Engine jet pipe preparation method of space launch vehicle

Abstract

The invention provides an engine jet pipe preparation method of a space launch vehicle. The preparation method comprises the steps that an engine jet pipe matrix and a housing are provided, wherein two protruding ribs arranged at intervals are at least included in the outer surface of the engine jet pipe matrix, and grooves are formed by the two protruding ribs and the engine jet pipe matrix in the parts between the two protruding ribs; the housing is matched to the outside of the engine jet pipe matrix, wherein the housing, close to the engine matrix, is in close contact with the protruding ribs; and on the surface, away from the protruding ribs, of the housing, laser produced by a laser generating device is enabled to move along the positions corresponding to protruding ribs, so that thehousing is fixed to the engine jet pipe matrix by welding to the protruding ribs, thus, a cooling passage for the flow of coolant liquid is formed by the grooves and the housing. According to the engine jet pipe preparation method of the space launch vehicle, the laser welding method is adopted, through directly welding the housing with the engine matrix in the outside of the engine jet pipe housing, the welding process can be greatly simplified, the welding cost can be reduced and the welding quality can be improved.

Description

technical field [0001] The invention relates to the technical field of aerospace vehicle engine design, in particular to a preparation method for an engine nozzle of a space vehicle. Background technique [0002] The nozzle is the part in the liquid rocket engine responsible for accelerating the expansion of the gas and obtaining the reverse thrust. In order to withstand the high temperature of the gas, the nozzle generally adopts active cooling technology. For example, a propellant can flow through hundreds of tiny channels in the nozzle structure to take away the heat of the gas and ensure that the material (such as metal material) of the nozzle structure will not be ablated or burned by the gas. The structure is also called cooling jacket structure. [0003] The cooling jacket structure of the nozzle is composed of the inner wall and the outer wall of the milling groove. On the inner wall, for example, hundreds of flow channels can be processed by milling, and then the...

AI Technical Summary

Problems solved by technology

If the inner and outer walls are not welded firmly, the high pressure of the propellant in the cooling channel may cause the joints of the inner and outer walls to disengage

Once this happens, the local structure of the engine nozzle will be unstable and torn, and the nozzle will burn out, the cooling of the engine will fail, and the rocket will fail to fly.

[0005] The existing welding methods of inner and outer jackets include vacuum pressure brazing and diffusion welding, but the welding process of these two welding methods is relatively complicated, and the welding cost is high, which increases the production cost of the engine nozzle

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