Research on Loading Method of Simulation Ignition Shock Testing for Solid Rocket Propellant at Low Temperature

doi:10.3969/j.issn.1000-1093.2018.04.011

Abstract

Abstract: A simulation ignition shock test device with controllable pressure is designed using propellant quenched combustion experimental principle to deal with the structure failure problem of solid propellant at low temperature, which can be caused by the coupling effect of high speed loading. The simulation ignition shock against propellant is made by the gas produced from the combustion of ignition material. The ignition pressure is calculated using the formula of chamber volume and weight of ignition material, and the quenched pressure is controlled by rupture disc. The ignition pressure and ignition mode have great influence on the gas pressurization rate according to p-t and dp/dt-t curves of the ignition shock process. Pressurization rate can be up to 2 000 MPa/s in weak ignition case and 5 000 MPa/s in strong ignition case, which is higher than real motor ignition rate. The pressure is controllable (the pressure deviation is less than ±5%) in repeated experiments. The testing is expected to be used to simulate the ignition shock process for solid propellant at low temperature. Key

Key words: solidrocketpropellant, ignitionshock, lowtemperature, pressurizationrate

CLC Number:

V512⁺.3

ZHANG Huai-long, JIAN Xiao-xia, ZHOU Wei-liang, XIAO Le-qin. Research on Loading Method of Simulation Ignition Shock Testing for Solid Rocket Propellant at Low Temperature[J]. Acta Armamentarii, 2018, 39(4): 717-723.

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第39卷
第4期2018 年4月兵工学报ACTA
ARMAMENTARIIVol.39No.4Apr.2018

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