固体火箭冲压发动机推进剂中多加入了大量的金属颗粒。以铝颗粒为研究对象研究了颗粒相对冲压发动机绝热层的热增量影响,分别对30µm与10µm的颗粒进行了数值模拟。数值模拟结果表明热增量的影响主要集中在进气道两侧。大颗粒引起的热增问题要远大于小颗粒。大颗粒由于惯性力的作用,轴向碰壁位置较小颗粒更靠近下游喷管。颗粒对壁面的热增量影响同颗粒速度也有很大关系,大量的液滴与壁面碰撞后破碎飞溅。由推进剂不完全燃烧产生的固相碳颗粒对发动机的冲蚀影响较小,实际中可以忽略。

High energy particles are added in solid ramjet propellant in order to enhance specific pulse. It is argued the effect of particles on insulator in heat transfer and impingement erosion. The particle in this paper is aluminum particle. The particles of two different diameters were argued in this paper. The result shows that heat transfer has been enforced in inlet-downstream area, and large particles make more heat transfer. Lots of particles break up while impinging on the insulator. Carbon particles generated by incomplete propellant burning performs little effect on insulator ablation.