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为对比不同喷管形式的固体火箭发动机热安全性,对潜入式和非潜入式喷管固体火箭发动机采用二维轴对称模型和准定常方法进行两相内流场模拟和分析。采用6种不同粒子直径,分别就6组不同状态条件进行计算。对比结果表明,撞击在非潜入式发动机后封头壁面上的粒子数目较多,粒子质量流率、平均速度以及动量比撞击在潜入式发动机上的超出数倍,最大达到20倍,因此粒子对壁面的撞击更为直接,撞击侵蚀更为严重。在其他条件相同的情况下,较大的壁面恢复系数会给予撞击在壁面上的粒子更多的动能,粒子与壁面的接触增加,加重了壁面的撞击侵蚀。
In order to compare the thermal safety of solid rocket motors with different nozzle configurations, a two-dimensional axisymmetric model and a quasi-steady method were used to simulate and analyze the two-phase flow field in submerged and non-submerged nozzle solid rocket motors. Using six different particle diameters, six groups of different state conditions were calculated. The comparison results show that the number of particles impinging on the headwall of non-submersible engine is large, and the particle mass flow rate, average velocity and momentum ratio exceed several times the impact on submerged engine up to 20 times, so particle pair The impact of the wall is more direct, impact erosion is more serious. Under other conditions, the larger wall recovery factor will give more kinetic energy to the particles colliding with the wall surface, and the contact between the particles and the wall surface increases, which aggravates the impact erosion of the wall surface.