6 results about "Rocket engine" patented technology

The invention provides an anti-backfire nozzle for a rocket engine. The anti-backfire nozzle comprises a rotary core body (1), an anti-backfire ring (2) and a shell (3); the anti-backfire ring (2) is arranged between the rotary core body (1) and the shell (3); the inner wall face and the outer wall face of the anti-backfire ring (2) cling to the outer wall face of the rotary core body (1) and the inner wall face of the shell (3) respectively; a liquid propellant storing and distributing cavity (11), a tangential hole (12) and a swirl chamber (13) are formed in the rotary core body (1); the shell (3) is provided with a nozzle exit (31) and a thermal insulation material (32); and a propellant flows along a flowing passage defined by the anti-backfire ring (2), the liquid propellant storing and distributing cavity (11), the tangential hole (12), the swirl chamber (13) and the nozzle exit (31), is uniformly distributed and shunted by the liquid propellant storing and distributing cavity (11), forms uniform conical mist spray at the outlet of the nozzle exit and is atomized. The anti-backfire nozzle has the advantages of simple structure, mature process and the like, has both the functions of backfire resistance and efficient combustion and is suitable for other engines and combustion devices with high requirements on performance and easiness in generating backfire.

The invention discloses a dual-pulse solid rocket engine soft interlayer ablation test device comprising an end combustion powder charging cavity, a test piece ablation cavity, a spray pipe cavity anda center cube connector (5). The end combustion powder charging cavity and the test piece ablation cavity are symmetrically installed at the two ends of a through hole of the center cube connector (5). The spray pipe cavity is connected with the third hole of the center cube connector (5). An end combustion powder charging cavity blocking cap (1), an end combustion powder charging cavity shell (2), the center cube connector (5), a spray pipe cavity shell (6), a spray pipe cavity rear section (9), a test piece ablation cavity shell (11) and a test piece ablation cavity blocking cap (14) of thetest device are all made of high-strength 45 steel material. An end combustion powder charging cavity liner (3), a spray pipe cavity liner (7), a spray pipe cavity rear section liner (10) and a testpiece ablation cavity liner (12) are all made of ethylene propylene terpolymer material. A spray pipe cavity throat liner (8) is made of graphite. Through the dual-pulse solid rocket engine soft interlayer ablation test device, the problems that the work process of a dual-pulse engine ii pulse soft interlayer is difficult to simulate and observe are solved.

The invention relates to the technical field of a rocket engine, specifically relates to a rocket engine injection structure, an injection device, a rocket engine and a rocket suitable for a liquid rocket engine. An inner nozzle structure in the rocket engine injection structure is provided with an inner wall structure distributed circumferentially, the inner wall structure extends outward integrally to form an outer wall structure; the injection structure forms an annular cavity surrounding the inner nozzle structure between the inner wall structure and the extended outer wall structure; an outer inlet is formed in the annular cavity and provided with an outer nozzle arranged in the same direction of the inner nozzle, so that the annular cavity can play a role similar to the outer nozzlestructure; when realizing atomizing and mixing oxidant and fuel in the rocket engine, the annular cavity is formed by the inner wall structure of the inner nozzle integrally extending outwards, so thesituation that the existing inner nozzle structure and the outer nozzle structure adopt a welding mode to generate welding seams is avoided, the use of welding in the injector is reduced, and the quality and yield of the injector are improved.