Combined exhaust pipe for solid rocket engine

Abstract

The invention discloses a combined exhaust pipe for a solid rocket engine. A Laval tube is arranged in a cavity of an exhaust pipe base, and the two ends of the Laval tube are limited by the inner end face of the exhaust pipe base and an annular gland. The annular gland is positioned through a safety pin penetrating through the exhaust pipe base and extending into the annular gland. Shearing sleeves are arranged between the safety pin and the exhaust pipe base and between the safety pin and the annular gland. Combination design is adopted for an exhaust pipe body, according to different design requirements and the exhaust pipe ablation condition, only structural parameters of the Laval tube are changed and the Laval tube is replaced so that the exhaust pipe base can still continue to be used, the exhaust pipe has certain universality and reusability, and cost is effectively used. The safety pin is used in cooperation with the inner shearing sleeve and the outer shearing sleeve, and the diameter of the safety pin, the inner diameter of the inner shearing sleeve and the inner diameter of the outer shearing sleeve can be adjusted according to design requirements; the shearing strength of the safety pin is convenient to adjust, the safety of the engine is guaranteed, and the universality of the exhaust pipe is also guaranteed.

Description

technical field [0001] The invention belongs to the field of solid rocket motors, in particular to a combined nozzle of solid rocket motors. Background technique [0002] The structure of the existing solid rocket motor is generally composed of components such as the middle bottom, the front and rear baffle plates, the combustion chamber and the nozzle. Because the solid rocket motor has the characteristics of simple structure, easy maintenance and high reliability, it is widely used in military , Civil products. The nozzle is one of the important components in the structure of the solid rocket motor. As the energy conversion device of the solid rocket motor, it converts the thermal energy of the high-temperature gas into the kinetic energy of the gas, thereby generating thrust. Since the nozzle of the rocket engine is subjected to high temperature and high-speed gas flow during use, the throat diameter of the nozzle is easily deformed and ablated. Engines are generally di...

AI Technical Summary

Problems solved by technology

For the reusable engine, in order to ensure the consistency of the working state, the disposable nozzle generally used, after many static tests, due to the ablation of the throat of the nozzle, it is usually uneconomical to replace the whole component

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