Improved pseudo state method for aircraft controller design

Chin E. Lin, Jieh Shian Young

研究成果: Paper

5 引文 斯高帕斯(Scopus)

摘要

An improved method for compensator design in aircraft control applications is presented. A design technique using a pseudo-state equation together with an enlarged system is discussed. This method improves the redesign procedure when the compensator characteristics cannot meet the required specifications. The theoretical basis of the proposed method is investigated, and an algorithm is developed. To prove the effectiveness of the pseudo-state method, an example of an aircraft controller for landing approach is discussed and tested. The simulation results show that the redesign efforts are reduced, and the characteristics of the designed compensators are improved.

原文English
頁面128-133
頁數6
出版狀態Published - 1989 十二月 1
事件Proceedings of the 1989 American Control Conference - Pittsburgh, PA, USA
持續時間: 1989 六月 211989 六月 23

Other

OtherProceedings of the 1989 American Control Conference
城市Pittsburgh, PA, USA
期間89-06-2189-06-23

    指紋

All Science Journal Classification (ASJC) codes

  • Engineering(all)

引用此

Lin, C. E., & Young, J. S. (1989). Improved pseudo state method for aircraft controller design. 128-133. 論文發表於 Proceedings of the 1989 American Control Conference, Pittsburgh, PA, USA, .