A valve structure of a liquid rocket engine and the liquid rocket engine

Abstract

The invention discloses a valve structure of a liquid rocket engine and the liquid rocket engine, which comprise an actuator, a double-layer bellows, a thrust assembly and a valve main body; the inside of the actuator has a first valve for the circulation of gas medium and runs through both ends of the actuator. A channel and a second channel extending in a direction different from that of the first channel; one end of the thrust assembly is arranged in the cylinder through the base, and the other end is used to push the valve body to move, and the outer side of the base Closely attached to the inner wall of the actuator; the double-layer bellows is located on the inner side of the actuator, and the outer surface is in conflict with the inner wall of the actuator; A channel communicates with the third channel and the fourth channel through which the thrust assembly passes, and one end of the fourth channel communicates with the gap between the double-layer bellows, and the other end communicates with the second channel. Compared with the prior art, the structure reduces the amount of engine control gas and improves the sealing performance of the valve.

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.

Images