摘要
为评估翼柱型装药固体发动机在低温贮存后点火过程的结构完整性,采用了仿真计算和试验相结合的方法,开展了发动机在低温贮存、燃气内压联合作用下装药结构的应力、应变与位移场分布的计算。结果表明:翼槽过渡段是应变较大处,在温度载荷下药柱翼槽过渡段应力最大为280.6 kPa、应变最大10.85%;在温度载荷和压强载荷联合作用下药柱翼槽过渡段的应力最大为3.816 MPa、应变最大21.72%。安全系数最小值为1.93时,翼柱型装药结构完整性满足要求。
To evaluate the structural integrity of a solid rocket motor with a finocyl grain during ignition after low-temperature storage,this paper proposes a method integrating simulation and experimental validation.The approach calculates the stress,strain,and displacement field distributions in the finocyl grain under combined thermal-mechanical loads.The results show that the finocyl grain transition section exhibits the highest strain concentration,and the maximum stress and strain are 280.6 kPa and 10.85%respectively under the thermal loading.Under the combined action of thermal loading and pressure,the maximum stress and strain are 3.816 MPa and 21.72%respectively.When the minimum safety factor is 1.93,the structural integrity of solid rocket motor meets requirements.
作者
祝庆龙
乌日娜
薛潇潇
方常青
陈俊
ZHU Qinglong;WU Rina;XUE Xiaoxiao;FANG Changqing;CHEN Jun(Shanghai Aerospace Power Technology Research Institute,Shanghai 201109,China)
出处
《航天工程大学学报》
2025年第5期47-52,共6页
Journal of Space Engineering University
关键词
装药结构完整性
翼柱型装药
低温点火
固体火箭发动机
structural integrity of grain
finocyl grain
low temperature ignition
solid rocket motor
