English  |  正體中文  |  简体中文  |  全文筆數/總筆數 : 49433/84388 (59%)
造訪人次 : 7446041      線上人數 : 91
RC Version 7.0 © Powered By DSPACE, MIT. Enhanced by NTU Library & TKU Library IR team.
搜尋範圍 查詢小技巧:
  • 您可在西文檢索詞彙前後加上"雙引號",以獲取較精準的檢索結果
  • 若欲以作者姓名搜尋,建議至進階搜尋限定作者欄位,可獲得較完整資料
  • 進階搜尋
    請使用永久網址來引用或連結此文件: http://tkuir.lib.tku.edu.tw:8080/dspace/handle/987654321/106309

    題名: SDRE Missile Guidance Law
    作者: Tyan, Feng;Shen, Jeng-fu
    關鍵詞: State dependent Riccati equation;guidance law
    日期: 2010-06-09
    上傳時間: 2016-04-22 13:45:37 (UTC+8)
    摘要: In this work, a state dependent Riccati equation (SDRE) missile guidance is formulated and studied. With the aid of a line of sight (LOS) fixed coordinate, the order of the system equations describing the three dimensional missile guidance problem is reduced to three. In addtion, the computational effort of solving SDRE is less than the usual guidance formulations which often have the order greater than three. Three different state dependent coefficient forms are proposed and compared under the consideration of optimality and implementation. For more constructive design, a simple shift of variable is also introduced to achieve better performance. From the results of numerical experiments, we also find that the proposed SRRE guidance law outperforms the conventional PPN guidance (for navigation constant equals 5) in the sense of time but at the cost of energy.
    關聯: 2010 8th IEEE International Conference on Control and Automation, pp.866-870
    DOI: 10.1109/ICCA.2010.5524364
    顯示於類別:[航空太空工程學系暨研究所] 期刊論文


    檔案 描述 大小格式瀏覽次數



    DSpace Software Copyright © 2002-2004  MIT &  Hewlett-Packard  /   Enhanced by   NTU Library & TKU Library IR teams. Copyright ©   - 回饋