Novel connecting structure for composite-material spray pipe extending section and short spray pipe thrust chamber of rocket engine

Abstract

The invention discloses a novel connecting structure for a composite-material spray pipe extending section and a short spray pipe thrust chamber of a rocket engine. The novel connecting structure comprises the composite-material spray pipe extending section and the short spray pipe thrust chamber, wherein a first flange is arranged on the composite-material spray pipe extending section; the first flange is integrally formed with the composite-material spray pipe extending section, and is a tapered curved surface which is outwards expanded; a plurality of unthreaded holes are uniformly distributed in the first flange; the number of the unthreaded holes is greater than 4; the spray pipe outlet of the short spray pipe thrust chamber is provided with a second flange which is a tapered curved surface having a bending angle matched with that of the first flange; threaded holes which are as many as the unthreaded holes in the first flange are uniformly distributed in the second flange; sealing groove structures are distributed inside the threaded holes; and the composite-material spray pipe extending section and the short spray pipe thrust chamber are connected through the first flange and the second flange, are sealed by a flexible graphite sealing ring, and are reinforced through bolts. The novel connecting structure realizes fastening connection between the spray pipe extending section and the short spray pipe thrust chamber, and realizes reliable sealing of high-temperature fuel gas in a spray pipe.

Description

technical field [0001] The invention relates to the technical field of spacecraft propulsion systems, in particular to a novel connection structure of a rocket engine composite material nozzle extension section and a short nozzle thrust chamber. Background technique [0002] The engine is the heart of spacecraft such as launch vehicles and satellites, providing power for the spacecraft to change its orbit and attitude. The nozzle is the core component of the rocket engine, which converts the heat energy of the high-temperature gas in the combustion chamber into kinetic energy to make the engine generate thrust. In order to improve the performance of the rocket engine, it is usually necessary to increase the area ratio of the nozzle, that is, to use the nozzle extension. For traditional rocket engines, the material of the nozzle extension is niobium alloy, which is connected with the thrust chamber of the short nozzle by welding. [0003] Based on the carbon fiber prefabric...

AI Technical Summary

Problems solved by technology

[0005] 1) It is difficult to form the flange of the composite material nozzle;

[0006] 2) The axial fiber content at the flange is low, resulting in low axial strength;

[0007] 3

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