摘要
为了研究翻转条件下固体火箭发动机燃烧室药柱-衬层界面力学响应、探究现有的固体火箭发动机翻转方式合理性,采用试验与数值模拟相结合的方法,对药柱-衬层界面在不同翻转时间内应力应变及位移变化进行分析。研究结果表明:翻转可以一定程度上消除固化降温产生的残余应力;匀角速度翻转产生的应力相较其余翻转方式更为平缓。在翻转过程中,发动机两端人工脱粘层底部界面是其可靠性分析重点关注的对象。其界面危险点位于上部前人工脱粘层底部边缘和其相对应翼槽底部边缘之间的区域;翻转条件下界面的最大Mises应力为0.0455MPa,设计的翻转方式能够满足界面安全裕度需求。
In order to study the dynamic response of solid rocket motor combustor grain-liner interface under flip condition and explore the rationality of existing flip way,the stress and strain,as well as the displacement of solid rocket motor grain-liner interface under different space of flip time were analyzed by a combination of experiments and numerical simulation method.It is demonstrated that flipping could eliminate the residual stress caused by cooling process after curing in a certain extent.The stress produced by the flip under uniform angular velocity is more gentle than the others.The both stress-release boot end face of motor should be focused on,while the danger point of solid rocket motor interface under flip condition is located in the area between the bottom edge of the upper front stress-release boot and the bottom edge of its corresponding fin-slot.For the condition of existing flip way,it is demonstrated that the maximum Mises stress of interface under flip condition is0.0455MPa,which demonstrates that the required margin of safety is satisfied.
作者
贾乐凡
史宏斌
沙宝林
JIA Le-fan;SHI Hong-bin;SHA Bao-lin(Xi’an Aerospace Solid Propulsion Technology Institute,Xi’an 710025,China)
出处
《推进技术》
EI
CAS
CSCD
北大核心
2022年第12期390-396,共7页
Journal of Propulsion Technology
