推进剂/包覆层界面脱粘率相关特性研究

Rate-dependent property of propellant and inhibitor interface debonding

固体火箭发动机(SRM)装药包覆界面性能对发动机安全工作意义重大。为研究改性双基(CMDB)推进剂/三元乙丙(EPDM)包覆层界面在不同受载速率下的脱粘情况,采用双悬臂梁(DCB)试件对包覆粘接界面进行了界面脱粘性能试验研究,获取了脱粘界面扩展过程中的加载点载荷-位移曲线。同时,构建了界面率相关内聚力模型(CZM),并采用Hooke_Jeeves优化算法反演识别出相关模型参数。通过对比多阶段加载实验及仿真结果曲线验证了模型的可靠性,结果表明,二者变化趋势基本一致,最大误差小于15%,所得结论对固体火箭发动机装药界面脱粘研究具有一定参考价值。

The interfacial property between propellant and inhibitor has a significant impact on the working stability of the solid rocket motor（SRM）.In order to investigate the debonding property of the interface between the composite modified double-base（CMDB）propellant and the ethylene-propylene-diene monomer（EPDM）inhibitor at different loading rates,an test research is conducted using double cantilever beam（DCB）specimen and the load-displacement curves are obtained.Meanwhile,an interface model is proposed based on the rate-dependent cohesive zone model（CZM）and the relevant parameters are inversed by the Hooke-Jeeves optimization algorithm.The model＇s accuracy is verified by comparing the multistage loading experiment curve with the simulation curve.The result shows that the change trend is consistent and the tolerance is less than 15%,which certificates that the interface model has some reference values for the debonding research in the solid rocket motor.