Aiming at the application of three annular gerospike nozzle structure typies to solid rocket motor, the finite volume method is adopted to get the numerical simulation results. Through flow structure analysis and performance comparison, the results show that the multi-unit annular clustered aerospike nozzle with small cell gap has high thrust efficiency during the flight, which is fit for the basic structure of plug nozzle in solid propellant rocket engine. And then, the particle trajectory model is used to simulate the two-phase flow of 20 units annular clustered aerospike nozzle. Due to the existence of particles, flow field shape of nozzle can be changed,and the mainstream distribution of two-phase flow is larger than that of pure gas flow. The Maｃh number is delayed by particles in two-phase flow filed,thｅ larger particle diameter is,the lower nozzle efficiency is. In this paper,the performance of 20 units annular clustered aerospike nozzle with diameter 10 μm particles is decreased about 9％ relative to pure gas flow filed.%针对可应用于固体火箭发动机的3种环状塞式喷管构型,采用有限体积法进行计算,通过流场结构分析和性能比较,表明单元间隙较小的多单元环簇型塞式喷管在整个飞行高度下均具有较高的推力效率,适合作为固体火箭发动机用塞式喷管的基本构型.在此基础上,采用颗粒轨道模型模拟了20单元环簇型塞式喷管的两相流场,由于颗粒的存在使得两相流场较纯气相的形态有较大改变,主流分布范围变大,马赫数产生滞后,且颗粒直径越大喷管效率越低,颗粒直径10μm时的喷管性能相对纯气相下降9%左右.
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