采用扫描电镜原位拉伸试验观察固体火箭发动机粘接界面试件在拉伸过程的变形和破坏过程，分析了载荷作用下界面失效模式和机理；依据粘接界面细观结构，建立了界面的细观数值模型，考虑了其细观损伤特点，在推进剂内部颗粒与基体之间以及推进剂/衬层之间引入界面元，对界面细观变形和破坏过程进行了数值模拟。结果表明， 在外界应变5%时，表现为非均质材料内部应力分布不均，随应变的增加，推进剂内部脱湿形成的微孔洞不断扩展，最终导致界面破坏，界面拉伸失效过程表现为损伤的起裂和扩展，是推进剂内部脱湿和粘接界面脱粘共同作用的结果；界面元能有效地模拟粘接界面的脱粘过程，细观数值计算结果与试验结果吻合，正确反映了粘接界面在拉伸过程中细观损伤萌生与扩展的规律。

Three-dimensional flows of variable-burning rate propellant solution in the screw aresimulated using the POLYFLOW indifferent operating conditions. Simulation results indicatethat the volume flow of corematerial is directly proportional to the screw velocity. When thescrew velocity is different, the high frequencyfluctuation values of the volumeflow rate arebetween 0.02% and 0.03%. The fluctuation values of the volume flow rate are directly proportional to the fluctuationvalues of the screw velocity.The volume flow rate of the core material aredirectly proportional to the entrance pressure. When the entrance pressure is different,the high frequency fluctuation values of the volume flow rate are between 0.024%and 0.026%. The fluctuation values of the volume flow rate rapidly increasewith the entrance pressureincrease, when the fluctuation value of entrancepressure is greater.