• DocumentCode
    550533
  • Title

    Finite time convergent sliding-mode guidance law with impact angle constraint

  • Author

    Zhang Yunxi ; Jiao Gangling ; Sun Mingwei ; Chen Zengqiang

  • Author_Institution
    Dept. of Autom., Nankai Univ., Tianjin, China
  • fYear
    2011
  • fDate
    22-24 July 2011
  • Firstpage
    2597
  • Lastpage
    2601
  • Abstract
    Based on the finite time convergence stability theory and the variable structure control, a finite time convergent sliding-mode guidance law with terminal impact angle constraint is presented. The analysis manifests that the guidance system is convergent. It is proved that, before the final time of the guidance process, the line-of-sight rate will converge to zero in finite time and the terminal impact angle will meet the requirement. Finally, the simulation results show that the guidance law is effective.
  • Keywords
    aerospace control; military systems; missile guidance; stability; variable structure systems; finite time convergence stability theory; finite time convergent sliding mode guidance law; impact angle constraint; line-of-sight rate; stability theory; terminal impact angle; variable structure control; Convergence; Navigation; Optimized production technology; Sliding mode control; Stability analysis; Sun; Switches; Finite time convergence; Guidance law; Sliding-mode control; Terminal impact angle;
  • fLanguage
    English
  • Publisher
    ieee
  • Conference_Titel
    Control Conference (CCC), 2011 30th Chinese
  • Conference_Location
    Yantai
  • ISSN
    1934-1768
  • Print_ISBN
    978-1-4577-0677-6
  • Electronic_ISBN
    1934-1768
  • Type

    conf

  • Filename
    6000872