GB885490A - Improvements in rocket motor assemblies - Google Patents

Abstract

885,490. Rocket motor assemblies. GENERAL ELECTRIC CO. July 16, 1959 [July 21, 1958], No. 24463/59. Class 110 (3). In a rocket motor assembly, the propellant container is of ring form, either circular or polygonal, and a series of rocket motor units is mounted therearound and connected thereto so as to discharge at right angles to the plane of the ring. The cross-section of the container may be round, elliptical or approximately square. In the case of mono-fuel a single fuel container is provided but where fuel and oxidizer are used two concentric containers each of ring form are provided; alternatively a single container may be partitioned to provide two compartments, The container 10 in Fig. 1 is of toroidal form and a series of rocket motor units 11 each comprising a combustion chamber, a propellant injector and a propulsion nozzle is mounted thereon, each motor discharging normally to the plane of the container 10. In Fig. 2 the combustion chambers 17 are disposed along either side of the propellant container 10 which is of square cross-section, the gases discharging along the surfaces of the guide member 18. The combustion chambers 17 may each be divided into short lengths. The fuel container 10 in Fig. 4 is partitioned to afford fuel and oxidizer chambers 22, 23 which are connected to the injectors 24 by ducts 25, 26. The combustion chambers are shown at 28 and the combustion gases discharge through the outlet nozzles along the sides of the guide plug 29. A divided combustion chamber 34 is shown in Fig. 6, the propellant injector being indicated at 33 and the dividing baffles at 36. Rocket motor assemblies may be arranged in stages. The object of the invention is to provide a rocket assembly capable of providing thrust of the order of fifty million pounds. Specification 885,489 is referred to.