GB930961A - Guidance system - Google Patents

Abstract

930,961. Automatic steering control. Mc- DONNELL AIRCRAFT CORPORATION. April 11, 1961, No. 12981/61. Class 38 (4). [Also in Groups XXI and XL (c)] In a system for guiding a missile, detectors spaced round the missile respond to a beam of energy defining a path for the missile and control appropriate thrust producing means spaced round the missile so as to correct deviations of the missile from the beam by transverse movements without turning. In Fig. 2 a rocket missile launching tube 54 is aimed at a target with the aid of a sighting device 56. After firing, the missile is above a trough-shaped beam of infra-red light 40 emanating from a projector 39. A number of photo-cells 19, Fig. 1, are mounted on fins 14 which move outwards after launching, and when the missile descends into the light beam due to gravity, one of the cells responds to the light and detonates a propellant charge 18 in a recess located at a corresponding position round the circumference of the missile. The jet side-thrust thus produced together with similar thrusts produced by other photo-cell/charge combinations as the missile rolls, maintain the missile within the trough during its short flight. Charges 18 are located approximately at the centre of gravity of the missile to avoid turning effects. Mounting of the photo-cells directly on the missile without fins is referred to. In a modification each charge is replaced by a longitudinal row of charges, and pairs of charges in each row, equally spaced from the centre of gravity of the missile are available for detonation so that a flight of longer duration may be controlled. In another modification the charges are replaced by motor-operated control surfaces. Maintaining the missile within a beam of annular cross-section or maintaining it in the radiation instead of outside are referred to. Use of a radio beam is also referred to.