Combined tool for thrust chamber preparation process and thrust chamber preparation process

Abstract

The invention provides a combined tool for a thrust chamber preparation process and the thrust chamber preparation process. The combined tool comprises a spray pipe section tool body and a body section tool body; the spray pipe section tool body comprises a spray pipe positioning assembly, a pressing ring assembly and a short shaft assembly; the body section tool body comprises a body shaft assembly, a pressing block assembly and a force transmission assembly; in a spray pipe short shaft state, the spray pipe positioning assembly, the pressing ring assembly and the short shaft assembly cooperate for use, and thus a thrust chamber spray pipe is positioned and clamped; in a body shaft state, the body shaft assembly, the pressing block assembly and the force transmission assembly cooperate for use, and a thrust chamber body is positioned and clamped; and in a spray pipe short shaft state, the spray pipe positioning assembly, the pressing ring assembly, the body shaft assembly, the pressing block assembly and the force transmission assembly cooperate for use, and thus the thrust chamber body and the thrust chamber spray pipe are positioned and clamped in a whole. By means of the combined tool for the thrust chamber preparation process and the thrust chamber preparation process, the number of single tools can be greatly reduced, floor occupation and management of multiple single tools are reduced, and the production cost of thrust chambers is reduced.

Description

technical field [0001] The application belongs to the technical field of rocket engine manufacturing, and in particular relates to a composite tooling used in the thrust chamber preparation process and the thrust chamber preparation process. Background technique [0002] As an important part of the liquid rocket engine, the thrust chamber is mainly used to provide a place for chemical energy to be converted into thermal energy, and to use the Laval nozzle to convert the thermal energy of the high-temperature gas into a supersonic airflow with high kinetic energy, thereby obtaining reverse thrust . In order to withstand the high temperature of the gas, the nozzle generally adopts a cooling jacket structure. When the propellant flows through hundreds of tiny channels in the nozzle structure, the heat of the gas is taken away to ensure that the metal material of the nozzle structure is not ablated or burned by the gas. The cooling jacket structure of the nozzle is composed of ...

AI Technical Summary

Problems solved by technology

In the manufacturing process of the existing nozzles, these toolings each undertake their own functions and are not universal, which leads to the following problems in the manufacturing process of the nozzles: high production cost, large demand for manufacturing sites, and frequent use by workers The unloading products reduce the product quality and production efficiency

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