GB780721A - Improvements in or relating to rocket launching tube - Google Patents

Abstract

780,721. Discharging rockets from aircraft. NORTHROP AIRCRAFT, Inc. June 13, 1955, No. 16993/55. Class 9(2) Rocket launching tubes 7 mounted in aircraft as in Specification 780,722 and communicating with a common exhaust port are provided with rear closure means displaceable by the exhaust gases when the rockets are fired therefrom to vent the tubes and the closures are returned to normal after escape of the gases. Each tube 7 comprises a cylinder 9 strengthened at the forward end, which houses the rocket 6, by a tubular cage 11 and partly covered by an electrically heated blanket 13 which controls the temperature of the rocket 6. Spaced channel elements 14 within the tube serve as guides for the rocket which is stopped by a bracket 15 when inserted in the tube from the muzzle end. The rocket has folding tail vanes 16 and is held in the firing position by a latch 17..Within the rear part of the tube 7 a cylinder 19. Fig. 4, is fixed by diametrically opposed leg members 21 so that there is free passage for the exhaust gases around the cylinder. which carries an igniter 22 contacting firing means in the rocket. Valve closure means for the rear of the tube 7 consists of a frustoconical element 28 mounted on a stem 24 slidable through a bushing 23 closing the cylinder 19 and surrounded by a spring 27 which holds the valve in the closed position until a rocket is fired, when the gas thrust opens the valve. Specification 772,884 also is referred to.