关键词: 固体火箭发动机;斜切喷管;推力测试;激波;推力偏转角

Abstract: In order to study the characteristics of nozzle flow field and thrust for a solid rocket motor （SRM） with a structure of angle-cut nozzle， the conservative N-S equations are solved by using the second-order accuracy AUSM scheme， combining them with the Realizable k-ε turbulence model， and then the nozzle flow field and thrust characteristics are researched on the numerical simulation method for different degrees of angle-cut nozzle. At the same time， a thrust stand for the thrust test of angle-cut nozzle SRM is designed. The thrust curve of engine working process is adopted by this thrust stand， and it is compared with the numerical simulation results and the effectiveness and feasibility are verified for this competing method accordingly. Results show that the error between the thrust of angle-cut nozzle SRM obtained by the numerical simulation method and the test results is small. From the simulation and test results， it can be seen that there is an angle between the thrust line and the nozzle axis for 45° of angle-cut nozzle and it has been shown that the thrust deflection phenomenon exists. In addition， there are two high pressure areas which shock waves converged in the nozzle flow field， and the structural strength of the second shock wave is higher than that of the first shock wave. When the degree of angle-cut nozzle reaches 40°， with the increase of the degrees of angle-cut nozzle， the mass flow rate， the total thrust and the thrust deflection angle continuous decrease， but the decreasing trend slows down.

Key words: Solid rocket motor;Angle-cut nozzle;Thrust test;Shock wave;Thrust deflection angle