王磊,李鹤,许良,回丽. 某飞机腹板构件结构改进及试验验证[J]. 航空制造技术, 2018, 61(23/24): 64-68. WANG Lei, LI He, XU Liang, HUI Li. Structure Improvement and Experimental Validation of Aircraft Web Plate[J]. Aeronautical Manufacturing Technology, 2018, 61(23/24): 64-68.
WANG Lei, LI He, XU Liang, et al. Structure Improvement and Experimental Validation of Aircraft Web Plate[J]. Aeronautical Manufacturing Technology, 2018, 61(23/24).
王磊,李鹤,许良,回丽. 某飞机腹板构件结构改进及试验验证[J]. 航空制造技术, 2018, 61(23/24): 64-68. WANG Lei, LI He, XU Liang, HUI Li. Structure Improvement and Experimental Validation of Aircraft Web Plate[J]. Aeronautical Manufacturing Technology, 2018, 61(23/24): 64-68. DOI: 10.16080/j.issn1671–833x.2018.23/24.064.
WANG Lei, LI He, XU Liang, et al. Structure Improvement and Experimental Validation of Aircraft Web Plate[J]. Aeronautical Manufacturing Technology, 2018, 61(23/24). DOI: 10.16080/j.issn1671–833x.2018.23/24.064.
For fatigue failure occurring in a stiffener of an aircraft web plate earlier
the structure of the web plate is improved by means of simulation analysis and experimental validation. Firstly
the web plate dynamic model is set up
the causes of fatigue failure are analyzed by calculating the stress distribution and fatigue life of the web plate. Secondly
an improvement design is conducted on the original structure of the web plate based on principle of stiffness distribution. The finite element calculation result shows that improved design decreases the maximum stress of the stiffener and improves the fatigue life of the web plate. Finally
by comparing the fatigue tests of original structure and improved structure
the results verify the accuracy of finite element model and the effectiveness of the improvement.