High-pressure fuel gas exhaust guide device

Abstract

The invention provides a high-pressure fuel gas exhaust guide device. The device comprises a cylinder body, an ejector used for forming high-temperature and high-pressure fuel gas flow is arranged in the cylinder body, a piston rod is further arranged in the cylinder body, and one end of the piston rod is fixedly connected with the ejector; and an exhaust hole is formed in the cylinder body, a sealing assembly used for closing or opening the exhaust hole is embedded in the exhaust hole, a lever is rotationally installed on the outer side of the cylinder body, one end of the lever abuts against the sealing assembly and applies pre-tightening force to the sealing assembly, and a loading assembly used for providing the pre-tightening force is arranged at the other end of the lever. After a missile smoothly completes the launching task, fuel gas flow is sealed in the cylinder body, after the temperature of the fuel gas flow is reduced, the pre-tightening force of the lever to the sealing assembly can be cancelled through a control assembly at any time, thus reliable exhaust guide of the high-pressure gas flow is realized, and further, the reliable exhaust guide of the high-pressure gas flow is facilitated without affecting launching.

Description

technical field [0001] The invention relates to the technical field of high-pressure fluid drainage, in particular to a high-pressure gas drainage device. Background technique [0002] At present, missile cold launch technology is widely used in the field of defense and control weapon technology. Most of them use catapults to generate high-pressure gas to provide initial speed for missiles to complete the launch process. [0003] However, after the missile is launched, the high-pressure and high-temperature gas generated in the actuating cylinder is usually discharged through the vent hole, that is, after the catapult travels a certain distance and passes the vent hole, the high-pressure gas is discharged through the vent hole. [0004] The existing Chinese patent with the publication number CN105910492B discloses a concentric cylinder structure with an inner circle and an outer square for vertical thermal launch of a winged missile, including an outer cylinder, an inner cyl...

AI Technical Summary

Problems solved by technology

[0005] The inventor believes that the guide device in the prior art is easily affected by complex environmental factors, which can easily cause the gas flow to start to exhaust outside the missile before it is completely launched out of the cylinder, which in turn causes the initial velocity of the missile to fail to reach a predetermined value and affect Launch, even cause launch failure, there is room for improvement

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