航空学报 > 2022, Vol. 43 Issue (6): 526134-526134   doi: 10.7527/S1000-6893.2022.26134

大型飞机整体壁板损伤断裂分析方法

张志楠1, 宁宇1,2, 庄茁3, 王恒4, 秦剑波1, 严红1   

  1. 1. 航空工业第一飞机设计研究院, 西安 710089;
    2. 北京航空航天大学 航空科学与工程学院, 北京 100083;
    3. 清华大学 航天航空学院, 北京 100084;
    4. 空军研究院 航空兵研究所, 北京 100076
  • 收稿日期:2021-07-20 修回日期:2022-04-08 出版日期:2022-06-15 发布日期:2022-04-06
  • 通讯作者: 宁宇,E-mail:ningyu89@163.com E-mail:ningyu89@163.com
  • 基金资助:
    国家自然科学基金(10272060)

Analysis method for damaged and fractured integral panel of large aircraft

ZHANG Zhinan1, NING Yu1,2, ZHUANG Zhuo3, WANG Heng4, QIN Jianbo1, YAN Hong1   

  1. 1. The First Aircraft Design and Research Institute of AVIC, Xi'an 710089, China;
    2. School of Aeronautic Science and Engineering, Beihang University, Beijing 100083, China;
    3. School of Aerospace Engineering, Tsinghua University, Beijing 100084, China;
    4. Air Arm Labaratory, PLA Airforce Research Institute, Beijing 100076, China
  • Received:2021-07-20 Revised:2022-04-08 Online:2022-06-15 Published:2022-04-06
  • Supported by:
    National Natural Science Foundation of China (10272060)

摘要: 通过对大型飞机整体壁板结构的损伤断裂特性分析,在壳体断裂力学统一计算理论框架下,将扩展有限元应用于大型飞机整体加筋壁板结构损伤断裂计算;实现了大尺寸加筋板壳结构断裂参数的精确求解;通过采用基于应力强度因子和能量释放率的三维壳体断裂准则,建立了以结构重量、裂纹扩展长度和壳体剩余寿命等多参数设计目标的大型飞机整体壁板损伤断裂分析方法,以及综合考虑壁板厚度、加筋截面面积和间距的参数优化方法,并给出了工程试验件的设计与验证结果。

关键词: 大型飞机, 整体壁板, 壳体断裂, 止裂特性, 参数设计

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

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