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Pulse gun

A pulse and detonator technology, applied in the field of pulse guns, can solve the problems of long time consumption, complex structure, and many explosion transmission links, and achieve the effects of reducing effective volume, increasing work reliability, and isolating external high-temperature and high-pressure gas

Active Publication Date: 2017-08-18
XIAN AEROSPACE PROPULSION INST
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AI Technical Summary

Problems solved by technology

[0007] The disadvantage of the above-mentioned traditional pulse gun is that there are two stages of explosion transmission, and the primary charge in the igniter is used to ignite the output charge to generate high-temperature gas, thereby igniting the propellant powder filled in the drug cavity of the shell to realize the pulse disturbance of the engine. There are many detonation links and take a long time; a special drug chamber is set in the shell to fill the powder, and the structure is complex

Method used

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Embodiment Construction

[0032] The present invention will be described in further detail below in conjunction with the accompanying drawings and embodiments.

[0033] Such as figure 1 As shown, the pulse gun is composed of a detonating device 1 and a housing assembly 2 . The detonator 1 comprises a detonator body 11, a pressure ring 12 and a tablet 13; the input end of the detonator body 11 is connected with an excitation source, and the output end of the detonator body 11 is a boss 111, and the center of the boss 111 is provided with a stepped hole; the above-mentioned The pressure ring 12 is embedded in the large hole cavity of the step hole; the cavity of the pressure ring 12 is filled with the output drug 3, which is cyclotrimethylammonium trinitrate, also known as RDX, which has high energy , the advantages of high density, the charging method of the output medicine 3 is loose packing in the natural state or pressure packing; the above-mentioned drug blocking piece 13 is arranged at the large h...

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Abstract

The invention relates to a pulse gun which is specially suitable for a testing device for evaluating combustion stability of a low-thrust rail attitude-control liquid-propellant rocket engine. The pulse gun solves the technical problems that a traditional pulse gun is multiple in explosion propagation link, long in consumed time and complex in structure. The pulse gun comprises a priming device and a shell assembly. The priming device comprises an exploder body, a pressing ring and an explosive stop piece. The output end of the exploder body is provided with a boss. A step hole is formed in the center of the boss. The pressing ring is fixedly installed in a large hole cavity of the step hole. The explosive stop piece is arranged at a large hole opening of the step hole and installed on the pressing ring in a sealing manner. A cavity of a small hole of the step hole is filled with starting explosive. A cavity of the pressing ring is filled with output explosive. The shell assembly comprises a shell and a detonating membrane. One end of an inner cavity of the shell is a joint end with the diameter enlarged. The joint end is in screw connection with the boss at the output end of the exploder body. The detonating membrane is arranged at the other end of the inner cavity of the shell in a sealing manner.

Description

technical field [0001] The invention relates to a test device specially suitable for evaluating the combustion stability of a small-thrust orbit attitude control liquid rocket engine, in particular to a pulse gun. Background technique [0002] The small-thrust liquid rocket engine is a propulsion device that provides power for missile weapons and spacecraft to perform various maneuvers in space. It is mainly used for orbit control, attitude control, docking and rendezvous of spacecraft, and landing. Its working feature is to start pulse work multiple times in the space environment to change the thrust, the thrust is small, and the minimum pulse width is milliseconds. Low-thrust orbit and attitude control liquid rocket engine technology is widely used in small satellite orbit positioning, attitude adjustment, flight control of small aircraft, final repair and precise positioning of small missiles, etc. [0003] Periodic oscillations of combustion in rocket engine combustors,...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/96F42B3/12
CPCF02K9/96F42B3/12
Inventor 李应强李斌高凤川刘铭李永锋张建刚夏开红李平
Owner XIAN AEROSPACE PROPULSION INST
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