GB1440560A - Rocket motors - Google Patents

Abstract

1440560 Rocket motors IMPERIAL METAL INDUSTRIES (KYNOCH) Ltd 14 Nov 1968 [27 Nov 1967] 53848/67 Heading F3A A rocket motor comprises an annular nozzle 43 concentric with the longitudinal axis X-X of the motor and at least two equiangularly spaced spin-inducing nozzles 20 spaced from the longitudinal axis and inclined to a radial plane of the motor so that propellant gases from a common combustion chamber are directed through the annular nozzle 43 to impart an axial thrust to the motor, and through the nozzles 20 to impart spin to the motor. In the embodiment illustrated, a circular plug 6 is releasably secured to a longitudinally extending central support 1 by means of a bolt 16. Four spin-inducing nozzles 20 are suitably dimensioned to be a press fit in holes 14 in the plug 6. A spider member 25 secured to the plug 6 is provided on its forward face with four equi-angularly spaced radial slots 26 and a flange 30 on the forward end of the central support 1 is provided on its rearward face with four equi-angularly spaced radial slots 37 in alignment with the slots 26. Four rectangular plates 38 each carrying cordite charges 33 are fitted radially into the motor by sliding the ends of the plates along the slots 26, 37. The radially inner edges of the plates are located in grooves 39 in the central support 1. An annular recess 31 on the rearward face of the flange 30 accommodates an igniter 32 comprising magnesium based ignition material and a fuse for ignition of the cordite charges 33. Four apertures 27 extend through the spider member 25 intermediate the slots 26, each aperture 27 being in axial alignment with a hole 15 in the plug 6 so that pyrotechnic flares 28 may be fitted in the holes 15 to extend through the spider inwardly along the motor. The periphery of flange 30 has an external screw-threaded portion 40 for engagement with an internal screw threaded portion 41 of a tubular casing 42 which extends rearwardly over the motor to the plug 6. The rearward end of the casing 41 is radially spaced from the contoured periphery of the plug 6 to define the annular nozzle 43. A typical use of the motor is for the first stage propulsion unit of a missile. The particular embodiment described above is intended for applications in which the motor may be reused by unscrewing the casing 42, removing the plates 38 which carried the spent cordite charges, fitting a new igniter 32, and reloading new flares 28 and charges 33.