Gunpowder combustion property test device under pressure reduction condition

Abstract

The invention discloses a gunpowder combustion property test device under pressure reduction condition, wherein, a watch window, a pressure discharge component, a pressure sensor and an igniting component are arranged on a combustion chamber of the device; the pressure discharge component is communicated with a pressure gas buffer tank which is filled with certain-pressure nitrogen and a high-speed camera can shoot combustion process of gunpowder sample through optical lens and the watch window; when the gas pressure in the combustion chamber reaches the pressure-proof critical value of the pressure discharge component by the combustion of gunpowder sample, the pressure discharge component discharges the gas in the combustion chamber into the pressure gas buffer tank; a data collection system collects and records the data output by the pressure sensor and the high-speed camera; and an operator can obtain related property parameters of the gunpowder sample based on analysis and calculation of recorded data. The invention can measure the combustion speed, flameout state and parameters of gunpowder under different pressures and pressure reduction rates and has the outstanding advantages of high measurement pressure, large regulating range of pressure reduction rate, low test cost and wide application scope.

Description

technical field [0001] 本发明属于火炸药技术领域,涉及一种火药非稳态燃烧特性测试装置,尤其涉及一种压力下降条件下的火药燃烧特性测试装置。 Background technique [0002] 在火药实际应用领域内,火药的燃烧大多是在非稳态下进行的,如点火过程、压力变化条件下的燃烧(振荡燃烧)、火药在气流中的燃烧和熄火等均是非稳态燃烧过程。非稳态燃烧可能被任何外界条件所引发,即任何破坏稳态燃烧关系的外界条件均可引起非稳态燃烧。在火药燃烧测试得到的各种p-t曲线中,可以很明显地发现非稳态燃烧现象,有的是由于压力急增引起的,有的是由于压力骤降引起的。其中最重要的是了解压力降低时的非稳态燃烧问题,这对保证火箭发动机的可靠性是非常有益的,因为压力的急降可能引起发动机熄火而停止工作,或出现喘燃的不正常现象。对于火炮而言,火炮发射药的整个燃烧过程也属于非稳态燃烧,即从点火开始就是非稳态,随后压力的急剧上升和达到最大压力点后压力急剧下降也是非稳态,此时的压力急剧下降有可能引起火药燃速的急剧下降,从而在火炮发射时出现火药燃烧不完全的现象。因此,研究火药在压力急剧下降情况下的火药燃烧情况具有现实意义。 [0003] 1961年,美国人在严格模拟实际发动机的实验燃烧实验室中,首次进行了系统的快速降压瞬变实验研究,通过突然打开燃烧室放气孔获得快速降压,从而获得了几种火药的熄火机理和结论。该燃烧室初始压力在3.4MPa~8.2MPa范围,环境压力最低达到466.4Pa。美国人的实验装置主要针对固体推进剂在火箭发动机应用出现的问题而建立的,没有将燃烧室初始压力、压力下降速率、最终的环境压力等进行扩展,因而其应用受到很大的限制。 Contents of the invention [0004] 本发明要解决的技术问题是,针对现有类似火药压力下降燃烧的实验装置存在的初始压力范围窄和最终火药熄火环境压力点少的问题,提供一种压力下降条件下的火药燃烧特性测试装置。该测试装置不仅可以在火药燃烧中止后控制火药气体的降压速率,而且可以控制和观察火药是否熄火、是否完全燃烧、是否断续燃烧等多种状态,同时还能够测量火药在不同压力下降区间的火药燃烧速度以及火药压力下降到大气压或其它设定压力点的燃烧行为。 [0005] 为解决上述技术问题,本发明提供的...

AI Technical Summary

Problems solved by technology

[0004] The technical problem to be solved by the present invention is to provide a propellant combustion characteristic testing device under pressure drop conditions in view of the problems of narrow initial pressure range and few pressure points in the final propellant extinguishing environment in existing experimental devices similar to propellant pressure drop combustion

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