One of the problems of automatic approach and landing is the accuracy of aircraft guidance as the aircraft flies along the ILS Beams. The system studied here can smooth the Loc data and ensure continuation of aircraft guidance in the event of a Localizer failure. This system only needs complementary speed information from an inertial sensor system in order to provide the auto-pilot with a filtered Loc signal instead of the raw signal. The final system, based on Kalman filtering, was implemented by means of a digital computer, then flight tested on the AIRBUS A. 300. B. Certification of this system with reduced operational visibility minima is expected in the Spring of 1978.

  • Supplemental Notes:
    • AGARD Conference Proceedings N220: Appl of Advances in Navigation to Guidance and Control; Guidance and Control Panel Meeting, 24th, May 10-13, 1977.
  • Corporate Authors:

    Advisory Group Aerospace Research and Development

    7 Rue Ancelle
    92 Neuilly-sur-Seine,   France 
  • Authors:
    • Irvoas, J
    • Buisson, D
    • Lloret, P
    • Lagarde, X
  • Publication Date: 1978-2

Media Info

  • Features: References;
  • Pagination: 11 p.

Subject/Index Terms

Filing Info

  • Accession Number: 00188538
  • Record Type: Publication
  • Source Agency: Engineering Index
  • Report/Paper Numbers: Conf Paper
  • Files: TRIS
  • Created Date: Feb 27 1979 12:00AM