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Publikācija: Delamination and Skin-Stringer Separation Analysis in Composite Stiffened Shells

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Publikācijas valoda English (en)
Nosaukums oriģinālvalodā Delamination and Skin-Stringer Separation Analysis in Composite Stiffened Shells
Pētniecības nozare 2. Inženierzinātnes un tehnoloģijas
Pētniecības apakšnozare 2.5. Materiālzinātne
Autori Rolands Rikards
Kaspars Kalniņš
Olģerts Ozoliņš
Atslēgas vārdi skin-stringer delamination, composite laminate,mixed mode fracture, energy release rates
Anotācija Stiffened composite panels and shells are often used in different aircraft structural design. The deformations associated with post-buckling response can produce severe bending and shear loads at the skin-stringer interface. It can cause stiffener separation from the skin. Therefore, accurate computational methods are required to analyze and predict skin-stiffener debonding failures [1-3]. To analyze the skin-stringer debonding the fracture mechanics approach has been used based on 3D solid or shell finite element analysis results. A combined shell/3D modelling technique was developed in [4]. The 3D solid finite element model is used only in vicinity of the delamination front and the remainder of the structure is modelled using plate or shell elements. Such shell/3D technique can combine the computational efficiency of the shell finite element model with the accuracy of the full three-dimensional solution in the area of delamination.
Atsauce Rikards, R., Kalniņš, K., Ozoliņš, O. Delamination and Skin-Stringer Separation Analysis in Composite Stiffened Shells. No: Proceedings of the seventh International Conference on Computational Structures Technology, Portugāle, Lisbon, 7.-9. septembris, 2004. Lisbon: Civil-comp press, 2004, 103.-104.lpp.
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