An apparatus comprising, inter alia, gyroscope feed-back circuitry which allow scanning the rotor magnet of a gyroscope disposed in an associated guided missile system so as to increase the seeker field thereof is disclosed. A signal from the cage coil of the gyroscope having an amplitude approximating a sine function of the angular position of the spin axis of the rotor magnet portion of the gyroscope with respect to the body axis of the associated guided missile is used to generate a constant amplitude drive signal for driving the precession coil of the gyroscope. Scanning, so as to drive the rotor magnet in a predetermined scan pattern is accomplished by phase shifting the signal from the cage coil as a function of its amplitude and then driving the precession coil with the aforementioned constant amplitude drive signal which is phased- locked to the phase shifted or processed cage coil signal.

  • Supplemental Notes:
    • Filed 31 May 83 patented 11 Jun 85; Supersedes PAT-APPL-6-499 576, AD-D010 394.; This Government-owned invention available for U.S. licensing and, possibly, for foreign licensing. Copy of patent available Commissioner of Patents, Washington, DC 20231 $1.50.; Patent
  • Corporate Authors:

    Department of the Navy

    Washington, DC  United States 
  • Authors:
    • Moran, R D
  • Publication Date: 0


  • English

Media Info

  • Pagination: 6 p.

Subject/Index Terms

Filing Info

  • Accession Number: 00666738
  • Record Type: Publication
  • Source Agency: National Technical Information Service
  • Report/Paper Numbers: PAT-APPL-6-499 576; PATENT-4 522 355
  • Files: TRIS
  • Created Date: Oct 3 1994 12:00AM