摘要
为了实现固体火箭发动机的脉冲启动功能,设计了一种软质隔层结构(PSD),数值模拟了隔层的承压及打开过程,得到其应力应变场分布。当隔层承受来自I脉冲10MPa内压作用时,隔层及药柱的最大主应力及应变都在安全范围内,从而证明了该结构承压可靠性;利用扩展有限元XFEM技术模拟了隔层的破坏过程,隔层在II脉冲1.3MPa内压下打开,且打开形式可靠。设计了承压和打开单项试验,验证了数值模拟的准确性,并说明该结构承压、打开及密封性能均满足设计要求,隔层结构可以应用于实际的脉冲发动机之中。
In order to achieve the pulse start of solid rocket motor,one soft pulse separation device（PSD） was designed. The process of bearing pressure and opening up was simulated, and its strain and stress distribution was obtained. When the PSD bore 10MPa pressure coming from I pulse chamber, the max stress and strain of PSD or grain were smaller than the materi- al limits,which proved that the structure of PSD was reliable. The XFEM was used to simulate its failure process,and the PSD was opened up reliably under 1.3MPa pressure. The verification monomial test was designed to verify the accuracy of simula- tion,and the bearing capability and failure form of PSD were satisfied with the design requirements. The PSD can be applied to pulse motor. The simulation techniques ,test methods and conclusions are useful for designing pulse solid rocket motor.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2012年第5期790-794,830,共6页
Journal of Propulsion Technology
