Actuator control delay and delay compensation time of spinning missile

被引：1

作者：

Lian J. ^{[1
]}

Yao X. ^{[1
]}

Guo Z. ^{[1
]}

机构：

[1] School of Aerospace Engineering, Beijing Institute of Technology, Beijing

来源：

Xi Tong Gong Cheng Yu Dian Zi Ji Shu/Systems Engineering and Electronics | 2018年 / 40卷 / 06期

关键词：

Actuator delay compensation time; Lag angle; Lag compensation; Missile control; Spinning missile;

D O I：

10.3969/j.issn.1001-506X.2018.06.18

中图分类号：

学科分类号：

摘要：

This paper is mainly about the control delay of dual-channel spinning missiles with the canard deployment of "+". The formula of the lag angle of control is derived by the control method built by the control force of the actuator. The formation and transmission of the command are analyzed from the system composition, and two reasons for the formation of the lag are obtained. One is the input command signal delay of the actuator induced by the geomagnetic gyro and the missile-borne computer. The other is the command response signal delay induced by the actuator itself. The delay compensation time of the input command signal and command response signal, which is calculated by the formula of lag angle and the swept-sine method, is a time constant. An algorithm of compensation, which is based on the constant of delay compensation time and roll speed, has been verified by experiment. The results show that this method has a good compensation effect. © 2018, Editorial Office of Systems Engineering and Electronics. All right reserved.

引用

页码：1318 / 1324

页数：6

共 27 条

[1]

Fan S.P., Wu G., Sun Y., Et al., Analysis of control coupling characteristic and forward decoupling technique for rolling missile, Systems Engineering and Electronics, 39, 2, pp. 398-403, (2017)

[2]

Philippe W., Spilios T., Yannick M., Flight dynamics properties of 155 mm spin-stabilized projectiles analyzed in different body frames, Proc.of the Atmospheric Flight Mechanics Conference, (2010)

[3]

Li K.Y., Yang S.X., Zhao L.Y., Stability of spinning missiles with an acceleration autopilot, Journal of Guidance, Control and Dynamics, 34, 1, pp. 278-283, (2011)

[4]

Yan X.Y., Yang S.X., Xiong F.F., Stability limits of spinning missile with attitude autopilot, Journal of Guidance, Control and Dynamics, 35, 3, pp. 774-786, (2012)

[5]

Song T., Lin D.F., Wei Z.J., Et al., Research on decoupling algorithm for control coupling of a spinning missile autopilot, Acta Armamentarii, 34, 4, pp. 454-460, (2014)

[6]

Richard L., Analysis of control and guidance of rolling missile with a single plane of control fins, Proc.of the AIAA Guidance, Navigation, and Control Conference, (2010)

[7]

Zhang W., Xia L.Y., Fu H.C., Analytical decoupling control of a generic hypersonic vehicle based on internal model control, Proc.of the IEEE 36th Chinese Control Conference, pp. 6163-6168, (2017)

[8]

Duan Z.S., Huang L., Yang J.Y., Et al., On decoupled or coupled control of bank-to-turn missiles, Science China Information Sciences, 58, 3, pp. 1-13, (2015)

[9]

Fan Y.H., Wu X.F., Xu H.Y., Et al., Design of lateral control system for a hypersonic cruise missile, Proc.of the 21st AIAA International Space Planes and Hypersonics Technologies Conference, (2017)

[10]

Joon H.Y., Seong H.S., Jin W.H., Et al., Singular perturbationlike approach to compensation of actuator dynamics effect in missile control, IEEE Trans.on Aerospace and Electronic Systems, 50, 4, pp. 2417-2439, (2014)

← 1 2 3 →