Valve structure of liquid rocket engine and liquid rocket engine

Abstract

The invention discloses a valve structure of a liquid rocket engine and the liquid rocket engine. The valve structure includes an actuating cylinder, a double corrugated pipe, a thrust assembly and avalve main body. A first channel for gas medium circulation and penetrating through two ends of the actuating cylinder and a second channel different from the first channel in the extension directionare arranged in the inner side of the actuating cylinder, one end of the thrust assembly is arranged in the actuating cylinder through a base, the other end of the thrust assembly is used to drive thevalve main body to move, the outer side of the base is tightly attached to the inner wall of the actuating cylinder, the double corrugated pipe is located in the inner side of the actuating cylinder,and the outer side surface of the double corrugated pipe abuts against the inner wall of the actuating cylinder. A supporting plate is provided with a third channel and a fourth channel communicatingwith the first channel for passing of the thrust assembly, one end of the fourth channel communicates with a gap in the double corrugated pipe, and the other end of the fourth channel communicates with the second channel. Compared with the prior art, the structure reduces the amount of engine control gas, and the sealing of the valve is improved.

Description

technical field [0001] The invention relates to the field of liquid rockets, in particular to a valve structure of a liquid rocket engine and the liquid rocket engine. Background technique [0002] With the rapid development of the aerospace industry, various technologies involved in the rocket field have also achieved rapid progress. Valves are an important part of starting and shutting down liquid rocket engines. The medium of the cryogenic liquid rocket engine is an ultra-low temperature propellant, the temperature range of the medium is usually around 20K-120K, and the pressure is above 10MPa. The valve operating gas is usually high-pressure gas with a pressure of about 20MPa. [0003] At present, in addition to liquid hydrogen and liquid oxygen, liquid propellants used in domestic active low-temperature liquid rocket engines, some domestic liquid rocket models under research also use liquid methane as propellant. The dynamic seals for valves used in liquid engines us...

AI Technical Summary

Problems solved by technology

This valve action mode requires the engine to carry a large amount of control gas, which in turn increases the weight and structural size of the rocket

In addition, due to the high vibration intensity during the working process of the engine, the large temperature difference between cold and hot, and harsh environmental conditions, the sealing effect of the sealing device may be weakened, affecting the reliability of the engine.

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