Strength analysis and test verification of composite fuselage panels

被引：0

作者：

Li Z. ^{[1
]}

Wang J. ^{[1
]}

Deng F. ^{[2
]}

Yu Z. ^{[1
]}

机构：

[1] Shanghai Aircraft Design and Research Institute, Shanghai

[2] China Aircraft Strength Research Institute, Xi'an

来源：

Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2020年 / 41卷 / 09期

关键词：

Composite material; Damage tolerance; Fatigue; Fuselage panel; Stability;

D O I：

10.7527/S1000-6893.2020.23688

中图分类号：

学科分类号：

摘要：

The application of composite materials in the main loading structure of the aircraft fuselage is the development trend in recent years. In this paper, the static loading capacity, fatigue and damage tolerance characteristics of composite fuselage panels are analyzed with large-scale panel test. The buckling load of skin and the loading capacity of panel are examined by adopting the theoretical formula, the semi empirical formula, and the finite element modal analysis. The advanced multi-load panel test rig is used to simulate the actual loads of fuselage panel, achieving the independent and combined application of the pressure, tension, compression, and shear load. The engineering and finite element analysis method of skin buckling and the residual strength loading analysis method of panel are verified by static tests. By introducing the embedded defect, BVID and VID damage, the influence of the damage on strain distribution is studied by experiment, and the non-expansion property of the damage is verified by fatigue and damage tolerance experiments. © 2020, Beihang University Aerospace Knowledge Press. All right reserved.

引用

共 23 条

[1]

WALKER T H, MINGUET P J, FLYNN B W, Et al., Advanced technology composite fuselage-Structural performance: NASA Contractor Report 4732, (1997)

[2]

DEGENHARDT R, KLING A, ROHWER K, Et al., Design and analysis of stiffened composite panels including post-buckling and collapse, Computers and Structures, 86, pp. 919-929, (2008)

[3]

ORIFICI A C, THOMSON R S, DEGENHARDT R, Et al., Degradation investigation in a postbuckling composite stiffened fuselage panel, Composite Structures, 82, pp. 217-224, (2008)

[4]

BISAGNI C, VESCOVINI R, DAVILA C G., Single stringer compression specimen for the assessment of damage tolerance of post bulked structures, Journal of Aircraft, 48, 2, pp. 495-502, (2011)

[5]

MO Y M, GE D Y, ZHOU J F., Experiment and analysis of hat stringer stiffened composite curved panels under axial compression, Composite Structures, 123, pp. 150-160, (2015)

[6]

WANG H B, LIN G W, HAN X B., Shear buckling performance of composite hat-stiffened panels, Acta Aeronautica et Astronautica Sinica, 40, 8, (2019)

[7]

CHANG Y Y, XU X W, GUO S X., Nonlinear progressive damage analysis of integral stiffened composite panels under compressive load, Acta Materiae Compositae Sinica, 28, 4, pp. 202-211, (2011)

[8]

YAN Y, ZENG D., Study on the post-impact compressive strength of composite laminates, Acta Aeronautica et Astronautica Sinica, 24, 2, pp. 137-139, (2003)

[9]

CUI H P, WEN W D, CUI H T., Research on low velocity impact damage and residual compressive strength of laminated composites, Mechanical Science and Technology, 25, 9, pp. 1113-1117, (2006)

[10]

LIN Z Y, XU X W., Residual compressive strength of stiffened composite laminates with impact damage, Acta Aeronautica et Astronautica Sinica, 30, 1, pp. 56-61, (2009)

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