A test device for measuring the combustion-to-detonation performance of propellants

Abstract

The invention discloses a testing device for testing the deflagration to detonation transition performance of propellant powder. The testing device comprises an electric igniter, an end cover, ignition powder, a pressure sensor, a deflagration to detonation transition pipe and charged propellant powder, and further comprises a sleeve, a simulated bullet and a simulated launching pipe. The end cover is a cylinder with a center step through hole in the axial direction, and is connected with the sleeve through threads, the igniter and the ignition powder are arranged in the center through hole of the end cover, the sleeve is a cylinder with an observation slot along a generatrix of the cylinder, the deflagration to detonation transition pipe is arranged in the sleeve, and is compactly filled with the charged propellant powder, and the charged propellant powder is in close contact with the ignition powder. The simulated launching pipe is a cylinder with external threads at one end, and is connected with the sleeve through the threads, and the simulated bullet is arranged in the simulated launching pipe. The error of testing the wave surface-time relation of explosive and powder deflagration and detonation can be reduced, and the simulated launching pipe is closer to a real launching pipe, and can be equivalent to the actual launching environment.

Description

Technical field [0001] The invention belongs to the technical field of propellant laboratory test devices, and relates to a combustion-to-detonation device, in particular to a combustion-to-detonation device for propellant. Background technique [0002] In modern warfare, in order to meet the needs of long-range artillery strikes, it is required to greatly increase the burning rate of the propellant, thereby increasing the initial velocity of the projectile. However, due to the high sensitivity of the burning rate to pressure, excessive pressure can destabilize combustion, making it easy to transform into detonation. Once the propellant burns during combustion or even at the moment of ignition, it will cause the weapon system to fail or even detonate. Damage to own launch platform. Therefore, it is particularly important to establish a scientific simulation experiment and evaluation method of propellant combustion to detonation to ensure the safe application of propellant. [000...

AI Technical Summary

Problems solved by technology

But this device has the following disadvantages: First, the wave front-time relationship of propellant and explosive combustion and detonation is characterized by the position-time relationship of the recorded pressure waveform, and the ionization probe method is used to record the position-time relationship of the pressure waveform. In the time relationship, the data acquisition rate of the ionization probe is not high, and false triggering is prone to occur, resulting in a large error in the test results. Therefore, the obtained wavefront-time relationship results of propellant combustion and detonation have large errors

Secondly, when the propellant burns in the gun barrel, one end is a closed barrel and the other end is a movable projectile. The projectile is constantly moving during the reaction process of the propellant, and the two ends of the test tube of the device are closed structures. There are certain differences with the actual launch tube, and cannot be equivalent to the actual launch environment

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