流体力学与飞行力学

导引头隔离度寄生回路对最优制导律性能的影响

  • 李富贵 ,
  • 夏群利 ,
  • 祁载康
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  • 北京理工大学 宇航学院, 北京 100081
李富贵男,博士研究生。主要研究方向:飞行器总体、制导控制。Tel:010-68911923E-mail:lfg20041079@sina.com;夏群利男,博士,副教授,博士生导师。主要研究方向:飞行器总体。Tel:010-68911923E-mail:1010@bit.edu.cn;祁载康男,硕士,教授。主要研究方向:飞行器总体、制导控制。Tel:010-68911923E-mail:qzk@bit.edu.cn

收稿日期: 2013-01-17

  修回日期: 2013-08-15

  网络出版日期: 2013-08-27

基金资助

中国博士后科学基金(2011M500008)

Effect of Seeker Disturbance Rejection Rate Parasitic Loop on Performance of Optimal Guidance Law

  • LI Fugui ,
  • XIA Qunli ,
  • QI Zaikang
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  • School of Aerospace, Beijing Institute of Technology, Beijing 100081, China

Received date: 2013-01-17

  Revised date: 2013-08-15

  Online published: 2013-08-27

摘要

为分析导引头隔离度寄生回路对最优制导律性能的影响,针对空战中目标机动主模式,应用极小值原理推导了一种贴近工程的最优制导律。根据弹上可量测信息提出了该制导律的工程应用策略,包括目标机动估计方法、剩余飞行时间估计方法、导弹和目标机动动力学时间常数装订方法等。在典型雷达平台导引头下建立了隔离度寄生回路模型,分析了隔离度传递函数的特性,研究了制导参数对寄生回路稳定性能的影响。在典型随机扰动输入下,分别在最优制导律和比例导引律制导下利用无量纲伴随方法对比分析了隔离度寄生回路对制导脱靶量的影响。仿真结果表明:最优制导律对隔离度寄生回路的影响更加敏感,即使估计信息准确,只有当隔离度小于2%时,最优制导律的脱靶量才小于比例导引律,而当估计信息存在偏差时,只有隔离度更小时,最优制导律的性能才会优于比例导引律;想要应用最优制导律改进导弹的制导性能,相比于比例导引律,必须严格控制导引头隔离度的指标以抑制隔离度寄生回路的影响。

本文引用格式

李富贵 , 夏群利 , 祁载康 . 导引头隔离度寄生回路对最优制导律性能的影响[J]. 航空学报, 2013 , 34(12) : 2658 -2667 . DOI: 10.7527/S1000-6893.2013.0359

Abstract

In order to study the effect of a seeker disturbance rejection rate parasitic loop on the performance of the optimal guidance law, a practical guidance law is obtained based on the minimum theory under the main maneuver mode of an aerial target. Engineering application strategies of the guidance law are presented in terms of the information measured by the missile, such as the target maneuver estimate strategy, time to go filter and target and missile maneuver time constant equivalent measure, etc. A model of the parasitic loop is established for a typical radar gimbaled seeker. Then its characteristics of disturbance rejection rate transfer function as well as their effect on guidance parameters are analyzed. Under typical random inputs, the miss distance is compared using the ajoint method and the nondimensional method between the optimal guidance law and proportional navigation guidance law. The simulation results show that the optimal guidance law is more sensitive to the effect of the parasitic loop. When the disturbance rejection rate is under 2%, the miss distance of the optimal guidance law may be smaller than that of the proportional navigation guidance law, even if the estimate information is significant and correct. If there is something wrong in the estimate information, when the disturbance rejection rate can be kept much smaller, the performance of the optimal guidance law is still superior to the proportional navigation guidance law. Compared with the proportional navigation guidance law, if the optimal guidance law is used to improve the performance of the missile, then the index of the disturbance rejection rate should be much stricter to reduce the effect of the parasitic loop.

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