GB758212A - Improvements in and relating to fuel igniters for rocket motors and like devices - Google Patents

Abstract

758,212. Igniters for rocket motors. ENGLISH ELECTRIC CO., Ltd. Feb. 18, 1955 [Feb. 19, 1954], No. 5036/54. Class 9(2) An igniter 1 for a rocket motor 3 comprises a case 2 containing the ignition mechanism and having an end closure 4 on which is mounted the arming mechan- .ism 5. Within the other end of the case is a cap 6 held in place by a circlip 7 and a spring 8 which urges a piston to the armed position. The hollow stem 14 of the piston houses a tube 10 containing the ignition substance, the tube acting as a core along which the piston can slide. An annular channel for the flow of gas from one side of the piston to the other is provided by a recess 11 in the wall of the case 2. Vents 12 are provided in the closure 4. Lead wires for electric current passing through sealing screws 13 are used to ignite the substance in the tube 10 and the hot gases liberated pass through vents 16 in the stem 14 into the case 2. Before the igniter is armed, the piston is depressed by a pin 21 so that a plug 15 which terminates the stem 14 is pressed into an aperture in the cap 6, the plug 15 and the cap together forming a valve. In this position of the plug, the gases entering the case 2 pass through the recess 11 to discharge through the vents 12. Sealing rings 17, 18, 19, 20 prevent undesired leakage of gas. The arming mechanism 5 comprises a locking member 24 which locks a pivoted arm 22 carrying an adustable screw 26 in engagement with the pin 21. To arm the igniter, the locking member 24 is withdrawn, whereupon the arm 22 swings on its pivot and allows the pin 21 to move outwards releasing the piston, which is then moved bv its spring 8, so that the plug 15 is withdrawn from its seating. The hot gases from the tube 10 then pass to the rocket motor to ignite the fuel.