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An analytical control law of length rate for tethered satellite system

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Abstract

Based on the nonlinear dynamic equations of a tethered satellite system with three-dimensional attitude motion, an analytical tether length rate control law for deployment is derived from the equilibrium positions of the system and the scheme of the value range of the expected in-plane pitch angle. The proposed control law can guarantee that the tensional force acting on the end of the tether remains positive. The oscillation of the out-of-plane roll motion in conjunction with the in-plane pitch motion is effectively suppressed during deployment control. The analytical control law is still applicable, even if the system runs on a Keplerian elliptical orbit with a large eccentricity. The local stability of the non-autonomous system during deployment control is analyzed using the Floquet theory, and the global behavior is numerically verified using simple cell mapping. The numerical simulations in the paper demonstrate the proposed analytical control law.

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Acknowledgements

This study was funded by the Natural Science Foundation of China (11290153, 11672125), and in part by the Fundamental Research Funds for the Central Universities (NS2016009) and the Priority Academic Program Development of Jiangsu Higher Education Institutions.

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Authors and Affiliations

  1. State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing, 210016, People’s Republic of China

    B. S. Yu, D. P. Jin & H. Wen

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  1. B. S. Yu
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  2. D. P. Jin
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  3. H. Wen
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Correspondence to B. S. Yu.

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B. S. Yu, D. P. Jin and H. Wen have no conflicts of interest.

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Yu, B.S., Jin, D.P. & Wen, H. An analytical control law of length rate for tethered satellite system. Meccanica 52, 2035–2046 (2017). https://doi.org/10.1007/s11012-016-0567-z

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  • DOI: https://doi.org/10.1007/s11012-016-0567-z

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