GB736738A - Improvements in and relating to ejectable seats for aircraft - Google Patents

Abstract

736,738. Stud and socket fastenings. SOC. NATIONALE DE CONSTRUCTIONS AERONAUTIQUES DU NORD. July 15, 1953 [July 16, 1952], No. 19622/53. Class 44. [Also in Group XXXIII] A spindle 15 passes through pairs of circular bores 16, 17, 18 in a launching ramp 5a secured to an aircraft (see Group XXXIII), lugs 14a on a seat 14, and lugs 8a on a carriage 8 respectively. The spindle is formed with rectangular cross sections 21 in the vicinity of members 5a, adapted to pass through slots 19 therein, Fig. 4, and second rectangular cross sections 27 in the vicinity of lugs 8a, being at right angles to sections 21, and adapted to pass through slots 25. As shown in Fig. 3, if the aircraft seat ejection gun is accidentally fired, the carriage 8 rises alone, the slots 25 passing over sections 27, Fig. 4. A spindle 15 is turned through a right angle delineated by pins 22 engaging slots 23 in the spindle, and the gun is fired, the carriage 8 and seat 14 are locked together, and rise together, the sections 21 passing through slots 19. A further connection D<SP>2</SP> (not shown) is provided between the seat, launching ramp, and carriage to prevent relative tilting. An alternative connection is shown in Fig. 8, where the member 8c is free to rise alone. The plug 15c may be moved to the right by a push rod 45 engaged with the plug 15c by a knob 43 seated on a semicircular extension of rod 45, so that knob 43 is clear of member 5c, and plug 15c extends inside members 14c and 8c, so that the latter are locked and rise together, knob 43 leaving its seating. Specification 583,257, [Group, XXXIII], is referred to.