• DocumentCode
    3334581
  • Title

    Hypersonic guidance via the state-dependent Riccati equation control method

  • Author

    Cloutier, James R. ; Zipfe, Peter H.

  • Author_Institution
    Air Force Armament Lab., Eglin AFB, FL, USA
  • Volume
    1
  • fYear
    1999
  • fDate
    1999
  • Firstpage
    219
  • Abstract
    In this paper, the state-dependent Riccati equation (SDRE) control method is used to design a guidance law for the midcourse phase of flight of a hypersonic vehicle. The guidance law converts flight path angle and heading angle commands to angle of attack and bank angle commands for input to an attitude autopilot
  • Keywords
    Riccati equations; aerospace control; military aircraft; SDRE control method; angle of attack; attitude autopilot; bank angle commands; flight path angle; guidance law; heading angle commands; hypersonic guidance; hypersonic vehicle flight; midcourse phase; state-dependent Riccati equation; Acceleration; Aerodynamics; Atmosphere; Force control; Navigation; Pressure control; Riccati equations; Smoothing methods; Space vehicles; Vehicle dynamics;
  • fLanguage
    English
  • Publisher
    ieee
  • Conference_Titel
    Control Applications, 1999. Proceedings of the 1999 IEEE International Conference on
  • Conference_Location
    Kohala Coast, HI
  • Print_ISBN
    0-7803-5446-X
  • Type

    conf

  • DOI
    10.1109/CCA.1999.806179
  • Filename
    806179
    • Link To Document
    https://search.isc.ac/dl/search/defaultta.aspx?DTC=49&DC=3334581