基于最优二次型理论的滚转导弹三回路驾驶仪设计与研究

doi:10.3969/j.issn.1000-1093.2015.05.010

兵工学报 ›› 2015, Vol. 36 ›› Issue (5): 831-838.doi: 10.3969/j.issn.1000-1093.2015.05.010

基于最优二次型理论的滚转导弹三回路驾驶仪设计与研究

范世鹏^1,2，林德福¹，姚怀瑾¹，路宇龙³，祁载康¹

（1.北京理工大学宇航学院，北京 100081； 2.北京航天自动控制研究所，北京 100854; 3.北京电子工程总体研究所，北京 100854)

收稿日期:2014-06-18 修回日期:2014-06-18 上线日期:2015-07-09
作者简介:范世鹏（1986—），男，博士后
基金资助:
江苏省2012年研究生创新计划项目（61172182）

Research on Three-loop Autopilot for Rolling Missile Based on Linear Quadratic Optimal Control Theory

FAN Shi-peng^1,2， LIN De-fu¹， YAO Huai-jin¹, LU Yu-long³， QI Zai-kang¹

(1.School of Aerospace Engineering，Beijing Institute of Technology，Beijing 100081，China；2.Beijing Aerospace Automatic Control Institute, Beijing 100854, China;3.Beijing Institute of Electronic System Engineering，Beijing 100854，China)

Received:2014-06-18 Revised:2014-06-18 Online:2015-07-09

摘要/Abstract

摘要： 建立了存在交叉耦合的滚转导弹动力学模型，并将通道耦合效应视为外界干扰，利用最优二次型(LQR)控制理论，提出了一种三回路驾驶仪的单输入多输出(SIMO)设计方法。分析了三回路驾驶仪的基本特点，并研究了权系数矩阵与驾驶仪性能指标之间的关系，可辅助设计者更合理地选择权系数矩阵。将考虑耦合的动力学模型视为多输入多输出(MIMO)系统，对滚转导弹控制系统进行了设计。设计结果表明：对于存在状态耦合的滚转导弹而言，以SIMO设计的三回路驾驶仪可以很好地抑制耦合的影响，与MIMO设计得到的控制律差异很小。通过对滚转导弹耦合系统的非线性数学仿真，验证了以上结论的正确性。

关键词: 飞行器控制、导航技术, 滚转导弹, 三回路驾驶仪, 最优二次型, 通道耦合

Abstract: A dynamical model including cross-coupling effects of rolling missile is built. The couplings among the channels are regarded as external interference. The linear quadratic（LQR）optimal control theory is used to propose a design method of three-loop autopilot and analyze its general features. The research on the relationship between the weight coefficient matrix and the autopilot performance could assist a designer in choosing the weight coefficient matrix. The dynamical model is perceived as multiple-input multiple-output（MIMO）system, and the corresponding control system of rolling missile is designed. The results show that the three-loop autopilot using single-channel design do well in restraining the influence of couplings in rolling missile with state couplings, which has little difference from the control law derived by MIMO design. The simulation validates the correctness of the above conclusion.

Key words: control and navigation technology of aerocraft, rolling missile, three-loop autopilot, linear quadratic regulator, channel coupling

中图分类号:

TJ765.4

范世鹏，林德福，姚怀瑾，路宇龙，祁载康. 基于最优二次型理论的滚转导弹三回路驾驶仪设计与研究[J]. 兵工学报, 2015, 36(5): 831-838.

FAN Shi-peng， LIN De-fu， YAO Huai-jin, LU Yu-long， QI Zai-kang. Research on Three-loop Autopilot for Rolling Missile Based on Linear Quadratic Optimal Control Theory[J]. Acta Armamentarii, 2015, 36(5): 831-838.

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基于最优二次型理论的滚转导弹三回路驾驶仪设计与研究

Research on Three-loop Autopilot for Rolling Missile Based on Linear Quadratic Optimal Control Theory

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