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

[1] 李亚智, 张向. 整体加筋壁板的破损安全特性与断裂控制分析[J]. 航空学报, 2006, 27(5):842-846. LI Y Z, ZHANG X. An analysis of fail-safety and fracture control of integrally stiffened panels[J]. Acta Aeronautica et Astronautica Sinica, 2006, 27(5):842-846(in Chinese).
[2] 殷之平, 黄其青, 傅祥炯. 变厚度壁板损伤容限特性研究[J]. 应用力学学报, 2005, 22(4):665-668, 685. YIN Z P, HUANG Q Q, FU X J. Damage tolerance behavior of plates with variable thickness[J]. Chinese Journal of Applied Mechanics, 2005, 22(4):665-668, 685(in Chinese).
[3] 肖群力, 黄其青, 殷之平. 典型机翼整体壁板止裂特性分析及优化设计[J]. 机械强度, 2012, 34(1):92-96. XIAO Q L, HUANG Q Q, YIN Z P. Analysis of crack-arrest property and optimum design for typical integrally stiffened panel[J]. Journal of Mechanical Strength, 2012, 34(1):92-96(in Chinese).
[4] 田硕, 尚建勤, 盖鹏涛, 等. 带筋整体壁板预应力喷丸成形数值模拟及变形预测[J]. 航空学报, 2019, 40(10):422847. TIAN S, SHANG J Q, GAI P T, et al. Numerical simulation and deformation prediction of stress peen forming for integrally-stiffened panels[J]. Acta Aeronautica et Astronautica Sinica, 2019, 40(10):422847(in Chinese).
[5] ZHUANG Z, CHENG B B. A novel enriched CB shell element method for simulating arbitrary crack growth in pipes[J]. Science China Physics, Mechanics and Astronomy, 2011, 54(8):1520-1531.
[6] ZENG Q L, LIU Z L, XU D D, et al. Modeling stationary and moving cracks in shells by X-FEM with CB shell elements[J]. Science China Technological Sciences, 2014, 57(7):1276-1284.
[7] WANG H, LIU Z L, XU D D, et al. Extended finite element method analysis for shielding and amplification effect of a main crack interacted with a group of nearby parallel microcracks[J]. International Journal of Damage Mechanics, 2016, 25(1):4-25.
[8] 《航空制造工程手册》总编委会. 航空制造工程手册[M]. 北京:航空工业出版社, 1992:397-400. 《Aeronautical Manufacturing Technology Manual》 Chef Editorial Committee. Aeronautical manufacturing technology manual[M]. Beijing:Aviation Industry Press, 1992:397-400(in Chinese).
[9] 曾元松, 黄遐. 大型整体壁板成形技术[J]. 航空学报, 2008, 29(3):721-727. ZENG Y S, HUANG X. Forming technologies of large integral panel[J]. Acta Aeronautica et Astronautica Sinica, 2008, 29(3):721-727(in Chinese).
[10] ZENG Q L, LIU Z L, XU D D, et al. Modeling arbitrary crack propagation in coupled shell/solid structures with X-FEM[J]. International Journal for Numerical Methods in Engineering, 2016, 106(12):1018-1040.
[11] 《民机结构耐久性与损伤容限设计手册》编委会. 损伤容限设计与分析[M]. 北京:航空工业出版社, 2003:63-283. 《Handbook of civil aircraft structural durability and damage tolerance design》Editorial Committee. Damage tolerance design and analysis[M]. Beijing:Aviation Industry Press, 2003:63-283(in Chinese).
[12] PARIS P, ERDOGAN F. A critical analysis of crack propagation laws[J]. Journal of Fluids Engineering, Transactions of the ASME, 1963, 85(4):528-533.
[13] FOSSATI M, COLOMBO D, MANES A, et al. Numerical modelling of crack growth profiles in integral skin-stringer panels[J]. Engineering Fracture Mechanics, 2011, 78(7):1341-1352.
[14] 王生楠, 张妮娜, 秦剑波. 整体机身结构纵向裂纹转折与止裂特性分析[J]. 西北工业大学学报, 2007, 25(4):472-477. WANG S N, ZHANG N N, QIN J B. Exploring engineering significance of turning of longitudinal crack in integral airframe structure[J]. Journal of Northwestern Polytechnical University, 2007, 25(4):472-477(in Chinese).
[15] 张志楠. 机身壁板损伤容限试验总结报告[R].西安:航空工业第一飞机设计研究院,2014:18-20. ZHANG Z N. Summary report of damage tolerance test for fuselage panel[R]. Xi'an:First Aircraft Design and Research Institute of Aviation Industry, 2014:18-20(in Chinese).
[16] 陈安, 魏玉龙, 廖江海, 等. 机身加筋壁板复合加载损伤容限性能试验[J]. 航空学报, 2017, 38(1):420093. CHEN A, WEI Y L, LIAO J H, et al. Damage tolerance test of stiffened fuselage panel under complex load[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(1):420093(in Chinese).
[17] 陈安, 魏玉龙, 廖江海, 等. 含纵向裂纹机身壁板损伤容限性能试验与分析[J]. 机械强度, 2017, 39(6):1463-1467. CHEN A, WEI Y L, LIAO J H, et al. Damage tolerance experiment and analysis of stiffened fuselage panel with longitudinal crack[J]. Journal of Mechanical Strength, 2017, 39(6):1463-1467(in Chinese).
[18] 陈安, 廖江海, 闫文伟, 等. 机身加筋壁板环向裂纹损伤容限试验与分析[J]. 航空工程进展, 2017, 8(1):38-43. CHEN A, LIAO J H, YAN W W, et al. Damage tolerance test and analysis of stiffened fuselage panel with circumferential crack[J]. Advances in Aeronautical Science and Engineering, 2017, 8(1):38-43(in Chinese).
[19] 李旭东, 关志东. 整体壁板损伤容限特性与修理技术研究[J]. 中国民航大学学报, 2008, 26(5):36-38. LI X D, GUAN Z D. Investigation of fuselage integral panel repair technology[J]. Journal of Civil Aviation University of China, 2008, 26(5):36-38(in Chinese).
[20] 庄茁, 蒋持平. 工程断裂与损伤[M]. 北京:机械工业出版社, 2004. ZHUANG Z, JIANG C P. Engineering fracture and damage[M]. Beijing:China Machine Press, 2004(in Chinese).

Analysis method for damaged and fractured integral panel of large aircraft

RichHTML

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 11

Recommended Articles

Metrics

Comments

[1]	Wanbo WANG, Yubiao JIANG, Yong HUANG, Xin ZHANG, Ran WEI. Lift enhancement wind tunnel test with flap blowing for large aircraft [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(13): 0-127870-.
[2]	ZHANG Min, TIAN Xitian, LI Bo. Shape control for press bend forming of integral panels [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(7): 623620-623620.
[3]	FENG Zhenyu, XIE Jiang, LI Henghui, CHENG Kun, MA Congyao, MOU Haolei. Finite element modeling and crashworthiness analysis of large aeroplane sub-cargo structure [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(2): 522394-522394.
[4]	LIU Zhitao, SUN Haisheng. A model attitude control and measurement technique for improving quality of wind tunnel dynamic test data [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(8): 2426-2435.
[5]	GAO Xiaoguang, XUE Yayong, WEN Zengkui. Task schedulability analyzing method of two-level hierarchical scheduling algorithm in integrated modular avionics [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(2): 585-595.
[6]	Huang Lin;Wan Min;Wu Xiangdong;Chi Cailou;Ji Xiusheng;Li Shanliang;Zhang Xinjuan. Prediction of Springback and Tool Surface Modification Technology for Age Forming of Integral Panel [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2009, 30(8): 1531-1536.
[7]	Peng Qing;Chen Guangnan;Wu Chenwu;Luo Gengxing;Wang Xiufeng. Laser-assisted Pre-stress Forming for Integral Panels [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2009, 30(8): 1544-1548.
[8]	Xia Yu;Huang Hai. Design Optimization for Hexapod Platform Parameters [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2008, 29(5): 1168-1173.
[9]	Chen Shaojie. composite technology and large aircraft [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2008, 29(3): 605-610.
[10]	JIAO Liang;ZHANG Jianhua. RESEARCH ON RAPID REPAIR OF BATTLE\\|DAMAGED INTEGRAL PANEL OF AIRCRAFT [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2000, 21(1): 64-66.
[11]	Lan Zhifang. THE APPLICATION AND DESIGN OF LARGE INTEGRAL PANELS FOR SH-5 AIRCRAFT [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1989, 10(8): 419-424.