Residual strength evaluation of curved hat-stiffened composite panels with discrete-source damage

被引：0

作者：

Wang H. ^{[1
]}

Wang X. ^{[1
]}

Lin G. ^{[1
]}

Li X. ^{[1
]}

Yang S. ^{[1
]}

机构：

[1] Aero. Science and Technology Key Laboratory of Full Scale Aircraft Structure Statics and Fatigue, Aircraft Strength Research Institute of China, Xi'an

来源：

Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2022年 / 43卷 / 06期

关键词：

combined loading; composite; curved hat-stiffened panels; discrete-source damage; residual strength;

D O I：

10.7527/S1000-6893.2022.25899

中图分类号：

学科分类号：

摘要：

Experiments and analysis on curved hat-stiffened composite panels with 7 stringers and 4 frames are conducted to investigate the residual strength of panels with discrete-source damage under combined internal pressure and axial compression. The research indicates that axial strain of stringers and skin is equal more than one stringer spacing from discrete-source damage, stress is redistributed near discrete-source damage, stress concentration reduces, and discrete-source damage can be simplified as a round hole. The research also proved that the method based on FD criterion and the classical laminate theory can be used to predict the residual strength of curved hat-stiffened composite panels with discrete-source damage under combined internal pressure and axial compression. An empirical method was proposed to estimate the residual strength of the curved hat-stiffened composite panels with discrete-source damage under combined internal pressure and axial compression based on the structural characteristics, strain distribution and failure mode. The calculated results are in good agreement with the experimental results. © 2022 AAAS Press of Chinese Society of Aeronautics and Astronautics. All rights reserved.

引用

共 27 条

[1] AC20-107B Subject: Composite aircraft structure, advisory circular, pp. 12-14, (2009)
[2] JIAO G Q, DU K, YANG CP, Et al., Compressive properties of stiffened composite panels with discrete-source damage [J], Acta Aeronautica et Astronautica Sinica, 28, 6, pp. 1383-1388, (2007)
[3] DU K, JIAO G Q, WANG X., Tensile properties of stiffened composite panels with discrete-source damage [J], Acta Materiae Compositae Sinica, 25, 4, pp. 181-186, (2008)
[4] WALKER T H, MINGUET P J, FLYNN B W, Et al., Advanced technology composite fuselage-structure performance: NASA CR-4732, (1997)
[5] WANG J, LOTTS C, SLEIGHT D., Analysis of discrete-source damage progression in a tensile stiffened composite panel, 40th Structures, Structural Dynamics, and Materials Conference and Exhibit, (1999)
[6] ALEX V., Designing primary structures with stitched composites [C], 31 st Congress of the International Council of the Aeronautical Sciences, (2018)
[7] ANDREW B, JOHN G B J, ANDREW L, Et al., Full-scale test and analysis results of a PRSEUS fuselage panel to assess damage containment features [C], Aircraft Airworthiness & Sustainment Conference, (2012)
[8] XU X D, TAKEDA S I, AOKI Y, Et al., Predicting notched tensile strength of full-scale composite structures from small coupons using fracture mechanics, Composite Structures, 180, pp. 386-394, (2017)
[9] WANG J T, POE C C, AMBUR D R, Et al., Residual strength prediction of damaged composite fuselage panel with R-curve method [J], Composites Science and Technology, 66, 14, pp. 2557-2565, (2006)
[10] LIANG L, JIA P R, JIAO G Q., Progressive failure study of discrete-source damage in stiffened composite panels, Advanced Materials Research, 314-316, pp. 963-967, (2011)

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