Load bearing capacity of composite panels with in-service damages

DOI: 10.34759/trd-2020-110-5

Аuthors

Golovan V. I.^*, Dudarkov Y. I.^*, Levchenko E. A.^**, Limonin M. V.^***

Central Aerohydrodynamic Institute named after N.E. Zhukovsky (TsAGI), 1, Zhukovsky str., Zhukovsky, Moscow Region, 140180, Russia

*e-mail: dzuba@tsagi.ru
**e-mail: evgeniy.levchenko@tsagi.ru
***e-mail: mikhail.limonin@tsagi.ru

Abstract

The article presents the results of numerical and experimental studies of residual strength of composite panels with in-service damages. The issues of damage size impact on buckling and strength properties of panels, as well as on their modes of failure while the critical state achieving, were under study. Structural panels of wing and empennage of the airframe structure of a long-distance aircraft were considered in conditions of uniaxial compression. The article presents experimental data obtained while compressing tests of panels with normalized impact damages, and gives its comparison with computational results. Virtual modelling of experiments was performed based on finite element method including the geometrically non-linear problem setting, realized in NSC Nastran and Marc software complexes. A technique for numerical studies performing and methods for damaged area modelling are described. It is demonstrated that modern numerical methods allow predict the load-bearing capacity of structural composite materials in both initial state and in the presence of defects in them. The difference in reaction of highly-loaded wing panels and medium-loaded empennage on in-service damages was established by the parametric studies results. Destruction mode associated with the process progressive growth of the damage zone is characteristic for the panels of the first type. The load bearing capacity for the panels of the second type is determined in a greater degree by the total or local buckling. It was shown also that the damage effect on the residual strength of the composite panels depended on the energy of the impact to which all structures might be subjected while their operation, as well as on the place of the damage location. The technique for computing-parametric studies performing proposed in the article can be employed for preliminary estimation of normalized in-service damages impact on the load bearing capacity of panels from CFRP, and required level of allowable stresses to meet the strength safety requirements of composite structures. The obtained results can be useful at the draft design stages to formulate appropriate destruction criteria.

Keywords:

composite materials, stringer panels, residual strength, buckling, load bearing capacity, in-service damages

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