[an error occurred while processing this directive] [an error occurred while processing this directive] [an error occurred while processing this directive]
[an error occurred while processing this directive]

弹箭与制导学报 >

2024 , Vol. 44 >Issue 1: 34 - 40

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2024.01.006

新型过载驾驶仪滚转弹制导系统稳定性研究

  • 李涛 1 ,
  • 付博 1 ,
  • 王齐双 1 ,
  • 段辰璐 1 ,
  • 林时尧 2
展开
  • 1 西安现代控制技术研究所,陕西 西安 710065
  • 2 中国兵器科学研究院,北京 100089

李涛(1997—),男,助理工程师,硕士研究生,研究方向:飞行器总体设计。

收稿日期: 2023-03-06

  网络出版日期: 2024-12-28

基金资助

国家自然科学基金项目(61827901)

收起

Stability Study on the New Overload Autopilot of Rolling Missile Guidance System

  • LI Tao 1 ,
  • FU Bo 1 ,
  • WANG Qishuang 1 ,
  • DUAN Chenlu 1 ,
  • LIN Shiyao 2
Expand
  • 1 Xi’an Modern Control Technology Research Institute,Xi’an 710065,Shaanxi,China
  • 2 Ordnance Science and Research Academy of China,Beijing 100089,China

Received date: 2023-03-06

  Online published: 2024-12-28

Fold

摘要

针对平台式图像导引头实际应用中的隔离度寄生回路问题,基于新型过载驾驶仪开展了滚转弹锥形运动的动态稳定性研究。根据滚转弹体的线性动力学模型,引入加速度反馈增稳的新型过载驾驶仪,构建了考虑平台图像导引头隔离度寄生回路的滚转弹体制导系统模型,推导了新型过载驾驶仪滚转弹制导系统的动态稳定性条件。分析了隔离度、舵机总延迟角等重要参数对包含隔离度寄生回路的滚转弹体动态稳定域的影响。研究表明:滚转效应、寄生效应与控制指令延迟是导致驾驶仪参数设计稳定域减小的主要因素,制导系统设计参数应远离稳定性边界从而提升锥形运动稳定性。

关键词： 平台图像导引头; 隔离度寄生回路; 过载驾驶仪; 锥形运动稳定性

本文引用格式

李涛 , 付博 , 王齐双 , 段辰璐 , 林时尧 . 新型过载驾驶仪滚转弹制导系统稳定性研究[J]. 弹箭与制导学报, 2024 , 44(1) : 34 -40 . DOI: 10.15892/j.cnki.djzdxb.2024.01.006

Abstract

To solve the problem of disturbance rejection rate parasitic loop (DRRPL) in the platform image seeker, the coning motion stability of rolling missile is studied based on a new overload autopilot. First, the linear dynamic model of rolling missile is deduced and simplified. And then, based on a new three-loop autopilot with an acceleration feedback augmentation loop as the inner loop, the rolling missile guidance system model considering the DRRPL of image seeker is constructed, and the dynamic stability conditions of the proportional navigation/new overload autopilot guidance system with DRRPL are deduced. Besides, the effects of DRRPL, rotational speed and total delay angle of steering gear on the dynamic stability region of rolling missile are analyzed. Simulations are carried out to demonstrate that roll effect, parasitic effect and control instruction delay are the main factors leading to the decrease of stability region of autopilot parameter. In addition, the design parameters of the guidance system should be far away from the stability boundary to improve the stability of coning motion.

Key words： platform imaging seeker; disturbance rejection rate parasitic loop; overload autopilot; coning motion stability

[an error occurred while processing this directive]

参考文献

原文顺序 | 文献年度倒序 | 文中引用次数倒序
[1]
王握文, 张照星. “深度科技化”带来战争新形态[N]. 解放军报, 2021-08-13( 11).

WANG W W, ZHANG Z X. “Deep science and technology” brings new forms of war[N]. PLA Daily, 2021-08-13( 11).

[2]
胡阳旭, 沈卫. 2018年国外陆军武器装备与技术发展综述[J]. 国防科技工业, 2018(12): 60-62.

HU Y X, SHEN W. A review of weapons, equipment and technology development of foreign land forces in 2018[J]. National Defense Technology Industry, 2018(12): 60-62.

[3]
WANG H, LIN D F, CHENG Z, et al. Optimal guidance of extended trajectory shaping[J]. Chinese Journal of Aeronautics, 2014, 27(5): 1259-1272.

[4]
孙一博, 孟秀云. 滑翔飞行器多投放条件下飞行性能优化[J]. 兵工学报, 2021, 42(4): 781-797.

DOI

SUN Y B, MENG X Y. Flight performance aptimization of glide vehicles under multiple launch conditions[J]. Acta Armamentarii, 2021, 42(4): 781-797.

DOI

[5]
李清源. 美国定向能激光武器的发展及其对弹道导弹的威胁[J]. 导弹与航天运载技术, 2000(2): 44-53.

LI Q Y. Development of directed energy laser weapon in US and its threat to ballistic missile[J]. Missiles and Space Vehicles, 2000(2): 44-53.

[6]
NICOLAIDES J D. On the free flight motion of missiles having slight configurational asymmetries: BRL-858[R]. Washington: USAARDC, 1953.

[7]
THOMSON W T. Introduction to space dynamics[J]. Physics Today, 1962, 15(9): 70-78.

[8]
MURPHY C H. Some special cases of spin yaw lock-in[J]. Journal of Guidance, Control, and Dynamics, 1989, 12(6): 771-776.

[9]
MOROTE J, LIAÑO G. Stability analysis and flight trials of a clipped wrap around fin configuration: AIAA 2004-5055[R]. Reston: AIAA, 2013.

[10]
MAO X, YANG S, XU Y. Coning motion stability of wrap around fin rockets[J]. Science in China Series E: Technological Sciences, 2007, 50(3): 343-350.

[11]
CARLUCCI D E, JACOBSON S S. Exterior Ballistics[M]. Oxford: Taylor & Francis Group, 2014: 45-56.

[12]
MOROTE J, LIANO G. Flight dynamics of unguided rockets with free rolling wrap around tail fins[J]. Journal of Spacecraft and Rockets, 2006, 43(6): 1422-1423.

[13]
JAVIER L, TERRY N. Coning motion control of a blunt-nose projectile using small deployable strakes[C]// AIAA. Proceedings of the 25th AIAA Applied Aerodynamics Conference. Reston: AIAA, 2007: 196-219.

[14]
PLATUS D H. Angle-of-attack control of spinning missiles[J]. Journal of Spacecraft and Rockets. 1975, 12(4): 228-234.

[15]
YAN X, YANG S, ZHANG C. Coning motion of spinning missiles induced by the rate loop[J]. Journal of Guidance, Control, and Dynamics, 2010, 33(5): 1490-1499.

[16]
YAN X, YANG S, XIONG F. Stability limits of spinning missiles with attitude autopilot[J]. Journal of Guidance, Control, and Dynamics, 2011, 34(1): 278-283.

[17]
LI K, YANG S, ZHAO L. Stability of spinning missiles with an acceleration autopilot[J]. Journal of Guidance, Control, and Dynamics, 2012, 35(3): 774-786.

[18]
LI K, YANG S, ZHAO L. Three loop autopilot of spinning missiles[J]. Journal of Aerospace Engineering, 2014, 228(7): 1195-1201.

[19]
ZHENG D, LIN D, XU X, et al. Dynamic stability of rolling missile with proportional navigation and PI autopilot considering parasitic radome loop[J]. Aerospace Science and Technology, 2017, 67: 41-48.

[20]
TIAN S, LIN D, WANG J, et al. Dynamic stability of rolling missiles with angle-of-attack feedback three-loop autopilot considering parasitic effect[J]. Aerospace Science and Technology, 2017, 71: 592-602.

[21]
FRANK E. On the zeros of polynomials with complex coefficients[J]. Bulletin of the American Mathematical Society, 1946, 52(2): 144-157.

Options
文章导航

/

〈 〉

[an error occurred while processing this directive]