The simulations results show that the spoiler is available to make the fuel and the oxidizer coming from the former to stay in the cavity for a long time , to let the fuel and oxidizer mix and burn completely . since there is a high temperature zone forming by vortex in the middle of the motor , it required a restricted thermal protection . the plate with holes decreased the vortex function in the cavity , which could not promote the combustion efficiency , but to decrease temperature in the cavity and be benefit to thermal protection of the wall 计算结果分析表明:扰流板可以使燃料和氧化剂在扰流腔内的滞留时间加长,促进燃料与氧化剂的掺混燃烧,提高燃烧效率,但由于涡流在发动机的中间部位形成了高温燃烧区域,致使局部燃料和绝热层烧蚀速率增大,加大了热防护的难度;孔板结构减弱了扰流腔内回流区的漩流作用,不能增加推进剂燃烧效率,但可以使扰流腔内的温度降低,给壁面热防护带来好处。
In this paper , the backward simulation was summarizd at home andabroad , the characteristics of shell nosing were introduced , the theory and scheme of backward simul - ation of shell nosing was constructed , the determined methods of the boundary conditions were put forward in backward simulation for the processes of shell nosing 通过对固体火箭发动机燃烧室绝热层作用、种类及其隔热机理的研究,分析了绝热层材料的性能特点,论述了绝热层配方选择与结构设计的过程,并给出了较优的材料选择和结构设计方法,对绝热层的具体工艺实施阶段具有一定的指导意义
