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Three-dimensional nonlinear coupling guidance for hypersonic vehicle in dive phase

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Abstract

Three-dimensional (3D) nonlinear diving guidance strategy considering the coupling between longitudinal and lateral motions for hypersonic vehicle is investigated in this paper. It constructs the complete nonlinear coupling motion equation without any approximations based on diving relative motion relationship directly, and converts it into linear state space equation with the same relative degree by feedback linearization. With the linear equation, slide mode control with strong robustness is employed to design the guidance law, and 3D diving guidance law which can satisfy terminal impact point and falling angle constraints with high precision is obtained by substituting the previous control law into the origin nonlinear guidance system. Besides, regarding lateral overload as the standard, hybrid control strategy which can take full advantage of the excellent characters of both bank-to-turn (BTT) and skid-to-turn (STT) controls is designed to improve the guidance accuracy further. Finally, the results of CAV-H vehicle guidance test show that the algorithm can realize high accuracy guidance even if serious motion coupling exists, and has strong robustness to the path disturbances and navigation errors as well.

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References

  1. Phillips T H. A common aero vehicle (CAV) model, description and employment guide. Schafer Corporation for AFRL and AFSPC, 27 January 2003

    Google Scholar 

  2. Richie G. The common aero vehicle: Space delivery system of future. AIAA Space Technology Conference & Exposition 28–30 Sept. 1999 Albuquerque NM, 1999

    Google Scholar 

  3. Xu M L, Chen K J, Liu L H, et al. Quasi-equilibrium glide adaptive guidance for hypersonic vehicles. Sci China Tech Sci, 2012, 55: 856–866

    Article  MathSciNet  Google Scholar 

  4. Yuan P J, Chern J S. Ideal proportional navigation. J Guid Control Dynam, 1992, 15: 1161–1165

    Article  Google Scholar 

  5. Chen K J, Zhao H Y. An optimal guidance law of maneuvering reentry vehicle at tacking ground fixed target (in Chinese). J Astronaut, 1994, 15: 1–7

    Google Scholar 

  6. Sun W M, Zheng Z Q. A new variable structure guidance law of three dimensional with multiple constraints (in Chinese). J Astronaut, 2007, 28: 344–349

    Google Scholar 

  7. Zhu J W, Liu L H, Tang G J, et al. Optimal Guidance with Multi-targets for Hypersonic Vehicle in Dive Phase. 6th International Conference in Recent Advances in Space Technologies, Turkey, 2013

    Google Scholar 

  8. Yin Y X, Yang M, Wu P. Three-dimensional guidance law with attack angle constraint for maneuverable target (in Chinese). J Sol Roc Tech, 2010, 33: 237–241

    Google Scholar 

  9. Fan Z, Yu D H, Gu W J. Three-dimensional guidance law with attack angle constraint and maneuvering target compensation (in Chinese). Syst Eng Ele, 2011, 33: 1856–1860

    Google Scholar 

  10. Peng S C, Sun W M, Wang N, et al. 3D guidance law of BTT missile considering movement coupling (in Chinese). J Astronaut, 2010, 31: 968–974

    Google Scholar 

  11. Han D P, Sun W M, Zheng Z Q, et al. A new 3D guidance law based on a lie-group method (in Chinese). J Astronaut, 2009, 30: 468–475

    Google Scholar 

  12. Jurdjevicw V, Sussmann H J. Control system on Lie group. J Differ Equations, 1972, 12: 313–329

    Article  Google Scholar 

  13. Chiou Y C, Kuo C Y. Geometric approach to three dimensional missile guidance problem. J Guid Control Dynam, 1998, 21: 335–341

    Article  Google Scholar 

  14. Cloutier J R, Donald T S. Nonlinear hybrid bank-to-turn/skid-to-turn missile autopilot design. AIAA Guidance, Navigation, and Control Conference and Exhibit. Montreal, Canada, 2001

    Google Scholar 

  15. Bharadwaj S, Rao A V, Mease K D. Entry trajectory tracking law via feedback linearization. J Guid Control Dynam, 1998, 21: 726–732

    Article  Google Scholar 

  16. Vinh N X. Optimal Trajectories in Atmospheric Flight. New York: Elsevier, 1981

    Google Scholar 

  17. Isidori A. Nonlinear Control Systems. London: Bertelsmann Springer Publishing Group, 2005

    Google Scholar 

  18. Wang P, Tang G J, Liu L H, et al. Nonlinear hierarchy-structured predictive control design for a generic hypersonic vehicle. Sci China Tech Sci, 2013, 56: 2025–2036

    Article  Google Scholar 

Download references

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Authors and Affiliations

  1. College of Aerospace Science and Engineering, National University of Defense Technology, Changsha, 410073, China

    JianWen Zhu, LuHua Liu, GuoJian Tang & WeiMin Bao

  2. China Aerospace Science and Technology Corporation, Beijing, 100048, China

    WeiMin Bao

Authors
  1. JianWen Zhu
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  2. LuHua Liu
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  3. GuoJian Tang
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  4. WeiMin Bao
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Correspondence to GuoJian Tang.

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Zhu, J., Liu, L., Tang, G. et al. Three-dimensional nonlinear coupling guidance for hypersonic vehicle in dive phase. Sci. China Technol. Sci. 57, 1824–1833 (2014). https://doi.org/10.1007/s11431-014-5615-0

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  • DOI: https://doi.org/10.1007/s11431-014-5615-0

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