Structure type and performance analysis of aerospike nozzle of solid rocket motor

Aiming at the application of three annular aerospike 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.