基于Terminal滑模的小行星探测器着陆连续控制

刘克平; 曾建鹏; 赵博; 李元春

doi:10.13700/j.bh.1001-5965.2013.0638

基于Terminal滑模的小行星探测器着陆连续控制

doi: 10.13700/j.bh.1001-5965.2013.0638

长春工业大学电气与电子工程学院, 长春 130012

基金项目: 国家973重点基础研究发展计划资助项目(2012CB720000)

详细信息

作者简介:
刘克平(1971-),男,吉林长春人,教授,liukeping@mail.ccut.edu.cn.

中图分类号: V448.22
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- 被引次数: 0
出版历程
- 收稿日期: 2013-11-06
- 网络出版日期: 2014-10-20

Continuous control for probe landing based on Terminal sliding mode

College of Electrical and Electronic Engineering, Changchun University of Technology, Changchun 130012, China

摘要

摘要: 针对弱引力场不规则小行星探测器安全下降与着陆,提出了一种基于比例微分(PD,Proportional plus Derivative)及非奇异Terminal滑模的连续控制方法.在着陆点坐标系下推导了探测器的动力学方程,设计了开环燃料次最优多项式标称轨迹制导方法.针对下降和着陆两个不同阶段提出了PD和非奇异Terminal滑模变结构连续控制方法.将PD控制的易操作性与非奇异Terminal滑模控制收敛速度快、调整时间短有效结合,保证了探测器安全着陆.仿真结果表明了提出方法的可行性和有效性.
- 小行星 /
- 软着陆 /
- PD控制 /
- Terminal滑模控制 /
- 连续控制
Abstract: For the probe descending and landing safely, a continuous control method based on proportional plus derivative (PD) and nonsingular Terminal sliding mode was proposed. First, the dynamic equation was deduced in the landing site coordinate system. Then the nominal trajectory guidance method based on optimal polynomial in open-loop state was designed, by which the consumption of fuel was suboptimal. Third, the operability of PD control method was combined with the fast convergence and short adjustment time of nonsingular Terminal sliding mode control method. In the descending phase, the PD control method was adopted. In the landing phase, the continuous control method based on nonsingular Terminal sliding mode variable structure was adopted. The influence caused by uncertainty during landing was compensated by nonsingular Terminal sliding mode control, which could effectively suppress the influence of external disturbance and weaken the system chattering. Finally, simulation results demonstrate that the probe can land safely, and also show the effectiveness and robustness of the proposed method.
- asteroid /
- soft landing /
- PD control /
- Terminal sliding mode control /
- continuous control

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参考文献(17)

[1]	Sears D W G, Allen C C,Bell M S,et al.The hera near-earth asteroid sample return mission: science requirements of the sample collector[J].Advances in Space Research,2004,34(11): 22762280
[2]	崔祜涛, 崔平远.软着陆小行星的自主导航与制导[J].宇航学报,2002,23(5):1-5 Cui Hutao,Cui Pingyuan.Autonomous navigation and guidance for soft-landing asteroid[J].Journal of Astronautics,2002, 23(5): 1-5(in Chinese)
[3]	Li S,Cui P Y, Cui H T.Autonomous navigation and guidance for landing on asteroids[J].Aerospace Science and Technology,2006,10(3):239-247
[4]	Broschart S B, Scheeres D J.Spacecraft descent and translation in the small-body fixed frame[R].AIAA-2004-4865,2004
[5]	Zhang Z X, Wang W D,Li L T,et al.Robust sliding mode guidance and control for soft landing on small bodies[J].Journal of the Franklin Institute,2012,349(2):493-509
[6]	Shao W, Cui P Y,Cui H T.Physical properties calculation of small body using points triangulations[J].Journal of Harbin Institute of Technology,2010,42(5):687-691
[7]	宋顺广,王春洁. 基于蒙特卡罗法的月球探测器着陆稳定性分析[J].北京航空航天大学学报,2013,39 (9):1192-1196 Song Shunguang,Wang Chunjie.Landing stability analysis of the lunar lander based on Monte Carlo approach[J].Journal of Beijing University of Aeronautics and Astronautics,2013,39(9):1192-1196(in Chinese)
[8]	高艾,崔平远, 崔祜涛.深空着陆器对偶控制策略[J].哈尔滨工业大学学报,2012,26(11):75-80 Gao Ai,Cui Pingyuan,Cui Hutao.Dual control strategy of planetary lander[J].Journal of Harbin Institute of Technology,2012,26(11):75-80(in Chinese)
[9]	Lan Q X, Li S,Yang J,et al.Finite-time control for soft landing on an asteroid based on line-of-sight angle[J].Journal of the Franklin Institute,2014,351(1):383-398
[10]	邢健,齐瑞云. 考虑燃料晃动效应的航天器自适应滑模姿态控制[J].空间控制技术与应用,2013,39(2):42-47 Xing Jian,Qi Ruiyun.Adaptive sliding-mode attitude control of spacecraft with fuel sloshing[J].Aerospace Control and Application,2013,39(2):42-47(in Chinese)
[11]	曾宪法, 王小虎,张晶,等.高超声速飞行器的干扰补偿 Terminal 滑模控制[J].北京航空航天大学学报,2012, 38(11): 1454-1458 Zeng Xianfa,Wang Xiaohu,Zhang Jing,et al.Disturbance compensated terminal sliding mode control for hypersonic vehicles[J].Journal of Beijing University of Aeronautics and Astronautics,2012,38(11):1454-1458(in Chinese)
[12]	Washabaugh P D, Scheeres D J.Energy and stress distributions in ellipsoids[J].Icarus,2002,159(2):314-321
[13]	单永正. 月球探测器软着陆的制导问题研究[D].哈尔滨:哈尔滨工业大学,2009 Shan Yongzheng.Research on guidance problem of lunar probe for soft landing[D].Harbin:Harbin Institute of Technology,2009(in Chinese)
[14]	郗晓宁,曾国强, 任萱,等.月球探测器轨道设计[M].北京:国防工业出版社,2001:119-139 Xi Xiaoning,Zeng Guoqiang,Ren Xuan,et al.Lunar probe track design[M].Beijing:National Defense University Press,2001:119-139(in Chinese)
[15]	孙军伟,崔平远. 月球软着陆多项式制导控制方法[J].宇航学报,2007,28(5):1171-1174 Sun Junwei,Cui Pingyuan.Polynomial guidance law for lunar soft landing[J].Journal of Astronautics,2007,28(5):1171-1174(in Chinese)
[16]	Feng Y, Yu X H,Man Z H.Non-singular terminal sliding mode control of rigid manipulators[J].Automatica,2002,38(12):2159-2167
[17]	张巍巍, 王京.基于指数趋近律的非奇异Terminal滑模控制[J].控制与决策,2012,27(6):909-913 Zhang Weiwei,Wang Jing.Nonsingular terminal sliding model control based on exponential reaching law[J].Control and Decision,2012,27(6):909-913(in Chinese)