE, 2006: 497-501.

DOI: 10.1109/isscaa.2006.1627645

Google Scholar

[8] ZHANG Xiaoyu, HE Youzhi, WANG Zicai. Fuzzy sliding mode attitude control approach to mass moment interception missile [J]. Journal of Astronautics, 2006, 27(6): 1419-1423.

Google Scholar

[9] SHEN Dongxiang, ZHANG Xiaoyu. Research on nonlinear predictive control of mass moment interception missile based on ant colony genetic algorithm optimization [J]. Machinery & Electronics, 2007(9): 3-7.

Google Scholar