摘要
主要分析和试验研究了飞机结构的下陷结构的细节参数中下陷过度区尺寸Ｌ２、下陷曲率半径Ｒ与疲劳寿命的关系。通过采用应力场强法对下陷结构进行有限元计算和疲劳试验得知，Ｌ２的增加可延长结构的疲劳寿命，而Ｒ的小范围尺寸变化不会对寿命有太大影响。
The relationship between the fatigue life and the length L 2, the curvature radius R of the step detail in the aircraft structure are mainly studied by experiment and analyzed in this paper. From the finite calculation by the stress field intensity method and the fatigue experiment of the step detail, it can be resulted that the increasement of L 2 can extend the fatigue life of the structure detail and the variance of R in small scope will not affect the fatigue life greatly. This conclusion is also supported by fatigue experiments.
出处
《机械强度》
CAS
CSCD
北大核心
1999年第1期61-62,68,共3页
Journal of Mechanical Strength
