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弹箭与制导学报 >

2010 , Vol. 30 >Issue 2: 1 - 3,70

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2010.02.067

导弹与制导技术

一种分析横向静不稳定导弹飞行攻角边界值的方法

  • 李友年 ,
  • 陈星阳 ,
  • 杨育荣
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  • 中国空空导弹研究院,河南洛阳 471009

李友年（1964－）,男,山东人,研究员,硕士,研究方向：导弹控制系统设计。

收稿日期: 2009-04-10

  网络出版日期: 2025-05-28

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An Approach of Lateral Static Unstable Missile's Angle of Attack Boundary Analysis

  • LI Younian ,
  • CHEN Xingyang ,
  • YANG Yurong
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  • China Airborne Missile Academy, Henan Luoyang 471009, China

Received date: 2009-04-10

  Online published: 2025-05-28

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摘要

工程设计初期,控制系统设计人员需要对气动特性进行快速分析,判定导弹能否满足制导控制系统的性能要求。文中以常见的几种横滚控制结构为基础,分析了横向静稳定性对控制系统的影响,并给出了控制系统最大稳定边界的计算方法。该方法物理概念清楚,计算简单,经数字仿真验证,所得到的飞行攻角边界值准确,可用于对气动外形和控制系统性能的评估。

关键词： 自动驾驶仪; 通道耦合; 横向静不稳定性; 空间稳定性

本文引用格式

李友年 , 陈星阳 , 杨育荣 . 一种分析横向静不稳定导弹飞行攻角边界值的方法[J]. 弹箭与制导学报, 2010 , 30(2) : 1 -3,70 . DOI: 10.15892/j.cnki.djzdxb.2010.02.067

Abstract

During initial phase of engineering design, control system designers should analyze pneumatic features to quickly judge if guidance and control system performance can meet the requirements. Based on some kinds of raw control structure, in the paper, the influences of lateral static stabilization were analyzed, and calculation method of the maximum stable range was given. Its physical concept is clear and easy to calculate. The simulation result shows the flight angle of attack boundary value can be used for evaluating aerodynamic outline and estimating the guidance and control system's performance.

Key words： autopilot; channels coupling; lateral static instability; space stability

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参考文献

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Nesline William F, Zarchan Paul . Why moder controlers can go unstable in practice[J]. Journal of Guidance, Control and Dynamics , 1984 , 7 ( 4 ): 495 - 500 .
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钱杏芳, 林瑞雄, 赵亚男 . 导弹飞行力学[M]. 北京 : 北京理工大学出版社 , 2000 : 28 - 64 .
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陈佳实 . 导弹制导控制系统分析与设计[M]. 北京 : 宇航出版社 , 1989 : 50 - 60 .
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Christian Tournes, Yuri Shtessel, Ilya Shkolnikow . Autopilot for missiles steered by aerodynamic lift and divert thrusters using nonlinear dynamic sliding manifolds, ΑΙΑΑ - 2005 6382[R]. San Francisco, California: AIAA Guidance, Navigation, and Control Conference and Exhibit , 2005 .
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Rui Hirokawa, Koichi Sato . Autopilot design for a missile with reaction-jet using coefficient diagram method, AIAA-2001-4162[R]. 2001 .
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