某制导炮弹尾段壳体发射强度仿真

The Launch Strength Simulation Computation of a Guided Projectile's Tail Shell

充分利用UG三维建模功能和ANSYS仿真功能,建立了某制导炮弹尾段壳体的有限元模型,仿真计算弹体在受到最大膛压260MPa时,并在高转速的情况下,弹体尾段壳体处应力、应变分布情况,为某制导炮弹尾段壳体结构设计和优化提供依据,以达到减少试验费用,缩短研制周期的目的。

By making full use of the functions of UG and ANSYS, the finite element model of the guided projectile＇ s tail shell was built at first, then, the stress-strain distribution of the tail shell with the simulation computation was obtained when the projectile was rotating and its bearing bore pressure reached into 260MPa. Finally, the purpose of decreasing the test cost and shortening the development cycle was realized by making the reference to the computed results for optimizing the structure design of the guided projectile＇ s tail shell.