某型高能固体火箭发动机烤燃性能研究  

Research on the Cook-off Performance of High Energy Solid Rocket Motor

作　　者：徐松林[1] 刘文一[1] 高庆福[2] Xu Song-lin;Liu Wen-yi;Gao Qing-fu(Unit 91 of PLA 91550, Dalian, 116023;Space Science and Engineering College in National University of Defense Technology, Changsha, 410073)

机构地区：[1]91550部队91分队 [2]国防科技大学航天科学与工程学院

出　　处：《导弹与航天运载技术》2017年第6期24-27,共4页Missiles and Space Vehicles

摘　　要：为研究某型高能固体发动机的热安全性,建立了发动机在火烧环境下的有限元计算模型,数值模拟了发动机及装药在不同烤燃工况下的温度分布和爆炸延迟期。研究表明,大型发动机烤燃特性与小型发动机呈现相同规律,热扩散速率在快速烤燃工况下较大,温度梯度在慢速烤燃工况下较大,烤燃速率对推进剂起始反应位置有一定影响。发动机尺寸和快烤环境温度对其热安全性影响较大,发动机尺寸减小和温度升高均导致推进剂点火延迟时间明显降低。The finite-element model of high energy solid rocket motor （SRM） is established to investigate the thermal safety of SRM when it is cooked-off,the temperature distribution and the explosion delay period of propellant were numerical simulated under fast cook-off mode and slow cook-off mode.It proves that the scale of motor have no obvious influence on the cook-off characteristic,the thermal diffusivity under fast cook-off mode is greater than that under slow cook-off mode,but the temperature gradient is negative;the reaction position of propellant is different when it achieved critical temperature.The scale of SRM and the outside temperature have obvious influence on the thermal safety;the decreased of scale or increased of temperature will reduce the explosion delay period of SRM dramatically.

关 键 词：固体火箭发动机 高能装药 烤燃 爆炸延迟期 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程]