Robust guidance law via integral-sliding-mode scheme

Yew Wen Liang, Chih Chiang Chen, Der Cherng Liaw, Yang Ching Feng, Chiz Chung Cheng, Chun Hone Chen

研究成果: Article

18 引文 斯高帕斯(Scopus)

摘要

A robust guidance law for missile interception was proposed by using the integral sliding mode control (ISMC) scheme. It was shown that the design possesses a remarkable feature that allows the engineer to select in advance an appropriate guidance law for the nominal system according to the interception requirements, so that the state responses of the overall uncertain system will be close to those of the nominal system. It is worth noting that the ISMC scheme forces the system states to be close to those of the RTPN0 at every time instant. Therefore, the effect of the uncertainty by using ISMC does not cumulate, which might explain why the ISMC generally requires smaller maximum control magnitude than that by uncertain or RTPN1. In addition, it is clear that, for a non-maneuvering target, the timing responses by using ISMC will agree with those via nominal or RTPN0.

原文English
頁(從 - 到)1038-1041
頁數4
期刊Journal of Guidance, Control, and Dynamics
37
發行號3
DOIs
出版狀態Published - 2014 一月 1

    指紋

All Science Journal Classification (ASJC) codes

  • Control and Systems Engineering
  • Aerospace Engineering
  • Space and Planetary Science
  • Electrical and Electronic Engineering
  • Applied Mathematics

引用此

Liang, Y. W., Chen, C. C., Liaw, D. C., Feng, Y. C., Cheng, C. C., & Chen, C. H. (2014). Robust guidance law via integral-sliding-mode scheme. Journal of Guidance, Control, and Dynamics, 37(3), 1038-1041. https://doi.org/10.2514/1.60669