战术导弹三回路过载驾驶仪时频特性分析

doi:10.3969/j.issn.1000-1093.2013.07.005

兵工学报 ›› 2013, Vol. 34 ›› Issue (7): 828-834.doi: 10.3969/j.issn.1000-1093.2013.07.005

战术导弹三回路过载驾驶仪时频特性分析

王嘉鑫, 林德福, 祁载康

北京理工大学宇航学院, 北京100081

收稿日期:2012-10-21 修回日期:2012-10-21 上线日期:2014-08-19
作者简介:王嘉鑫(1985—),男,博士研究生
基金资助:
国家自然科学基金项目(61172182)

Analysis of Tactical Missile Three-loop Lateral Acceleration Autopilot in the Time and Frequncy Domain

WANG Jia-xin, LIN De-fu, QI Zai-kang

School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China

Received:2012-10-21 Revised:2012-10-21 Online:2014-08-19

摘要/Abstract

摘要： 基于小扰动线性化的纵向弹体控制模型,研究了三回路驾驶仪及其新弹体的结构、快速性、鲁棒性以及对静不稳定弹体的增稳能力,建立并分析了驾驶仪的无量纲模型,针对三回路驾驶仪提出了一种新的设计思路。研究结果表明:阻尼回路新弹体增稳能力和鲁棒性较弱;增稳回路新弹体具有良好的鲁棒性和增稳能力但响应速度较慢;三回路驾驶仪通过设计一个远离开环弹体频率的一阶主导极点和一对阻尼合适的高频极点,使系统具备较好的快速性、稳定性和鲁棒性。

关键词: 兵器科学与技术, 导弹控制系统, 三回路过载驾驶仪, 静不稳定, 性能指标

Abstract: Based on the linearized and small perturbation model of the longitudinal missile control system, the configuration, response time, robustness and capability of stabilizing a static unstable missile are studied for the aforementioned systems. A non-dimensional model of the autopilot is established and analyzed, and a new method for the three-loop autopilot design is put forward. The results indicate that thestabilizing loop system is more robust and capable of stabilizing a static unstable missile compared withthe damping loop system,but its response time is longer; while the three-loop autopilot is more robust,and faster than the stabilizing loop system by designing a chief pole at lower frequency and a pair of higher frequency conjugate poles with a appropriate damping ratio.

Key words: ordance science and technology, missile control system, three-loop lateral acceleration autopilot, static instability, performance index

中图分类号:

TJ765. 2

王嘉鑫, 林德福, 祁载康. 战术导弹三回路过载驾驶仪时频特性分析[J]. 兵工学报, 2013, 34(7): 828-834.

WANG Jia-xin, LIN De-fu, QI Zai-kang. Analysis of Tactical Missile Three-loop Lateral Acceleration Autopilot in the Time and Frequncy Domain[J]. Acta Armamentarii, 2013, 34(7): 828-834.

参考文献

[1] Mracek C P, Ridgely D B. Missile longitudinal autopilot: comparison of multiple three loop topologies[C]//AIAA Guidance, Navigation, and Control Conference. San Francisco: AIAA, 2005:2005-6380.

[2] Mracek C P, Ridgely D B. Missile longitudinal autopilot: connections between optimal control and classical topologies[C]//AIAA Guidance, Navigation, and Control Conference. San Francisco:AIAA, 2005: 2005-6381.

[3] Wise K A. Robust stability analysisi of adaptive missile autopolit[C] //AIAA Guidance, Navigation, and Control Conference.Keystone: AIAA, 2008:1-18.

[4] Kang S, Kim H J, Won D, et al. Robust roll-pitch-yaw integratedautopilot for a high angle-of-attack missile [ C] //AIAA Guidance, Navigation, and Control Conference. Keystone: AIAA,2008: 2008-7001.

[5] Nesline F W, Zarchan P. Robust instrumentation configuration for homing missile flight control[C]//Guidance and Control Conference. Reston: AIAA, 1980: 209-219.

[6] Zarchan P. Tactical and strategic missile guidance[M]. 5rd ed.Virginia: AIAA Inc, 2007: 483-539.

[7] Garnell P, East D J. Guided weapon control systems[M]. Oxford: Pergamon Press, 1977.

[8] Lin D F, Fan J F, Qi Z K, et al. Analysis and improvement of missile three-loop autopilots [J]. Journal of Systems Engineering and Electronics, 2009, 20(4):844-851.

[9] Fan J F, Lin D F, Qi Z K, et al. Missile autopilot design using optimal control and frequency constraint[C] //2nd International Syposium on Systems and Contron in Aerospace and Astronauties,ISSCAA, Shenzhen, China: IEEE, 2008: 1-6.

[10] 王辉,林德福,祁载康. 导弹伪攻角反馈的三回路驾驶仪分析[J]. 系统工程与电子技术,2012,34(1):92-98.

WANG Hui, LIN De-fu, QI Zai-kang. Design and analysis of missile three-loop autopilot with pseudo-angle of attack feedback [J]. Systems Engineering and Electronics, 2012, 34(1):92-98. (in Chinese)

[11] Wang H, Lin D F, Wang J, et al. Design and analysis of missile two-loop autopilot with PI compensator under Multi-constraints [C]//3rd International Conference on Advanced Computer Theory and Engineering (ICACTE). Chengdu IEEE, 2010:V5-117- V5-121.

[12] 魏先利, 夏群力, 祁载康. 姿态及过载自动驾驶仪比例导引对比研究[J]. 弹箭与制导学报, 2003, 23(4): 5-8, 12.

WEI Xian-li, XIA Qun-li, QI Zai-kang. Comparing study of proportion navigation guidance law of attitude and acceleration autopilots[J]. Journal of Projectiles, Rockets, Missiles, and Guidance, 2003, 23(4): 5-8, 12. (in Chinese)

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战术导弹三回路过载驾驶仪时频特性分析

Analysis of Tactical Missile Three-loop Lateral Acceleration Autopilot in the Time and Frequncy Domain

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