Connecting and sealing device

Abstract

The invention discloses a connecting and sealing device comprising a shell and a spraying pipe connected with the shell. An assembling groove is formed in the inner wall of the shell; the spraying pipe is provided with an assembling step matched with the assembling groove; a clamping groove is further formed in the shell and is internally provided with a snap ring matched with the clamping groove; and part of the snap ring is installed in the clamping groove, and part of the snap ring is tightly clamped to the spraying pipe. The device is complete in function and convenient to operate and has high universality. At present, the device has been applied to many products, many experiments are successfully completed, a good effect is achieved, the assembling problem of a spraying pipe of a small-diameter solid rocket engine can be solved, and the purposes of reducing the structural mass and improving the assembling efficiency are achieved.

Description

technical field [0001] The invention belongs to the technical field of solid rocket motors, and in particular relates to a connection sealing device. Background technique [0002] The solid rocket motor is a power device that converts solid fuel into kinetic energy through combustion under high temperature and high pressure. It is mainly composed of ignition mechanism, shell, charge combustion chamber, nozzle and other components. Practice has shown that the connection form and sealing method between the shell and the nozzle are very critical, and the reliable connection between components is related to the reliability of the solid rocket motor system; at the same time, the effective sealing method prevents the The movement of high-temperature and high-pressure gas greatly reduces the possibility of structural strength failure, thereby effectively improving the safety and reliability of the solid rocket motor system. Usually, the traditional connection and sealing adopt fla...

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Problems solved by technology

During the design and manufacturing process, it was found that its structural mass is heavy and requires a large assembly space. Generally, it is widely used on engines with larger diameters, and will not bring additional negative mass to the solid rocket motor system; when the engine diameter When it is small (such as less than 200mm), there are many problems, such as limited external dimensions, small assembly space, inconvenient operation, etc. The traditional flange or thread structure has many disadvantages such as large structural quality and space exceeding the overall expectation. , unable to meet the design requirements of small-diameter solid rocket motors such as mass ratio and compact structure

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