Thrust chamber injector of hydrazine type low-thrust single-unit engine

Abstract

A thrust chamber injector of a hydrazine type low-thrust single-unit engine adopts a radial injection mode and structurally comprises injection pipes, a thrust chamber and an injection disc, wherein the injection pipes are fixed to the injection disc and installed at the front end of the thrust chamber, a thrust chamber head baffle is arranged at the front end of the thrust chamber, the injection disc is of an end cover structure capable of enveloping the front section of the thrust chamber, the injection disc is in matched connection with the front section of the thrust chamber, the front section of the thrust chamber is sleeved with the injection disc, an annular injection cavity is arranged between the injection disc and the front section of the thrust chamber, more than one circle of injection micropores are evenly formed in the periphery of the barrel wall of the annular injection cavity corresponding to the front section of the thrust chamber, the injection pipes are circumferentially and evenly distributed and fixed to the injection disc, and spray nozzles of the injection pipes correspond to the annular injection cavity. A propellant is radially injected through the micropores, reasonable injection pressure drop can be provided under the condition that related propellant flows are ensured, and the thrust chamber injector is reasonable in structure and simple in manufacture, is easily retrofitted to be serialized, and can meet the power demand of the single-unit engine.

Description

technical field [0001] The invention relates to a thrust chamber injector structure of a hydrazine type small-thrust single-component engine. Background technique [0002] The structure of thrust chamber and injector of existing small-thrust single-element engine is relatively complicated, and processing is relatively difficult. In the form of axial injection, such as figure 1 As shown, the injector injects the propellant axially into the catalyst bed. The nozzle needs to penetrate into the catalyst bed to a certain depth. In order to make the propellant have a wider injection range, it needs to penetrate into the catalyst bed That is, the nozzle diameter of the thrust chamber increases, but this will lead to an increase in the heat capacity of the nozzle, resulting in a sharp increase in the pressure roughness of the thrust chamber, and an increase in the aftereffect impulse of the engine, which cannot meet the technical requirements. Among them, the porous material inject...

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Problems solved by technology

[0002] The structure of thrust chamber and injector of existing small-thrust single-element engine is relatively complicated, and processing is relatively difficult. In the form of axial injection, such as figure 1 As shown, the injector injects the propellant axially into the catalyst bed. The nozzle needs to penetrate into the catalyst bed to a certain depth. In order to make the propellant have a wider injection range, it needs to penetrate into the catalyst bed That is, the nozzle diameter of the thrust chamber increases, but this will lead to an increase in the heat capacity of the nozzle, resulting in a sharp increase in the pressure roughness of the thrust chamber, and an increase in the aftereffect impulse of the engine, which cannot meet the technical requirements. Among them, the porous material injector The structure has the disadvantages of large thrust chamber pressure roughness, sensitivity to zero distance, difficulty in determining flow characteristics, and poor manufacturability; the main disadvantage of the penetration injector is that it is difficult to determine the depth of penetration into the catalyst bed, and it is difficult to Accurate calculation and distribution of the volume of the nozzle cavity, the diameter of the nozzle hole, and the total area of ​​the nozzle hole, the product consistency is not easy to guarantee, and there is an unpredictable impact on the thrust performance of the engine

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