A Disturbance Observer-based Inhibition Method for Disturbance Rejection Rate of Seeker

XU Jiao;WANG Jiang;SONG Tao;HU Kuan-rong

Acta Armamentarii ›› 2014, Vol. 35 ›› Issue (11) : 1790-1798. DOI: 10.3969/j.issn.1000-1093.2014.11.009
Paper

A Disturbance Observer-based Inhibition Method for Disturbance Rejection Rate of Seeker

  • XU Jiao1, WANG Jiang1, SONG Tao1, HU Kuan-rong2
Author information +
History +

Abstract

The disturbance rejection rate (DRR) of seeker has the effect on the output accuracy of seeker and the guidance performance.An online inhibition method based on disturbance observer is proposed for the problems of the guidance precision of missile caused by DRR. The errors of seeker models, the output frequencyof detector and the effect of measurement noise on DRR inhibition are presented. The result shows that the spring torque and the damping torque are the main factors of the DRR generation, and the missile guidance precision would be reduced. The online inhibition method based on disturbance observer can inhibit DRR effectively; but the errors of seeker models, the output frequency of the detector and the measurement noise reduce the inhibition effects to some extent.

Key words

ordnance science and technology / disturbance rejection rate / disturbance torque / miss distance / disturbance observer / online inhibition

Cite this article

Download Citations
XU Jiao, WANG Jiang, SONG Tao, HU Kuan-rong. A Disturbance Observer-based Inhibition Method for Disturbance Rejection Rate of Seeker. Acta Armamentarii. 2014, 35(11): 1790-1798 https://doi.org/10.3969/j.issn.1000-1093.2014.11.009

References

[1] ZipfelP H . Modeling and simulation of aerospace vehicle dyna-mics[M].Florida: American Institute of Aeronautics and Astronautics, 2000.
[2] TaylorJ H, Price C F. Direct statistical analysis of missile gui-dancesystem via CADET[R]. Massachusetts: Analytic Sciences Corporation, 1976.
[3] KwonY S,Hwang H Y,Choi Y S. Stabilization loop design on direct drive gimbaled platform with low stiffness and heavy inertia[C]∥ International Conference on Control, Automation and Systems 2007. Seoul, Korea:IEEE,2007:320-325.
[4] 穆虹. 防空导弹雷达导引头设计[M]. 北京: 宇航出版社, 1996.
MU Hong. Design of air defense missile seeker[M]. Beijing: China Astronautic Publishing House, 1996.(in Chinese)
[5] BhattacharyaR N, Tao T V, Sadhu S. Control structures and properties of missile seekers[J]. Journal of the Institution of Engineers: Electrical Engineering Division, 2002, 82(3): 253-261.
[6] 朱华征,范大鹏,马东玺,等. 导引头伺服系统隔离度与测试[J]. 光学精密工程,2009, 17(8): 1993-1998.
ZHU Hua-zheng, FAN Da-peng, MA Dong-xi, et al. Disturbance isolation index of seeker servo system and its test[J]. Optics and Precision Engineering, 2009,17(8):1993-1998.(in Chinese)
[7] 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[J]. 宇航学报, 2013, 34(8): 1072-1077.
LI Fu-gui, XIA Qun-li, CUI Xiao-xi, et al. Effect of seeker disturbance rejection rate parasitic loop on line of sight rate extraction[J]. Journal of Astronautics, 2013,34(8): 1072-1077.(in Chinese)
[8] KwonY S,Hwang H Y,Choi Y S. Stabilization loop design on direct drive gim-baled platform with low stiffness and heavy inertia[C]∥ International Conference on Control, Automation and Systems.Seoul Korea:IEEE,2007.
[9] 杜运理,夏群利,祁载康. 导引头隔离度相位滞后对寄生回路稳定性影响研究[J]. 兵工学报,2011, 32(1): 28-32.
DU Yun-li, XIA Qun-li, QI Zai-kang. Research on effect of seeker disturbance rejection rate with phase lag on stability of parasitical loop[J]. Acta Armamentarii, 2011, 32 (1) : 28-32.(in Chinese)
[10] MastenM K. Applications of control theory to design of line-of-sight stabilization system[C]∥American Control Conference.Boston, MA:IEEE, 1985:1219-1222. .
[11] LinC L,Hsiao Y H. Adaptive feedforward control for disturbance torque rejection in seeker stabilizing loop [J]. IEEE Transactions on Control Systems Technology, 2001, 9(1): 108-121.
[12] ChuZ Y,Sun F C,Cui J. Disturbance observer-based robust control of free-floating space manipulators[J]. IEEE Systems Journal, 2008, 2(1): 114-119.
[13] ChladnyR R., Koch C R. Flatness-based tracking of an electromechanical variable valve timing actuator with disturbance observer feedforward compensation[J]. IEEE Transactions on Control System Technology, 2008, 16(4): 652-663.
[14] YangZ J, Tsubakihara H, Kanae S, et al. A novel robust nonlinear motion controller with disturbance observer[J]. IEEE Transactions on Control Systems Technology, 2008, 16(1):137-147.
[15] NeslineF W, Zarchan P. Radome induced miss distance in aerodynamically controlled homing missiles,AIAA 84-1845[R]. Reston ,VA:AIAA, 1984.
[16] DwivdiP N, Tiwari S N, Bhattacharya A. A ZEM based effective integrated estimation and guidance of interceptors in terminal phase[C]∥AIAA Conference on Guidance, Navigation ,and Control. Toronto, Ontario Canada:AIAA, 2010: 6669-6693.
[17] ZarchanP. Tactical and strategic missile guidance[M]. 5th ed. Virginia: American Institute of Aeronautics and Astronautics Inc, 2007.
[18] 蔡毅. 光电精确制导武器[M]. 北京:兵器工业出版社, 2013.
CAI Yi. Photoelectric precision guided weapon[M].Beijing: Publishing House of Ordnance Industry, 2013.(in Chinese)

482

Accesses

0

Citation

Detail

Sections
Recommended

/