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Volume 35 Issue 11
Nov.  2009
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Journal of Beijing University of Aeronautics and Astronautics  > 2009  >  35(11): 1344-1348.
Li Huifeng, Xie Ling. Reentry guidance law design for RLV based on predictor-corrector method[J]. Journal of Beijing University of Aeronautics and Astronautics, 2009, 35(11): 1344-1348. (in Chinese)
Citation: Li Huifeng, Xie Ling. Reentry guidance law design for RLV based on predictor-corrector method[J]. Journal of Beijing University of Aeronautics and Astronautics, 2009, 35(11): 1344-1348. (in Chinese)
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Reentry guidance law design for RLV based on predictor-corrector method

  • School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

  • Received Date: 07 Nov 2008
  • Publish Date: 30 Nov 2009
    Abstract
  • A new on-line guidance law designed based on predictor-corrector method and quasi-equilibrium glide condition (QEGC) for the reentry of hypersonic reusable launch vehicles (RLV) was presented. This advanced guidance law can generate reasonable bank angle profiles which can simultaneously satisfy the target accuracy and the path constraints such as heat rate flow, normal load and dynamic pressure. After establishing the 3DOF dynamic equations and specifying the initial states, target accuracy (CEP) and path constraints, the predictor-corrector method and quasi-equilibrium glide condition were explained in detail. The predictor-corrector method was used to generate the basic reentry guidance law for RLV, and the QEGC was used to modify the bank angle profile so that it can satisfy all path constraints. Finally, the Monte Carlo simulation was used to evaluate the performance of the guidance law under uncertain initial states. The simulation results show that this guidance law not only works accurately and fast but also has a high robustness.

     

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  • [1] 沈作军.航天器先进再入制导技术研究综述 中国宇航学会首届学术会议论文集.北京:宇航出版社, 2005:103-104 Shen Zuojun. Advanced spacecraft re-entry guidance technology review The Academic Conference Proceedings of Chinese Academy of Astronautics. Beijing: China astronautic Publishing House, 2005:103-104 (in Chinese) [2] Shen Z, Lu P. On-board generation of three-dimensional Constrained entry trajectories [J]. Journal of Guidance Control and Dynamics, 2003, 26(1):111-121 [3] 赵汉元.飞行器再入动力学和制导[M].长沙:国防科技大学出版社, 1997:383 Zhao Hanyuan. The reentry dynamics and guidance of flying vehicles[M]. Changsha: Press of National University of Defense Technology, 1997: 383(in Chinese) [4] Vinh N X, Optimal trajectories in atmospheric flight[M]. New York: Elsevier Scientific Publishing Company, 1981:346-367 [5] Shkadov L M, Bukhanova R S, Illarionov V F, et al. Mechanics of optimum three-dimensional motion of aircraft in the atmosphere . NASA TT-777, 1975 [6] Harpold J C, Graves C A. Shuttle entry guidance[J]. The Journal of the Astronautically Sciences, 1979, XXXVII(3): 239-268 [7] Lu Ping. Predictor-corrector entry guidance for low lifting vehicles . AIAA 2007-6425, 2007
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