摘要
为了分析固体火箭发动机点火瞬态工作过程,通过采用基于子循环-预测校正的紧耦合算法,研究高效的耦合器耦合计算流体动力学代码及计算结构动力学代码,对某翼柱型装药固体火箭发动机点火瞬态进行数值模拟,结果表明:翼柱型发动机点火过程中,尾部药柱壁面最开始点燃,同时火焰快速向翼槽和头部传播,翼段是最容易发生破坏的地方;紧耦合算法能有效地应用于固体火箭发动机的研究。
For analyzing the process about the ignition of Solid Rocket Motor （SRM）, appropriate 3D SRM fluid-structure interaction simulation system was constructed by using the tightly coupled methods with subcycling based predict-correct scheme which coupled the CFD codes and the CSD codes with efficient coupler. The ignition transient of SRM with finocyl grain was simulated by this system. Simulation results showed that during the ignition proceeds, the tail of grain was ignited first, then the flame propagating to the fin-slot and the head of grain, and the fin part will broke damage easily. The research results show that the tightly coupling method is better for researching the SRM.
出处
《计算力学学报》
EI
CAS
CSCD
北大核心
2011年第B04期84-89,共6页
Chinese Journal of Computational Mechanics
基金
国家安全重大基础研究"973"(973-61338)资助项目
