Method and apparatus for automatically steering a missile

Abstract

Abstract 958, 415. Automatic steering of missiles. GENERAL DYNAMICS CORPORATION. Aug. 2, 1961, No. 28036/61. Heading G3R. In a system for automatically steering a missile towards a target, the missile is rolled continuously and a pair of oppositely disposed fixed incidence retractable wings are extended from the sides of the missile for such times as are necessary to correct heading and pitch. In Fig. 2 a Cassegrain telescope 17, 18 forms part of a gyro rotor having a permanent magnet 25 rotated by a pair of stator coils energized alternately by a magnetically operated switch (not shown) responsive to rotation of the permanent magnet. The gyro stabilized telescope is mounted in the nose of a missile having a window 24 transparent to radiation, e.g. infra-red, from a target, so that an image projected through a disc 21 having alternate transparent and opaque sectors and rotating with the rotor, produces, from a photo-cell 22, electric pulses on deviation of the telescope axis from the direction of the target. The pulses produced are applied through a transistor amplifier-demodulator, having automatic gain control, so that a coil 27 is energized to precess the gyroscope and bring the telescope into alignment with the target. A loud speaker is operated by the error signal so that it is known when the target has been acquired. The error signal applied to precess the gyro, together with a signal, representing the position of the gyro rotor relative to the missile, produced in a coil 28 by the rotor magnet, is applied to a demodulator the output of which controls an electromagnetically operated bleed valve controlling a hot gas fluid pressure jack 35, Fig. 11, to extend a pair of fixed angle of incidence wings 34 on each side at the rear end of the missile during appropriate periods of each roll cycle to turn the missile towards the target. The continuous roll of the missile is produced by canted nozzles or fins. An external battery is used to bring the gyro up to speed before launching. Hot gas for the control system is produced by solid propellant ignited at launching.

Inventors

• 👤 John Mcellroy Guthrie
• 👤 Casimir John Bonk
• 👤 Clark Ernst Allardt
• 👤 Glen William Ashley
• 👤 George Emmett Burkheimer
• 👤 Donald Irving Smith

Bibliographic Details