快速建压过程药柱泊松比动态特性实验与仿真分析  

Experimental and simulation of dynamic characteristic of Poisson's ratio of propellant grain during rapid pressure process

作　　者：许方毅 职世君[1,2] 蒋鹏琛 白涛涛 张泽远[1,2] XU Fangyi;ZHI Shijun;JIANG Pengchen;BAI Taotao;ZHANG Zeyuan(China Airborne Missile Academy,Luoyang 471000,China;National Key Laboratory of Air-based Information Perception and Fusion,Luoyang 471000,China)

机构地区：[1]中国空空导弹研究院,洛阳471000 [2]空基信息感知与融合全国重点实验室,洛阳471000

出　　处：《固体火箭技术》2024年第6期905-912,共8页Journal of Solid Rocket Technology

摘　　要：固体火箭发动机药柱在低温点火过程中处于受围压状态,其泊松比随压强建立而发生变化。为探究建压过程泊松比的变化特性,开展了快速建压实验。根据体积变形等效关系建立了端羟基聚二丁烯(HTPB)推进剂泊松比随压强变化的数学模型,通过ABAQUS的USDFLD子程序对泊松比随压强变化的数学模型进行验证,并应用该模型对某管+星形药柱固体火箭发动机进行低温点火建压载荷下的药柱结构完整性分析。实验和仿真结果表明,压强的增长将引起HTPB复合固体推进剂内部孔隙率下降,泊松比因而呈现逐渐放缓的非线性增长趋势;采用变泊松比与定常泊松比所得到的计算结果存在差异;在低点火压强下,变泊松比药柱的最大主应变显著高于定常泊松比药柱。The Poisson's ratio of solid rocket motor propellant grain,which is under ambient pressure during low temperature ignition,is dynamic with the increase of pressure.In order to investigate the variation of Poisson's ratio with ambient pressure,a rapid pressure experiment system was carried out.The function form of the results was obtained by the equivalent relationship of volume deformation.The grain structural integrity of a tube and star solid rocket motor in the ignition and the pressure process was analyzed by three-dimensional viscoelastic finite element method,while the USDFLD subroutine of ABAQUS was used to load the variable Poisson's ratio function.The experimental and simulation results indicated that the increase of pressure would cause the internal porosity of the HTPB composite solid propellant to crease,and the Poisson's ratio would present a nonlinear increasing trend with the pressure process.There were differences between the simulation results of variable Poisson's ratio and constant Poisson's ratio.The maximum principal strain of variable Poisson's ratio grain was significantly higher than that of constant Poisson's ratio at low ignition pressure.

关 键 词：固体火箭发动机 药柱结构完整性 泊松比 快速建压实验 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]