A method for evaluating delamination in elements of multilayer composite structures
Authors: Belousov I.S.
Published in issue: #11(155)/2024
DOI: 10.18698/2308-6033-2024-11-2401
Category: Aviation and Rocket-Space Engineering | Chapter: Strength and Thermal Conditions of Aircraft
Composite materials are widely used in aviation today. The use of layered composite materials with carbon fibers is an effective way to reduce the weight of a structure. However, one of the significant disadvantages of using layered composites is their susceptibility to interlayer defects, or delamination. At the moment, there is no unified standard approach for determination whether the detected interlayer defect is as dangerous that it will lead to a decrease in the load-bearing capacity of the structure, or the structural element with the detected defect can be left in operation. This work is an attempt to formulate a universal method that would allow for the rapid estimation of the degree of danger of a detected interlayer defect in an element of an aircraft structure. Specimens from a layered composite in the form of a strip with a wide-through embedded delamination and a plate with a round shape embedded delamination are considered. A parametric study of the effect of the size of the defect and its location along the thickness of the lay-up on the first buckling form was carried out. Various types of composite lay-up and different prepregs are considered. The areas of dependence of first buckling form of specimens on the geometric parameters of the defect are constructed, which allow us to assess the degree of danger of the delamination.
EDN EUFMHI
References
[1] Maksimenko V.N., Olegin I.P., Pustovoy N.V. Metody rascheta na prochnost i zhestkost elementov konstruktsiy iz kompozitov [Methods for calculating strength and stiffness of the structural elements made of composites]. Novosibirsk, NGTU Publ., 2015, 424 p.
[2] Grishin V.I., Dzyuba A.S., Dudarkov Yu.I. Prochnost i ustoychivost elementov i soedineniy aviatsionnykh konstruktsiy iz kompozitov [Strength and stability of elements and connections of the aircraft structures made of the composites]. Moscow, Fizmatlit Publ., 2013, 272 p.
[3] Rana S., Fangueiro R. Advanced composite materials for aerospace engineering: processing, properties and application. Woodhead Publishing, Elsevier, 2016, 496 p.
[4] Bolotin V.V., Novichkov Yu.N. Mekhanika mnogosloinykh konstruktsiy [Mechanics of the multi-layered structures]. Moscow, Mashinostroenie Publ., 1980, 375 p.
[5] Chawla. K.K. Composite materials: Science and Engineering. Springer Science + Business Media, Inc., 2019, 560 p.
[6] Valishin А.А. Kontsentratsiya mikrodefektov vblizi treshchiny razrusheniya v polimerakh i kompozitakh na ikh osnove [The concentration of microdefects near the crack fracture in polymers and composites based on them]. Inzhenerny zhurnal: nauka i innovatsii — Engineering Journal: Science and Innovation, 2015, iss. 6. https://doi.org/10.18698/2308-6033-2015-6-1409
[7] Kachanov L.M. Razrushenie kompozitnykh materialov putem rassloeniya [Destruction of composite materials by delamination]. Mekhanika polimerov — Mechanics of Polymers, 1976, no. 5, pp. 918–922.
[8] Cardenas D., Elizalolo H., Marzocca P., Abdi F., Minnetyan L., Probst O. et al. Progressive failure analysis of thin-walled composite structures. Composite structures, 2013, vol. 95, pp. 53–62.
[9] Navarro C., Vazquez J., Dominguez J. 3D vs. 2D fatigue crack initiation and propagation in notched plates. International Journal of Fatigue, 2014, vol. 58, pp. 40–46.
[10] Pascoe J.A., Alderliesten R.C., Benedictus R. On the relationship between disbond growth and the release of strain energy. Engineering Fracture Mechanics, 2015, vol. 133, pp. 1–13.
[11] Kassapoglou C. Modeling of the effect of damage in composite structures: simplified approaches. Wiley, 2015, 253 p.
[12] Greco F., Leonetti L., Lonetti P. A two-scale failure analysis of composite materials in presence of fiber/matrix crack initiation and propagation. Composite structures, 2013, vol. 95, pp. 582–597.
[13] Viktorov E.G. Podrastanie i izlom otsloeniy v kompozitakh pri szhatii [Growth and fracture of delaminations in composites under compression]. In: Mekhanika materialov i konstruktsiy [Mechanics of Materials and Structures]. Moscow, MEI Publ., 1982, pp. 36–40.
[14] Chai H., Babcock C.D. Two-dimensional modeling of compressive failure in delaminated laminates. Journal of Composite materials, 1985, vol. 19, no. 1, pp. 67–91.
[15] Chai H., Babcock C.D., Knous W.G. One-dimensional modeling of failure in laminated plates by delamination buckling. International Journal of Solids and Structures, 1981, vol. 14, no. 11, pp. 1069–1083.
[16] Shivacumar K.N., Whitcomb J.D. Buckling of sublaminate in a quasi-isotropic composite laminate. Journal of Composite materials, 1985, vol. 19, no. 1, pp. 2–18.
[17] Bohoeva L.A., Antokhonov V.B., Zangeev B.I. Teoreticheskaya otsenka maksimalnykh razmerov bezopasnykh defektov tipa otsloeniy [Theoretical estimation of the maximum sizes of safe defects such as delaminations]. In: Materialy Mezhdunarodnoy nauchnoy konferentsii “Problemy makhaniki sovremennykh mashin” [Proceedings of the International Scientific Conference “Problems of Mechanics of the Modern Machines”]. Ulan-Ude, 2000, pp. 14–15.
[18] Bohoeva L.A. Vliyanie defektov tipa otsloeniy v sloistykh plastinakh na velichinu kriticheskoy nagruzki [The influence of defects such as delaminations in laminated plates on the value of the critical load]. Vestnik BGU – BSU Bulletin, 2005, vol. 5, pp. 243–264.
[19] Kollner A., Kashtalyan M., Guz I., Vollmecke C. On the interaction of delamination buckling and damage growth in cross-ply laminates. International Journal of Solids and Structures, 2020, vol. 202, pp. 912–928.
[20] Bottega W.J., Maewal A. Delamination buckling and growth in lamination. Journal of Applied Mechanics ACME, 1983, vol. 50, no. 1, pp. 184–189.
[21] Wang K., Zhao L., Hong H., Gong Y., Zhang J., Ning H. An analytical model for evaluating the buckling, delamination propagation, and failure behaviors of delaminated composites under uniaxial compression. Composite structures, 2019, vol. 223, pp. 1–9.
[22] Wang K., Zhao L., Hong H., Gong Y., Zhang J., Ning H. Parameter studies and evaluation principles of delamination damage in laminated composites. Chinese Journal of Aeronautics, 2021, vol. 34 (7), pp. 62–72.
[23] Kapania R.K., Wolfe D. Buckling of axially loaded beam-plate with multiple delaminations. Journal of Pressure Vessel Technology, 1989, vol. 111, no. 2, pp. 151–158.
[24] Chermoshentseva A. S. Razrabotka metodiki povysheniya prochnosti tonkostennykh elementov konstruktsiy iz kompozitnykh materialov s defektami tipa rassloeniya. Dis. ... kand. tekhn. nauk [Development of a technique for increasing strength of the thin-walled structural elements made of composite materials with the delamination-type defects. Diss. … Cand. Sc. (Eng.)]. Moscow, Bauman Moscow State Technical University, 2018, 168 p.
[25] Bohoeva L.A. Osobennosti rascheta na prochnost elementov konstruktsiy iz izotropnykh i kompozitsionnykh materialov s dopustimymi defektami [Specifics in strength computation of structural elements made of the isotropic and composite materials with the permissible defects]. Ulan-Ude, VSGTU Publ., 2007, 192 p.