Abstract: The mechanism was analyzed for the influences of high acceleration on the internal flow field and the ablation of insulator of SRM. A new method was developed which includes two parts. The first part is to solve the three-dimension two phase flow field of SRM under high acceleration condition by numerical simulation method and the second is to establish the ablation model of insulator by ablation experiment using flow field simulation equipment. Based on these studies the technique of insulator design and ablation prediction for SRM under high acceleration condition can be developed. The key technique is to develop a flow field simulation experimental method. Several projects were discussed and the siphon device seemed to be more feasible. To demonstrate the feasibility of this method, two phase flow field in siphon was analyzed by using numerical simulation method. The results showed that the siphon device can congregate particles to generate two phase flow with high density particles.

Key words: High acceleration;Solid propellant rocket engine;Two phase flow;Numerical simulation;Proposal research

摘要： 分析了高过载对固体火箭发动机流场和绝热层烧蚀的影响规律,提出一种新的研究思路:采用数值模拟方法来预示发动机三维两相流场,建立高过载流场模拟实验装置,开展绝热层烧蚀实验,建立高过载条件下的绝热层烧蚀模型,在此基础上发展高过载发动机绝热层设计和烧蚀预示方法。其中关键技术是高过载流场的模拟,对粒子加入法和弯管分离法两种方案进行了论证,认为弯管分离法原理上是可行的。为了验证这种方案的可行性,开展了弯管通道两相流的数值模拟研究,计算结果表明弯管装置具有使凝相粒子聚集形成高浓度粒子流的功能。

关键词: 高加速度;固体推进剂火箭发动机;二相流;数值仿真;方案论证