大型飞机整体壁板损伤断裂分析方法

doi:10.7527/S1000-6893.2022.26134

Abstract

Abstract: The structure characteristics of the large aircraft integral panel is analyzed. Based on the unified theory of computation of fracture mechanics of shells, the continuum-based shell element of extended finite element method is applied for simulating the damage and fracture in the three-dimensional integral panel in this paper. The fracture parameters are solved accurately for large-size and variable cross-section combined shell structures. Based on the stress intensity factor and energy release rate principle of the fracture arrest criterion in three-dimension shells, a fracture analysis method is proposed for the design target, including a few main parameters such as structural weight, the length of crack extension, and the residual strength in the initial crack growth panel for double-spacing and integral stiffened shell. The geometric optimization method for wallboard thickness, cross section area and interval of reinforce bars are also developed. Results of the design and verification of experiment samples are given.

Key words: large aircraft, integral panel, shell fracture, crack-arrest property, parameter design

CLC Number:

V222
V215.5

ZHANG Zhinan, NING Yu, ZHUANG Zhuo, WANG Heng, QIN Jianbo, YAN Hong. Analysis method for damaged and fractured integral panel of large aircraft[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(6): 526134-526134.

References

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Analysis method for damaged and fractured integral panel of large aircraft

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