Analysis of control coupling characteristic and forward decoupling technique for rolling missile

被引：5

作者：

Fan S. ^{[1
]}

Wu G. ^{[1
]}

Sun Y. ^{[1
]}

Chen Y. ^{[1
]}

Li L. ^{[1
]}

机构：

[1] Beijing Aerospace Automatic Control Institute, Beijing

来源：

Xi Tong Gong Cheng Yu Dian Zi Ji Shu/Systems Engineering and Electronics | 2017年 / 39卷 / 02期

关键词：

Control coupling; Control efficiency; Decoupling technique; Rolling missile;

D O I：

10.3969/j.issn.1001-506X.2017.02.25

中图分类号：

学科分类号：

摘要：

Control coupling is a special problem of rolling missiles. Firstly, the transfer function matrix equivalent in non-spinning frame is derived, which explains the principle and characteristics of control coupling. Secondly, a function relationship between control efficiency and relevant parameters, such as dimensionless spinning rate and damping ratio, is presented. And then, two decoupling methods are compared and studied. The condition of physically realization for dynamically compensation is given. It is clearly that static decoupling of setting a lead angle which is widely used in engineering is the steady state of the feedforward dynamically compensation in essence. However, frequency of periodic command would influence on static decoupling but not dynamically compensation. In addition, dynamically compensation could set two zeros to improve the dynamic performance. Finally, the conclusions above are demonstrated through the mathematical simulation. © 2017, Editorial Office of Systems Engineering and Electronics. All right reserved.

引用

页码：398 / 403

页数：5

共 17 条

[1]

Zhu D.L., Tang S.J., Guo J., Et al., Flight stability of a dual-spin projectile with canards, Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering, 229, 4, pp. 1-14, (2014)

[2]

Yuan T.B., Liu X.J., Qin Z.Z., Dynamic and control of spinning ballistic missile, Journal of Astronautics, 27, 2, pp. 217-221, (2006)

[3]

Creagh M.A., Mee D.J., Attitude guidance for spinning vehicles with independent pitch and yaw control, Journal of Guidance, Control, and Dynamics, 33, 3, pp. 915-922, (2010)

[4]

Lestage R., Analysis of control and guidance of rolling missile with a single plane of control fins, Proc. of the AIAA Guidance, Navigation, and Control Conference and Exhibit, (2000)

[5]

Zhong Y.W., Wang L.M., Fu J., Hopf bifurcation analysis of nonlinear angular motion stability of projectile, Acta Armamentarii, 36, 7, pp. 1195-1202, (2015)

[6]

Vardulakis A.I.G., Internal stabilization and decoupling in linear multivariable systems by unity output feedback compensation, IEEE Trans. on Automatic Control, 32, 8, pp. 735-739, (1987)

[7]

Yan X.Y., Zhang C., Yang S.X., Decoupling technique for a class of rolling missile, Journal of Ballistics, 21, 4, pp. 17-21, (2009)

[8]

Yan X.Y., Yang S.X., Zhang C., Coning motion of spinning missiles induced by the rate loop, Journal of Guidance Control and Dynamics, 33, 5, pp. 1490-1499, (2010)

[9]

Yan X.Y., Yang S.X., Xiong F.F., Stability limits of spinning missiles with attitude autopilot, Journal of Guidance Control and Dynamics, 34, 1, pp. 278-283, (2011)

[10]

Li K.Y., Yang S.X., Zhao L.Y., Stability of spinning missiles with an acceleration autopilot, Journal of Guidance Control and Dynamics, 35, 3, pp. 774-786, (2012)

← 1 2 →