[1]冯云山,杨照华.模糊自适应的高超飞行器控制与干扰[J].智能系统学报,2012,7(02):129-134.
 FENG Yunshan,YANG Zhaohua.Control and disturbance analysis of hypersonic vehicles based on fuzzy adaptive[J].CAAI Transactions on Intelligent Systems,2012,7(02):129-134.
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模糊自适应的高超飞行器控制与干扰(/HTML)
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《智能系统学报》[ISSN:1673-4785/CN:23-1538/TP]

卷:
第7卷
期数:
2012年02期
页码:
129-134
栏目:
出版日期:
2012-04-25

文章信息/Info

Title:
Control and disturbance analysis of hypersonic vehicles based on fuzzy adaptive
文章编号:
1673-4785(2012)02-0129-06
作者:
冯云山杨照华
北京航空航天大学 仪器光电学院,北京 100191
Author(s):
FENG Yunshan YANG Zhaohua
School of Instrument Science and Optoelectronics Engineering, Beihang University, Beijing 100191, China
关键词:
模糊自适应高超声速飞行器干扰不确定性
Keywords:
fuzzy adaptive hypersonic vehicle disturbance uncertainty
分类号:
TP18;V448.22+3
文献标志码:
A
摘要:
针对具有超大飞行马赫数、超宽飞行包络、飞行环境复杂等特点的高超声速飞行器,提出了基于模糊自适应的高超飞行器高度控制方法,分别设计了高度和速度控制器.针对所设计的控制器,分析了气动干扰力矩、测量噪声、舵机干扰、气动参数不确定性和飞行器模型参数不确定性对飞行器高度控制和速度控制效果的影响,然后又分析了综合考虑以上干扰和不确定性对飞行器高度控制和速度控制效果的影响.仿真结果表明,对各种干扰和不确定性,所设计的控制器速度和高度控制有较好的跟踪性和鲁棒性,达到了满意的效果.
Abstract:
Hypersonic vehicles have ultrawide flight envelopes, a high flight Mach number, and complex flight environments. Due to these issues, this paper presented a control method based on fuzzy adaptive and designed altitude and velocity controllers. For the controllers, the effects of aerodynamic disturbance torque, measurement noise, interference with the steering gear, pneumatic parameter uncertainty, and aircraft model parameter uncertainty were analyzed in light of the aircraft height and speed control. The comprehensive effect of the above issues was then analyzed. Simulation results show that the altitude and velocity controllers have great tracking ability and robustness to various disturbances and uncertainties, and the designed controllers displays satisfactory results. 

参考文献/References:

[1]黄国勇,姜长生,薛雅丽. 新型自适应Terminal滑模控制及应用[J]. 航空动力学报, 2008, 23(1): 156162.
 HUANG Guoyong, JIANG Changsheng, XUE Yali. An adaptive terminal sliding mode control and its applications[J]. Journal of Aerospace Power, 2008, 23(1): 156162.
[2]吴森堂.飞航导弹制导控制系统随机鲁棒分析与设计[M]. 北京: 国防工业出版社, 2010: 4049.
[3]张军,王玫,赵德安. 高超飞行器的冉入非线性鲁棒控制[J]. 动力学与控制学报, 2011, 9(11): 9196.
 ZHANG Jun, WANG Mei, ZHAO De’an. Reentry nonlinear robust control law for hypersonic vehicles[J]. Journal of Dynamics and Control, 2011, 9(11): 9196.
[4]XU H J, MIRMIRANI M D, IOANNOU P A. Adaptive sliding model control design for a hypersonic fight vehicle[J]. AIAA Journal of Guidance, Control, and Dynamics, 2004, 27(5): 829837.
[5]LIN Chuankai, WANG Shengde. Adaptive fuzzy control of banktoturn missiles[C]//Proceedings of the Industrial Electronics, Control and Instrumentation. Taipei, China, 1996, 2: 596601.
[6]JIN Yuqiang, GU Wenjin, WU Jinhua, et al. Sliding mode control of BTT missile based on fuzzyneural approach[C]//Proceedings of the 5th World Congress on Intelligent Control and Automation. Hangzhou, China, 2004, 6: 54835486.
[7]高道祥,孙增圻,罗熊,等. 基于Backstepping的高超声速飞行器模糊自适应控制[J].控制理论与应用, 2008, 25(5): 805810.
GAO Daoxiang, SUN Zengqi, LUO Xiong, et al.Fuzzy adaptive control for hypersonic vehicle via Baskstepping method[J]. Control Theory & Applications, 2008, 25(5): 805810.
[8]李长青. 导弹控制系统设计研究[D]. 哈尔滨:哈尔滨工程大学, 2002: 1225.
 LI Changqing. Investigation on design of missile control system[D]. Harbin: Harbin Engineering University, 2002:1225.

备注/Memo

备注/Memo:
收稿日期:2011-11-14.
网络出版日期:2012-03-09.
基金项目:国家自然科学基金资助项目(91016004).
通信作者:冯云山.            E-mail:songshan68@163.com.
作者简介:
冯云山,男,1987年生,硕士研究生,主要研究方向为导航制导与控制.
 杨照华,女,1975年生,副教授,博士.主要研究方向为航天器姿态轨道控制、导航制导与控制等.曾经作为技术骨干参与国家“973”计划项目1项、国防重大基础科研项目1项、国家自然科学基金1项、国家“863”计划重大项目1项,目前负责国家“863”计划项目1项、国家自然科学基金1项. 曾获中国博士后科学基金一等资助,北京航空航天大学“蓝天新秀”,获部级二等奖1项、国防科学技术进步二等奖1项. 发表学术论文20余篇,其中被SCI、EI检索10余篇,被ISTP检索10篇,授权专利5项,登记软件著作权4项.
更新日期/Last Update: 2012-07-12