In order to study the second pulse ignition transient of a dual pulse solid rocket motor,a multi-physic solver is developed.The governing equations for unsteady compressible fluid flow are solved with dual time LU-SGS(lower upper symmetric Guass seidel)iterative algorithm by finite volume method.The conjugate heat transfer strategy is employed to calculate the propellant surface temperature.A finite element method is used to discretize the structural dynamic equation in space,whereas the temporal time integ...
【基金】
江苏省普通高校学术学位研究生科研创新计划(KYZZ15_0113)~~
【更新日期】
2017-05-10
【分类号】
V435
【正文快照】
网络出版地址:www.cnki.net/kcms/detail/11.1929.V.20160801.1034.002.html引用格式:李映坤,韩珺礼,陈雄,等.基于多物理场耦合的双脉冲发动机点火过程数值模拟[J].航空学报,2017,38(4):120409.LIY K,HAN J L,CHEN X,et al.Numerical simulation of the ignition transient of
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