对于结构塑性动力响应问题,一般的是先从静态极限分析的完全解出发,假设其速度场,然后根据各种条件进行求解。本文以圆板塑性动力响应问题为例,给出一种不同的求解方法,即联合运用拉普拉斯变换和加权余量法进行分析和求解。先通过拉普...对于结构塑性动力响应问题,一般的是先从静态极限分析的完全解出发,假设其速度场,然后根据各种条件进行求解。本文以圆板塑性动力响应问题为例,给出一种不同的求解方法,即联合运用拉普拉斯变换和加权余量法进行分析和求解。先通过拉普拉斯变换将薄板的动力问题转化为静力问题,然后根据弯矩 M 和挠度 w 的边界条件分别假设试函数,再应用加权余量法进行求解。展开更多
Aim To analyze dynamic failure of aerospace strutures subjected lateral impulsive loading. Methods Structures were modeled as rigid-perfectly plastic free-free stepped beams. Basic equations of motion un set up f...Aim To analyze dynamic failure of aerospace strutures subjected lateral impulsive loading. Methods Structures were modeled as rigid-perfectly plastic free-free stepped beams. Basic equations of motion un set up for analysis. Results Final pat deformation and rigid motion solutions were determined for a uniform impulsive loading. The critical rupture conditions for a space shuttle and a missile were obtained. Conclusion Failure is possible for aerospace structures under a uniform impulsive loading, but it is mere difficult in space.展开更多
文摘对于结构塑性动力响应问题,一般的是先从静态极限分析的完全解出发,假设其速度场,然后根据各种条件进行求解。本文以圆板塑性动力响应问题为例,给出一种不同的求解方法,即联合运用拉普拉斯变换和加权余量法进行分析和求解。先通过拉普拉斯变换将薄板的动力问题转化为静力问题,然后根据弯矩 M 和挠度 w 的边界条件分别假设试函数,再应用加权余量法进行求解。
文摘Aim To analyze dynamic failure of aerospace strutures subjected lateral impulsive loading. Methods Structures were modeled as rigid-perfectly plastic free-free stepped beams. Basic equations of motion un set up for analysis. Results Final pat deformation and rigid motion solutions were determined for a uniform impulsive loading. The critical rupture conditions for a space shuttle and a missile were obtained. Conclusion Failure is possible for aerospace structures under a uniform impulsive loading, but it is mere difficult in space.
