拦截大气层外机动目标的模糊导引规律

田源; 王俊波; 任章

拦截大气层外机动目标的模糊导引规律

北京航空航天大学自动化科学与电气工程学院, 北京 100191

详细信息

中图分类号: V 448.2
计量
- 文章访问数: 3088
- HTML全文浏览量: 35
- PDF下载量: 986
- 被引次数: 0
出版历程
- 收稿日期: 2009-05-20
- 网络出版日期: 2010-07-30

Fuzzy guidance law for interception of exoatmospheric maneuvering targets

School of Automation Science and Electrical Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 针对大气层外机动目标的拦截问题,分析了轨控发动机作用下拦截器与目标的相对运动规律,并据此提出了拦截能力的估计方法.根据轨控发动机能够修正的视线转率上限和最短工作时间设计了开机曲线.结合开机曲线和拦截能力的估算方法提出了基于模糊逻辑的导引规律.该导引规律根据专家经验制定模糊规则,利用相对距离和拦截能力作为模糊推理系统的输入对发动机的开机曲线进行调整,结合继电器方式的发动机开关机规律形成制导指令.针对两种典型的目标机动方式,通过仿真验证了该导引规律对机动目标进行拦截的有效性.
- 大气层外拦截器 /
- 末制导律 /
- 机动目标 /
- 模糊逻辑
Abstract: The relative motion law between the target and the interceptor was analyzed when the divert thruster was on or off. An estimator of the interception ability was proposed based on the relative motion law. On-off conditions for the divert thruster were designed according to the shortest working interval of the divert thruster and the upper boundary of the line-of-sight rate that could be restrained. A novel terminal guidance law was proposed based on the estimator and the on-off conditions. The guidance law took advantage of the experts- experiences to construct the fuzzy rules and adjusted the on-off conditions of the divert thruster based on the relative range and the interception ability. A relay on-off method was utilized to control the divert thruster. The effectiveness and the performance of the fuzzy guidance law are demonstrated through the simulation in which the guidance law is applied to intercept two kinds of maneuvering targets.
- exoatmospheric interceptor /
- terminal guidance law /
- maneuvering target /
- fuzzy logic

HTML全文

参考文献(1)

[1] Zarchan P.Tactical and strategic missile guidance[M].3rd ed.Washington DC:American Institute of Aeronautics and Astronautics,1990:95-118,291-372  [2] Hablani H B.Pulsed guidance of exoatmospheric interceptors with image processing delays in angle measurements //AIAA Guidance,Navigation,and Control Conference and Exhibit.Denver:AIAA,2000:1-18  [3] 张雅声,程国采,陈克俊.高空动能拦截器末制导导引方法设计与实现[J].现代防御技术,2001,29(2):31-34 Zhang Yasheng,Cheng Guocai,Chen Kejun.Design and realization of terminal guidance’s method for kinetic energy interceptor at high altitude[J].Modern Defence Technology,2001,29(2):31-34(in Chinese)  [4] 田源,任章.大气层外动能拦截器末段导引规律设计[J].宇航学报,2009,30(2):474-480 Tian Yuan,Ren Zhang.Design of guidance law for exoatmospheric interceptor during its terminal course[J].Journal of Astronautics,2009,30(2):474-480(in Chinese) [5] Asher B J,Yaesh I.Advances in missile guidance theory[M].Reston:American Institute of Aeronautics Astronautics,1998 [6] Shieh C S.Design of three-dimensional missile guidance law via tunable nonlinear H_∞ control with saturation constraint[J].IET Control Theory and Applications,2007,1(3):756-763 [7] 周荻.寻的导弹新型导引规律[M].北京:国防工业出版社,2002 Zhou Di.New guidance laws for homing missile[M].Beijing:National Defence Industry Press,2002 (in Chinese)  [8] Anthony T C,Wie B.Pulse-modulated control synthesis for a flexible spacecraft[J].Jounal of Guidance,Control and Dynamics,1990,13(6):1014-1022  [9] 周红建,赵拥军,吴瑞林.PWPF调节器在空间拦截器侧力控制中的应用[J].系统工程与电子技术,1997,18(4):9-12 Zhou Hongjian,Zhao Yongjun,Wu Ruilin.Application of PWPF modulator in space interceptor side force control[J].System Engineering and Electronics,1997,18(4):9-12 (in Chinese)

施引文献

资源附件(0)

访问统计