Fluid Mechanics and Flight Mechanics

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

  • LI Fugui ,
  • XIA Qunli ,
  • QI Zaikang
Expand
  • 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

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.

Cite this article

LI Fugui , XIA Qunli , QI Zaikang . Effect of Seeker Disturbance Rejection Rate Parasitic Loop on Performance of Optimal Guidance Law[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2013 , 34(12) : 2658 -2667 . DOI: 10.7527/S1000-6893.2013.0359

References

[1] Zhao M Y, Wei M Y. Finite time stable variable structure guidance law with double closed-loop filters. Acta Aeronautica et Astronautica Sinica, 2010, 31(8): 1629-1635. (in Chinese) 赵明元, 魏明英. 带有双闭环滤波器的有限时间稳定变结构制导律. 航空学报, 2010, 31(8): 1629-1635.

[2] Fan H T, Yang J, Zhu X P. Research on beam stable technology of phased array radar seeker. Acta Aeronautica et Astronautica Sinica, 2013, 34(2): 387-392. (in Chinese) 樊会涛, 杨军, 朱学平. 相控阵雷达导引头波束稳定技术研究. 航空学报, 2013, 34(2): 387-392.

[3] Zarchan P. Tactical and strategic missile guidance fourth edition. Virginia: Astronautics and Aeronautics, Inc, 2002: 145-161.

[4] Ryoo C K, Cho H J, Tahk M J. Optimal guidance laws with terminal impact angle constraint. Journal of Guidance, Control and Dynamics, 2005, 11(4): 724-732.

[5] Hexner G, Pila A. A practical stochastic optimal guidance law for a bounded acceleration missile. AIAA Guidance Navigation and Control Conference and Exhibit, 2010: 1-23.

[6] Liu D W, Xia Q L, Cui Y Y, et al. Generalized trajectory shaping guidance law with both impact position and angle constrains. Journal of Beijing Institute of Technology, 2011, 31(12): 1406-1413. (in Chinese) 刘大卫, 夏群利, 崔莹莹, 等. 具有终端位置和角度约束的广义弹道成型制导律. 北京理工大学学报, 2011, 31(12): 1406-1413.

[7] Wang X H, Zhang M L. Researching and accomplishing for homing missile attacking maneuvering target. Acta Aeronautica et Astronautica Sinica, 2000, 21(1): 30-33. (in Chinese) 王小虎, 张明廉. 自寻的导弹攻击机动目标的最优制导规律的研究及实现. 航空学报, 2000, 21(1): 30-33.

[8] Hexner G, Weiss H. Temporal multiple model estimator for a maneuvering target. AIAA Guidance Navigation and Control Conference and Exhibit, 2008: 1-26.

[9] Tahk M J, Ryoo C K, Cho H J. Recursive time-to-go estimation for homing guidance missiles. IEEE Transactions on Aerospace and Electronic Systems, 2002, 38(1): 13-24.

[10] Whang I H, Ra W S. Time-to-go estimator for missiles guided by BPNG. International Conference on Control, Automation and Systems, 2008: 463-467.

[11] Qi Z K, Xia Q L. Guided weapon control system. Beijing: Beijing Institute of Technology Press, 2004: 308-352.

[12] Li F G, Xia Q L, Qi Z K, et al. Effect of parasitic loop on strap-down seeker and compensated with identification method. Systems Engineering and Electronics, 2013, 35(8): 73-78. (in Chinese) 李富贵, 夏群利, 祁载康, 等. 全捷联导引头寄生回路影响与辨识校正. 系统工程与电子技术, 2013, 35(8): 73-78.

[13] Li F G, Xia Q L, Cui X X, et al. Effect of seeker disturbance rejection rate parasitic loop on line of sight rate extraction. Journal of Astronautics, 2013, 34(7): 1-6. (in Chinese) 李富贵, 夏群利, 崔晓曦, 等. 导引头隔离度寄生回路对视线角速度提取的影响. 宇航学报, 2013, 34(7): 1-6.

[14] Xu P, Wang W, Lin D F. Effect of seeker isolation on guidance and control of terminal guided projectile. Journal of Ballistics, 2012, 24(1): 17-22.(in Chinese) 徐平, 王伟, 林德福. 导引头隔离度对末制导炮弹制导控制的影响. 弹道学报, 2012, 24(1): 17-22.

[15] Spencer A, Moore W. Design trade-offs for homing missiles. AIAA SDIO Annual Interceptor Technology Conference, 1992: 1-20.

[16] Nesline F W, Zarchan P. A new look at classical vs modern homing missile guidance. Journal of Guidance and Control, 1981, 1(4): 78-85.

Outlines

/