This study numerically simulated and investigated the flow field characteristics of a typical dual-pulse solid rocket motor with a soft pulse separation device through thermal insulation ablation under high-temperature dual-pulse erosion. The ablation rate of ethylene -propylene-diene monomer (EPDM) insulator was measured after the experiment. Experimental results were analyzed through scanning electron microscopy and microcomputed tomography. The ablation mechanism of the EPDM insulator under the operation conditions of a dual-pulse solid rocket motor was evaluated by analyzing the results. The results reveal that the internal flow field of the motor with a soft pulse separation device is uniform. The original charred layer existing on the EPDM insulator surface in the first pulse combustor is the decisive factor affecting the final ablation rate of the dual-pulse motor during the second pulse operation, and the ablation characteristic region is easily formed with the exfoliation of the charred layer. The ablation rate difference of the insulator increases with gas velocity.

本研究数值模拟研究了典型双脉冲固体火箭发动机在高温双脉冲侵蚀下通过绝热烧蚀的软脉冲分离装置的流场特性。实验结束后测量三元乙丙橡胶绝缘体的烧蚀率。通过扫描电子显微镜和微计算机断层扫描分析实验结果。通过分析结果，评价了双脉冲固体火箭发动机运行工况下三元乙丙绝缘子的烧蚀机理。结果表明，带软脉冲分离装置的电机内部流场是均匀的。第一次脉冲燃烧器中EPDM绝缘子表面存在的原始烧焦层是影响第二次脉冲运行时双脉冲电机最终烧蚀率的决定性因素，烧焦特征区很容易随着烧焦的剥落而形成。层。绝缘体的烧蚀率差异随着气体速度的增加而增加。