Patent GB-1099621-A (GB)
Title: An apparatus for removing a load from a space especially an occupant from an aircraft
IPC: B64D25/08
Filed: 1965-06-15
Abstract: 1,099,621. Aircraft escape apparatus. STANLEY AVIATION CORPORATION. June 15, 1965 [Aug. 19, 1964], No. 25206/65. Heading B7G. [Also in Division F3] Escape apparatus for an aircraft comprises a rocket ejected from the aircraft and connected by a line to an airman. The rocket 104 is ejected by cartridge-generated gas pressure and rocket ignition is initiated by the line becoming taut (see Division F3). The ejection angle may be varied by a pneumatic ram (514) actuated by ram air pressure (Fig. 26, not shown) so that the rocket is ejected more forwardly at high speed. The seat back 30 to which the airman is strapped by a torso harness, is fixed to rails 36, 38 slidable along fixed supports 56, 58 and is extracted with the airman. The seat pan 28 is pivotally mounted about a horizontal axis and is restrained by the seat back resting upon it. The seat back is held down by latches 84 which release when a predetermined upward force is applied to the back. When the back is lifted on extraction the seat pan tips down (i.e. rear end up) to facilitate the movement of the airman's legs. In another embodiment (Figs. 26-28 and 33-37, not shown), the seat pan is hinged to the seat back and tips as the former is raised, but the upward movement of the seat causes disengagement of a lap strap (384) from the seat, by pivoting hooks (390) (Fig. 34, not shown) out of engagement with the strap fittings (388), and also ignites a fuse (572) to detonate cartridges (574, 576) to sever shoulder straps attached to the seat. The airman is then extracted without the seat, hinged panels (395, 396) (Fig. 26, not shown) connecting the front of the seat pan to the aircraft structure providing a guide for the airman's heels and restraining the seat. The seat back is held down by a latch (367) (Figs. 35, 36, not shown) on a tube rotated to release the latch by a line (392) attached to the lines connecting the airman's harness to the rocket. The detonator fired when the lines connected to the rocket become taut ignites a charge (280) (Figs. 10, 30 and 31, not shown) which ignites the rocket propellant (109) and also burns at such a rate that shortly before the propellant burns out it ignites a further charge (302) to fire a detonator lighting a fuse (292) leading to charges that explode to sever the lines (170, 172) connecting the rocket to the airman. Where the seat back is extracted with the airman, a parachute pack (54) (Figs. 14 and 14A, not shown) is housed behind the seat and a pilot parachute (312) is deployed either manually, or by barometric or timing apparatus to release a catch (322) and pivot the pack rearwardly about connections (318) at its lower end to the seat, to facilitate extraction of the main parachute. In the embodiment in which the seat is retained in the aircraft, a parachute pack is strapped to the airman's back. The escape apparatus is operated by pulling a handle which also actuates an inertia reel to wind in the shoulder straps, releases a latch on the extraction rocket, operates a canopy jettison mechanism and a canopy cutter (in case the jettison mechanism fails to operate). A further handle (582) (Fig. 32, not shown) is provided which merely activates the lap belt release and the charges severing the shoulder straps, thus permitting the airman to climb out.