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基于燃料最优解的火星精确着陆制导策略研究

郭延宁 马广富 曾添一 崔祜涛

郭延宁, 马广富, 曾添一, 崔祜涛. 基于燃料最优解的火星精确着陆制导策略研究[J]. 深空探测学报, 2015, 2(1): 61-68. doi: 10.15982/j.issn.2095-7777.2015.01.009
引用本文: 郭延宁, 马广富, 曾添一, 崔祜涛. 基于燃料最优解的火星精确着陆制导策略研究[J]. 深空探测学报, 2015, 2(1): 61-68. doi: 10.15982/j.issn.2095-7777.2015.01.009
GUO Yanning, MA Guangfu, ZENG Tianyi, CUI Hutao. Mars Precision Landing Guidance Strategy based on Fuel Optimal Solutions[J]. Journal of Deep Space Exploration, 2015, 2(1): 61-68. doi: 10.15982/j.issn.2095-7777.2015.01.009
Citation: GUO Yanning, MA Guangfu, ZENG Tianyi, CUI Hutao. Mars Precision Landing Guidance Strategy based on Fuel Optimal Solutions[J]. Journal of Deep Space Exploration, 2015, 2(1): 61-68. doi: 10.15982/j.issn.2095-7777.2015.01.009

基于燃料最优解的火星精确着陆制导策略研究

doi: 10.15982/j.issn.2095-7777.2015.01.009
基金项目: 国家973计划项目(2012CB720000) ;国家自然科学基金资助项目(61403103);中国博士后科学基金资助项目(2014M550195)

Mars Precision Landing Guidance Strategy based on Fuel Optimal Solutions

  • 摘要: 针对火星着陆任务高实时性和低燃耗的需求,提出了一种新的基于开环燃料最优解的精确着陆制导策略。通过分析开环燃料最优解特性,设计了利用发动机推力幅值切换处的状态作为路径点结合最优线性制导律进行分段制导的制导策略,在无需存储全部燃料最优轨迹的前提下,实现具有近燃料最优特性的着陆任务,节省了大量的存储空间。同时详细讨论了包括全局燃料最优解获取、路径点提取、路径点拟合等一系列关键问题,并通过典型火星着陆场景的大量数学仿真验证了所提出策略的可行性和优越性。
  • [1] Braun R D, Manning R M. Mars exploration entry, descent and landing challenges[J]. Journal of Spacecraft and Rockets, 2007,44(2):310-323.
    [2] 安德鲁·鲍尔等著. 行星着陆器和进入探测器[M].殷前根等译.北京:中国宇航出版社,2010.[ Ball A J,et al. Planetary landers and entry probes[M]. Translator, Yin Q G, et al. Beijing: China Astronautic Publishing House, 2010.]
    [3] D'Souza C N. An optimal guidance law for planetary landing[C]//Proceedings of the AIAA Guidance, Navigation and Control Conference. New Orleans:[s.n.], 1997.
    [4] Steinfeldt B A, Grant M J, Matz D A,et al. Guidance, navigation, and control system performance trades for Mars pinpoint landing[J]. Journal of Spacecraft and Rockets, 2010,47(1):188-198.
    [5] Najson F, Mease K D. Computationally inexpensive guidance algorithm for fuel-efficient terminal descent[J]. Journal of Guidance, Control, and Dynamics, 2006,29(4):955-964.
    [6] Furfaro R, Selnick S, Cupples M L, et al. Non-linear sliding guidance algorithms for precision Lunar landing[C]//21st AAS/AIAA Space Flight Mechanics Meeting. Louisiana, New Orleans:[s.n.], 2011:945-964.
    [7] Gaudet B, Furfaro R. Adaptive pinpoint and fuel efficient Mars landing using reinforcement learning[C]//22ed AAS/AIAA Space Flight Mechanics Meeting. Charleston, South Carolina:[s.n.], 2012:1309-1328.
    [8] Guo Y, Hawkins M, Wie B. Applications of generalized zero-effort-miss / zero-effort-velocity feedback guidance algorithm[J]. Journal of Guidance, Control and Dynamics, 2013,36(3):810-820.
    [9] Rutishauser D K, Epp C D, Robertson E A. Free-flight terrestrial rocket lander demonstration for NASA's autonomous landing and Hazard avoidance technology (ALHAT) system[C]//AIAA SPACE 2012 Conference & Exposition. Pasadena, California:[s.n.], 2012.
    [10] Acikmese B, Ploen S R. Convex programming approach to powered descent guidance for Mars landing[J]. Journal of Guidance, Control, and Dynamics, 2007,30(5):1353-1366.
    [11] Acikmese B, Blackmore L. Lossless convexification of a class of optimal control problems with non-convex control constraints[J]. Automatica, 2011,47(2):341-347.
    [12] Sostaric R R, Rea J R. Powered descent guidance methods for the Moon and Mars[C]//AIAA Guidance, Navigation, and Control Conference and Exhibit. San Francisco, California:[s.n.], 2005.
    [13] Shen H J, Seywald H, Powell R W. Desensitizing the minimum-fuel powered descent for Mars pinpoint landing[J]. Journal of Guidance, Control, and Dynamics, 2010,33(1):108-115.
    [14] Brian Kent Birge III. A computational intelligence approach to the Mars precision landing problem[D]. PhD dissertation of North Carolina State University, 2008.
    [15] Liu R, Li S, Chen X, et al. Powered-descent trajectory optimization scheme for Marslanding[J]. Advances in Space Research, 2013, 52(11):1888-1901.
    [16] Singh G, SanMartin A M, Wong E C. Guidance and control design for powered descent and landing on Mars[C]//IEEE Aerospace Conference. [S.l.]: IEEE, 2007:1-8.
    [17] Cui P Y, Gao A, Cui H T. Receding Horizon-based dual control strategy for pinpoint planetary landing[J]. Transactions of the Japan Society for Aeronautical and Space Sciences, 2012,55(4):222-228.
    [18] Li M D, Jing W X, Macdonald M,et al. Adaptive backstepping control for optimal descent with embedded autonomy[J]. Aerospace Science and Technology, 2011,15(7):589-594.
    [19] Guo Y, Hawkins M, and Wie B. Waypoint-optimized zero-effort-miss/zero-effort-velocity feedback guidance for Mars landing[J]. Journal of Guidance, Control, and Dynamics, 2013,36(3):799-809.
  • [1] 周敬, 胡军, 张斌.  限制性三体问题共线平动点轨道近似解析解 . 深空探测学报, 2020, 7(1): 93-101. doi: 10.15982/j.issn.2095-7777.2020.20190408001
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  • 收稿日期:  2014-12-01
  • 修回日期:  2015-02-12

基于燃料最优解的火星精确着陆制导策略研究

doi: 10.15982/j.issn.2095-7777.2015.01.009
    基金项目:  国家973计划项目(2012CB720000) ;国家自然科学基金资助项目(61403103);中国博士后科学基金资助项目(2014M550195)

摘要: 针对火星着陆任务高实时性和低燃耗的需求,提出了一种新的基于开环燃料最优解的精确着陆制导策略。通过分析开环燃料最优解特性,设计了利用发动机推力幅值切换处的状态作为路径点结合最优线性制导律进行分段制导的制导策略,在无需存储全部燃料最优轨迹的前提下,实现具有近燃料最优特性的着陆任务,节省了大量的存储空间。同时详细讨论了包括全局燃料最优解获取、路径点提取、路径点拟合等一系列关键问题,并通过典型火星着陆场景的大量数学仿真验证了所提出策略的可行性和优越性。

English Abstract

郭延宁, 马广富, 曾添一, 崔祜涛. 基于燃料最优解的火星精确着陆制导策略研究[J]. 深空探测学报, 2015, 2(1): 61-68. doi: 10.15982/j.issn.2095-7777.2015.01.009
引用本文: 郭延宁, 马广富, 曾添一, 崔祜涛. 基于燃料最优解的火星精确着陆制导策略研究[J]. 深空探测学报, 2015, 2(1): 61-68. doi: 10.15982/j.issn.2095-7777.2015.01.009
GUO Yanning, MA Guangfu, ZENG Tianyi, CUI Hutao. Mars Precision Landing Guidance Strategy based on Fuel Optimal Solutions[J]. Journal of Deep Space Exploration, 2015, 2(1): 61-68. doi: 10.15982/j.issn.2095-7777.2015.01.009
Citation: GUO Yanning, MA Guangfu, ZENG Tianyi, CUI Hutao. Mars Precision Landing Guidance Strategy based on Fuel Optimal Solutions[J]. Journal of Deep Space Exploration, 2015, 2(1): 61-68. doi: 10.15982/j.issn.2095-7777.2015.01.009
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