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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 realize the pulse starting function of a solid rocket motor, a soft spacer structure (PSD) is designed to simulate the pressure bearing and opening process of the spacer layer and obtain the stress-strain field distribution. When the interlayer is subjected to the internal pressure of 10 MPa from the I pulse, the maximum principal stress and strain of the interlayer and the column are within the safe range, which proves the reliability of the structure. Using the extended finite element XFEM technology, Of the destruction process, the barrier in the II pulse 1.3MPa pressure to open, and open the form of reliable. The single pressure test and the single pressure test were designed. The accuracy of the numerical simulation was verified. The results showed that the pressure, the opening and the sealing performance of the structure all meet the design requirements. The interlayer structure can be applied to the actual pulse engine.