Generator for hot gases, in particular the rocket engine, with a fixed and a liquid prop propellant with hypergolic properties

摘要

1,010,453. Self-propelled missiles. OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALES. July 31, 1962 [Aug. 30, 1961; July 12, 1962], No. 29317/62. Heading F3A. [Also in Division F1] A rocket engine using solid and liquid components hypergolic with respect to each other comprises a reaction chamber into the upstream end of which a liquid component is injected and a solid component arranged to leave a passage for the flow of reaction products therethrough to the outlet nozzle of the rocket, there being in the passage at least one transverse obstacle so as to increase the time spent by the flow of the products upstream of the obstacle and thereby intensify the consumption of solid component upstream thereof. A rocket engine, Fig. 1, has a combustion chamber 1 containing solid fuel components 3a, 3b, 3c with a circular passage 4 therein. An adjustable injector 5 delivers liquid oxidizer, such as nitric acid, which is hypergolic with respect to at least component 3a. Orifice plates 6a, 6b restrict the flow of reaction products upstream thereof and thereby intensify the consumption of components 3a, 3b. In a modification, Fig. 5, the oxidizer is also injected into intermediate zones of passage 4 through injectors 5b and through plastic pipes 8 embedded in component 3b. Optimum relative dimensions of components 3a, 3b, 3c, outlet nozzle 2 and the orifices in plates 6a, 6b are given. Components 3a, 3b, 3c may consist of a mixture of paratoluidine and a paste of polyvinyl chloride with the addition of a plasticizer, or a mixture of triethylaluminium and polystyrene and other components containing metallic hydrides or amides.