摘要
针对导弹头罩分离的安全性需要设计了两种导弹头罩分离方案,即内冲压四分旋转式分离和内冲压四分平推式分离。采用结构重叠网格方法求解Euler方程耦合6自由度刚体运动方程,对两种方案的头罩分离过程进行数值仿真分析,获得了两种方案分离过程的载荷历程、运动轨迹、分离线速度和角速度等工作技术参数。分析比较了两种方案的技术特征,为头罩分离机构方案提供可行性论据以满足构形设计与载荷设计要求。
It designs two schemes of shroud separation for missile, that is, inner air-pressed fourfold rotating separation and inner air-pressed fourfold shoot-off separation. With moving chimera grid technology,Euler fluid equation and 6DOF rigid kinematical equations are coupled and solved on the CFD-FUS- TRAN software platform. Both the processes of the shroud separations are simulated numerically,and the loading history,separating track and speed,as well as rotating angle speed about body axis are all obtained for the two schemes. Based on the analyses of these technical parameters ,the features of both shroud separations are compared,which provides important evidence for the mechanical configuration design scheme and loading requirement.
出处
《机械设计与制造》
北大核心
2008年第9期8-10,共3页
Machinery Design & Manufacture
