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。 The influence of high overload on the flow field and thermal insulation ablation of solid rocket motor was analyzed. A new research idea was put forward: numerical simulation method was used to predict three-dimensional two-phase flow field of engine, and a simulation experiment device of high overload flow field was established. Thermal insulation ablation experiment was carried out to establish a thermal insulation ablation model under high overload conditions. Based on this, the design of high thermal insulation engine layer and the prediction of ablation were developed. Among them, the key technology is simulation of high overcurrent field. The two schemes of particle addition method and elbow separation method are demonstrated. It is considered that elbow separation method is feasible in principle. In order to verify the feasibility of this scheme, the numerical simulation of two-phase flow in the elbow channel was carried out. The calculation results show that the elbow device has the function of aggregating the condensed particles to form a high-concentration particle flow.