摘要
为得到双脉冲发动机隔舱结构关键部件金属膜片适宜结构,通过圆板大挠度理论和断裂力学理论推导出金属膜片预制缺陷处应力强度因子计算公式,得到金属膜片在内压作用下的设计方法,建立了膜片破坏压强与结构尺寸之间定量关系,并通过6次膜片动态破坏单项实验验证了其正确性。在此基础上,利用缩比发动机分别开展了隔舱热流承压、热流打开、热流联合实验以进一步考核隔舱的工作特性。结果表明:所导出的金属膜片设计方法与实验结果较为一致,平均误差约4.394%,可以用于脉冲发动机膜片具体结构尺寸设计;隔舱承压、密封、打开、消融性能良好,可以较好满足双脉冲发动机使用要求。
Circular plates with large deflection and fracture mechanics theory were employed to investi- gate calculating formula of stress intensity factor of prefab gap at the condition of inner pressure, and the re- lationship between the opening pressure and physical dimension of hard pulse separation device （PSD） in order to achieve the feasible configuration of metal diaphragm, which plays the important role in dual-pulse solid rocket motor. Moreover, six monomial tests of metal diaphragm were conducted to validate the compu- ting precision of designing formula. In addition, three kinds of scale experiments, namely, the compres- sive, opening and associated test, were performed to explore working characters of pulse separation device. The results indicate that the error between the experimental conclusions and designing results is 4. 394% and the method can be applied to confirm the physical dimension of metal diaphragm. The performances of bearing capacity,seal,working characters and ablation are demonstrated and the PSD agrees well with the requirements.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2013年第8期1115-1120,共6页
Journal of Propulsion Technology
关键词
实验研究
设计方法
金属膜片
隔舱结构
双脉冲发动机
Experimental investigation
Designing method
Metal diaphragm
Pulse separation de-vice
Dual-pulse motor
