Fully utilizing the post-buckling capacity of stiffened composite panels is important to reduce the weight of aeronautical composite structures. However, owing to the complex post-buckling failure modes and mechanisms, there are no effective analysis methods. This paper explores the impacts of the mode III fracture energy on the damage behavior of the stiffener–skin interface of composite stiffened panels under post-buckling conditions. To characterize the bonding interface damage, an interface damage initiation criterion considering the effects of through-thickness compression on the shear failure was used and combined with the Reeder damage extension criterion, which considers the mode III fracture. The mode III fracture toughness characteristics of the damage evolution of the stiffener–skin interface were obtained using the edge crack torsion (ECT) test method. Moreover, the compressive deformation response, buckling load, buckling modes, failure load, and failure modes of the panel were obtained by a compression test of I-shaped stiffened panels. Based on the aforementioned experimental data and numerical model, the post-buckling behavior of the I-shaped stiffened composite panels with an open cross-section stiffener was studied. It was found that the mode III fracture energy caused by the longitudinal shear stress τ31 played a major role in the stiffener–skin interface damage extension of the stiffened panels. Therefore, the mode III fracture behavior should not be ignored in the post-buckling analysis. The numerical analysis method developed can accurately predict the damage initiation and evolution processes of the composite panel interface. The method can be effectively used for post-buckling analysis of aeronautical composite panels.
CuiD. Structure technology development of large commercial aircraft. Acta Aeronautica et Astronautica Sinica2008; 29(3): 573–582. (Chinese).
2.
MertMKayranA. Post-buckling load redistribution of stiffened panels in aircraft wing box structures. In: 57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, San Diego, California, USA, 2016.
3.
DegenhardtRCastroSGPArbeloMA, et al.Future structural stability design for composite space and airframe structures. Thin-wall Struct2014; 81(7): 29–38.
4.
GliszczynskiAKubiakT. Progressive failure analysis of thin-walled composite columns subjected to uniaxial compression. Compos Struct2017; 169: 52–61.
5.
ZimmermannRRolfesR. POSICOSS—improved postbuckling simulation for design of fibre composite stiffened fuselage structures. Compos Struct2006; 73: 171–174.
6.
DegenhardtRRolfesRZimmermannR, et al.COCOMAT—improved material exploitation of composite airframe structures by accurate simulation of postbuckling and collapse. Compos Struct2006; 73: 175–178.
7.
DegenhardtRKlingARouwerK, et al.Design and analysis of stiffened composite panels including post-buckling and collapse. Comput Struct2008; 86: 919–929.
8.
GengXJiFWangJ, et al.Experimental and numerical investigations of compression stability of stiffened composite panel with ply interleaving. J Compos Mater2017; 51(26): 3647–3656.
9.
ZhaoLWangKDingF, et al.A post-buckling compressive failure analysis framework for composite stiffened panels considering intra-inter-laminar damage and stiffener debonding. Results Phys2019; 13: 102205. DOI: 10.1016/j.rinp.2019.102205
10.
RiccioAGordanoMZarrelliM. A linear numerical approach to simulate the delamination growth initial in stiffened composite panels. J Compos Mater2010; 44(15): 1841–1866.
11.
RiccioARaimondoAFeliceGD, et al.. A numerical procedure for the simulation of skin-stringer debonding growth in stiffened composite panels. Aerosp Sci Tech2014; 39: 307–314.
12.
AkterskaiaMJansenEHallettSR, et al.Analysis of skin-stringer debonding in composite panels through a two-way global-local method. Compos Struct2018; 202: 1280–1294.
13.
BorrelliRRiccioASellittoA, et al.On the use of global-local kinematic coupling approaches for delamination growth simulation in stiffened composite panels. Compos Sci Tech2015; 115: 43–51.
14.
JiRZhaoLWangK, et al.Effects of debonding defects on the postbuckling and failure behaviors of composite stiffened panel under uniaxial compression. Compos Struct2021; 256: 113121. DOI: 10.1016/j.compstruct.2020.113120
15.
RaimondoARiccioA. Inter-laminar and intra-laminar damage evolution in composite panels with skin-stringer debonding under compression. Compos B2016; 94: 139–151.
16.
MilazzoAOliveriV. Buckling and postbuckling of stiffened composite panels with cracks and delaminations by Ritz Approach. AIAA J2017; 55(3): 965–980.
17.
YeYZhuWJiangJ, et al.Computational modelling of postbuckling behavior of composite T-stiffened panels with different bonding methods. Composites B: Eng2019; 166: 247–256.
18.
GonenliCDasO. Effect of crack location on buckling and dynamic stability in plate frame structures. J Braz Soc Mech Sci Eng2021; 43: 311. DOI: 10.1007/s40430-021-03032-2
19.
GonenliCOzturkHDasO. Effect of crack on free vibration of a pre-stressed curved plate. Proc Inst Mech Eng C: J Mech Eng Sci2022; 236(2): 811–825. DOI: 10.1177/0954406221994869
20.
DasOGonenliC. The impact of the cracks on the harmonic response of stiffened steel plates. Latin Am J Sol Struct2022; 19(2): e427.
21.
SabooriBTorabiARKeshavarzS. Experimental and stress-based theoretical studies on mixed mode I/III fracture of round-tip V-notched polystyrene specimens. Theor Appl Fracture Mech2018; 95: 283–305.
22.
TorabiARSabooriB. Experimental and theoretical investigation of mixed mode I/III brittle fracture of U-notched polystyrene components. Strain Anal2018; 53(1): 15–25.
23.
AlihaaMRMLinulEBahmaniA, et al.Experimental and theoretical fracture toughness investigation of PUR foams under mixed mode I+III loading. Polym Test2018; 67: 75–83.
24.
MansourianAHashemiSAlihaaMRM. Evaluation of pure and mixed modes (I/III) fracture toughness of Portland cement concrete mixtures containing reclaimed asphalt pavement. Construction Building Mater2018; 178: 10–18.
25.
SabooriBAyatollahiMR. A novel test configuration designed for investigating mixed modeII/III fracture. Eng Fracture Mech2018; 197: 248–258.
26.
CricrìGPerrellaM. Investigation of mode III fracture behaviour in bonded pultruded GFRP composite joints. Composites B2017; 112: 176–184.
27.
Lopez-MenendezAVinaJArguellesA, et al.A new method for testing composite materials under mode III fracture. J Compos Mater2016; 50(28): 3973–3980.
28.
LeeSMastersJO'BrienT, et al.An edge crack torsion method for mode III delamination fracture testing. J Compos Technol1993; 15(3): 193–201.
29.
PennasDCantwellWJ. The influence of loading rate on the mode III interlaminar fracture toughness of composite/steel bi-material systems. J Compos Mater2009; 43(20): 2255–2268.
30.
BrowningGCarlssonLARatcliffeJG. Redesign of the ECT test for mode III delamination Testing. part I: finite element analysis. J Compos Mater2010; 44(15): 1867–1881.
31.
BrowningGCarlssonLARatcliffeJG. Modification of the edge crack torsion specimen for mode III delamination testing. Part II – experimental study. J Compos Mater2011; 45(25): 2633–2640.
32.
MehrabadiFAKhoshravanM. Mode III interlaminar fracture and damage characterization in woven fabric-reinforced glass/epoxy composite laminates. J Compos Mater2012; 47(13): 1583–1592.
33.
BakerAAScottML. Composite materials for aircraft structures. 3rd edition. Reston, VA, USA: American Institute of Aeronautics and Astronautics, 2016.
34.
KootteLJBisagniCDavilaC, et al.Study of skin-stringer separation in postbuckled composite aeronautical structures. In: Proceedings of American Society for Composites (ASC) 33rd Annual Technical Conference and 18th US-Japan Conference on Composite Materials, Seattle, Washington, USA, September 24–26, 2018.
35.
KootteLJBisagniC. A methodology to investigate skin-stringer separation in postbuckled composite stiffened panels. In: Proceedings of AIAA SciTech 2020 Forum, Orlando, Florida, USA, 6–10 January 2020. DOI: 10.2514/6.2020-0477
36.
KootteLJBisagniCRanatungaV, et al., Effect of composite stiffened panel design on skin-stringer separation in postbuckling. In: Proceedings of the AIAA SciTech 2021 Forum, Virtual Event, 11–15 & 19–21 January 2021. DOI: 10.2514/6.2021-0441
37.
TsaiSWWuEM. A general theory of strength for anisotropic materials. J Compos Mater1971; 5: 58–80.
38.
ChenXSunXChenP, et al.Rationalized improvement of Tsai–Wu failure criterion considering different failure modes of composite materials. Compos Struct2021; 256: 113120. DOI: 10.1016/j.compstruct.2020.113120
39.
LindePPleitnerJDe BoerH, et al.Modelling and simulation of fibre metal laminates. In: ABAQUS Users’ Conference, Boston, USA, 2004, pp. 421–439.
40.
YeL. Role of matrix resin in delamination onset and growth in composite laminates. Composites Sci Technol1988; 33(4): 257–277.
41.
ChenXSunXChenP, et al.A delamination failure criterion considering the effects of through -thickness compression on the interlaminar shear failure of composite laminates. Compos Struct2020; 241: 112121. DOI: 10.1016/j.compstruct.2020.112121
42.
ReederJR. An evaluation of mixed-mode delamination failure criteria, NASA-TM-104210, 1992.
43.
BenzeggaghMLKenaneM. Measurement of mixed-mode delamination fracture toughness of unidirectional glass/epoxy composites with mixed-mode bending apparatus. Composites Sci Technol1996; 56(4): 439–449.
44.
TuronACamanhoPPCostaJ, et al.A damage model for the simulation of delamination under variable-mode loading. Mech Mater2006; 38: 1072–1089.
