Spiral grain type solid-liquid rocket engine

Abstract

The invention discloses a spiral grain type solid-liquid rocket engine. The spiral grain type solid-liquid rocket engine comprises a head cover, a jetting panel, a front combustion chamber, a combustion chamber shell, a grain, a rear combustion chamber, a rear sealing head, a spraying pipe and a spraying pipe pressing plate. A threaded groove is designed in the inner wall of the grain, and therefore the combustion speed of the grain can be effectively increased, and the performance of the solid-liquid rocket engine is improved. For the solid-liquid rocket engine in which the specific value of the length of the grain to the inner diameter of the grain ranges from 5 to 15 and the ratio of the inner diameter of the grain to the outer diameter of the grain ranges from 1/6 to 1/2, the grain is subjected to optimization design. The spiral grain type solid-liquid rocket engine has the beneficial effects that the combustion speed of the solid-liquid rocket engine can be better increased, and the performance of the solid-liquid rocket engine is improved.

Description

technical field [0001] The invention belongs to the field of rocket engines, and in particular relates to a solid-liquid rocket engine using spiral grains. Background technique [0002] The solid-liquid rocket engine is a new type of engine, the oxidant is gaseous or liquid, and the fuel is solid, which determines that its mixing and combustion process is different from traditional liquid and solid rocket engines. Solid-liquid rocket motors have the advantages of good safety, low cost, and good environmental friendliness. [0003] However, the low burning rate of solid fuel is an important factor restricting the development of solid-liquid rocket engines. At present, methods such as adding high-energy metal particles to solid fuels and improving oxidant injection methods have been used to increase the burning rate of solid fuels. Adding high-energy metal particles to increase the burning rate will increase the ablation of the nozzle, and it is only suitable for castable gr...

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Problems solved by technology

[0004] In order to solve the problem of low burning rate of the solid-liquid rocket engine, the patent of the present invention proposes a new type of solid-liquid rocket engine, including the head cover, the injection panel, the front combustion chamber shell, the front combustion chamber insulation layer, the powder column, and the combustion chamber shell Body, after combustion chamber shell, after combustion chamber insulation layer, rear head shell, rear head insulation layer, nozzle and nozzle pressure plate

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