摘要
导弹在高空中作机动飞行时易出现内弹道异常现象,严重时可能导致飞行任务失败。为了了解横向过载对固体火箭发动机内弹道性能的影响,对飞行过载下发动机内弹道性能进行更好地预示,建立了一种非均匀燃面退移离散坐标求解方法。从简单的内孔燃烧管型装药到常用的复杂星孔药型,利用离散坐标求解方法模拟横向过载下推进剂的燃面退移,得出了不同过载下的燃面退移规律,计算了燃面面积的变化情况;同时,将不同微元处的面积和燃速相对应,预示了横向过载下发动机的内弹道特性。结果表明,横向过载导致推进剂燃烧发生偏心,燃烧室压强提高,绝热层提前暴露。100 g横向过载下,燃烧室压强增加4%,压强峰值出现时间0.4 s,绝热层暴露时间增加1.6 s;星孔药型燃面的下降段数等于星角数N/2+1。分析了横向过载对燃面退移及发动机内弹特性的影响,对发动机设计具有指导意义。
The abnormal phenomena of internal ballistics is easy to occur for most of the missiles flying at high altitudes,leading to mission failure under serious cases.In order to understand the influence of lateral overload on the internal ballistic performance of solid rocket motor(SRM)and better predict the internal ballistic performance of SRM under flight overload,a discrete coordinate solution method for non-uniform burning surface regression was established.From the simple inner hole combustion tube grain to the common complex star hole grain,the discrete coordinate solution method was used to simulate the burning surface regression under lateral overload,and the regression law of the burning surface was obtained.At the same time,the areas of different micro units were corresponding to the burning rate,which can predict the internal ballistic characteristics of the SRM under lateral overload.The results show that the lateral overload leads to eccentric combustion,the pressure of the combustion chamber increases,and the insulation is exposed in advance.Under 100 g lateral overload,the combustion chamber pressure increases by 4%,pressure peak occurs at 0.4 s,and exposure time of the insulation increases by 1.6 s.The number of drop sections of the burning surface of star hole grain is equal to the number of star angles N/2+1.The influence of lateral overload on surface regression and interior ballistic performance of SRM is analyzed,which has guiding significance for SRM design.
作者
田忠亮
李军伟
黄刚
王向港
王宁飞
TIAN Zhongliang;LI Junwei;HUANG Gang;WANG Xianggang;WANG Ningfei(Schoof of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China;Sichuan Aerospace System Engineering Research Institute,Chengdu 610199,China)
出处
《固体火箭技术》
CAS
CSCD
北大核心
2022年第4期512-521,共10页
Journal of Solid Rocket Technology
关键词
横向过载
燃面退移
离散
内弹道
lateral overload
burning surface regression
discretization
interior ballistics
作者简介
田忠亮(1997—),男,硕士生,研究方向为过载条件下固体发动机内弹道特性。E-mail:18811370679@163.com;通讯作者:李军伟(1978—),男,副教授,研究方向为固体火箭发动机不稳定燃烧、液体燃料微尺度燃烧、固体火箭发动机设计与仿真技术等。E-mail:david78lee@sina.com。
