GB959897A - Ejection of airmen from aircraft - Google Patents

Abstract

959,897. Aircraft ejection seats. J. MARTIN. March 30, 1962 [March 30, 1961; June 2, 1961; June 13, 1961], Nos. 11865/61, 20041/61 and 21322/61. Heading B7G. [Also in Division F3] An aircraft seat ejection system comprises an ejection gun (not shown) for initial ejection of the seat from the aircraft in a predetermined direction (relatively to the aircraft) and a rocket motor independent of the gun, for producing a thrust vector substantially aligned with the predetermined direction, and means for adjusting the position of the thrust line of the rocket motor relatively to the seat, while preserving its direction, so that the thrust line may pass substantially through the centre of gravity of the seat and its occupant. In one embodiment, Fig. 2, the seat has a rocket motor pack beneath the seat pan as in Specification 920,545, the spine of the pack being slidably received in slots 41 in brackets 12 on the seat. The igniting cartridge breech tube 31 is slidable relatively to the spine, and is supported from the seat by a bracket 13. The pack, and hence the line of thrust of the nozzles 19, is movable fore-andaft relatively to the seat by rotation of a knurled nut 38. A window in a strip 44 on the bracket 12 co-operates with a scale 43 on the motor pack to show the position of the pack, preferably in terms of the pilot weight moment as indicated by the test seat of Specification 959,900. Alternatively, the pack may be movable by a lockable hand lever on the seat, Fig. 6 (not shown), or may be locked to the seat by pins inserted into co-operating apertures on the spine and on the seat, Fig. 7 (not shown). In another embodiment, Fig. 9, a pair of rocket motors 60 are mounted behind the seat back, each communicating through an elbow 63 with a sliding nozzle 65, which can be locked in any of a plurality of positions by insertion of pin 67 into apertures 71 in a fixed sleeve 68 so as to pass through a hollow cross-head 70 on a rod 66 attached to the nozzle. The firing mechanism with its cocking and releasing sear 62 are located at the upper end of the motor. In a modification, Fig. 11 (not shown), the nozzle is slidable by rotation of a knurled nut, and the firing mechanism is at the front of the sleeve 68, and slides with the nozzle, hot gases from the firing mechanism passing through the sleeve of nozzle 65 and elbow 63 to ignite the rocket motor charge. Specifications 583,257, 640,520, 652,131, 711,234, 889,689 and 959,899 also are referred to.