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Modelling of linear elasticity and viscoelasticity of thermosets and unidirectional glass fibre-reinforced thermoset-matrix composites. Part 1, Theory of modelling

Klasztorny Marian, Nycz Daniel B.

Composites Theory and Practice

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2022

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R. 22, nr 1

3--15

EN

The paper presents advanced analytical modelling of the linear elasticity and viscoelasticity of thermosets and unidirectional long glass fibre-reinforced thermoset-matrix (UFRT) composites. New non-aging materials fully relaxed after the curing and post-curing processes are considered. Quasi-static long-term isothermal reversible viscoelastic processes under normal conditions are modelled. The thermosets are isotropic materials with viscoelastic shear strains and elastic bulk strains, and the fibres are isotropic and elastic. New rheological models for thermosets and UFRT composites, described by the smallest possible number of material constants, are developed. The viscoelastic generic function for shear/quasi-shear stresses is assumed as the Mittag-Leffler fractional exponential function in an integral form. The thermoset is described by two elastic and three viscoelastic parameters. The homogenized UFRT composite is described by five elastic and five viscoelastic parameters. Conjugated/unconjugated standard/inverse constitutive equations of the linear elasticity/elasticity-viscoelasticity governing thermosets and UFRT composites are formulated. The equations are mutually analytically transformable.

2

Modelling of linear elasticity and viscoelasticity of thermosets and unidirectional glass fibre-reinforced thermoset-matrix composites. Part 2, Homogenization and numerical analysis

Klasztorny Marian, Nycz Daniel B.

Composites Theory and Practice

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2022

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R. 22, nr 1

25--39

EN

The study continues the advanced analytical modelling of the linear elasticity and viscoelasticity of thermosets and unidirectional glass fibre-reinforced thermoset-matrix (UFRT) composites. The thermosets are isotropic materials with viscoelastic shear strains and elastic bulk strains, and the fibres are isotropic and elastic. The modified homogenization theory for UFRT composites, based on the selected tasks of the linear theory of elasticity, is developed. The modifications include a volumetrically equivalent cylindrical representative volume cell, solutions determined for an isotropic fibre based on the solutions for a monotropic (transversely isotropic) fibre, and certain modifications in the third task of the theory of elasticity. The viscoelastic constants of the thermoset are derived analytically and validated by fitting of the simulation and experimental shear strains on a logarithmic time scale in the unidirectional tension creep test. The viscoelastic constants of the UFRT composite are derived analytically and validated by fitting of the storage compliances corresponding to the new viscoelastic model and one obtained from the viscoelastic-elastic correspondence principle. The tension creep experiment is performed on the selected structural unsaturated polyester resin. Identification and validation are carried out for that thermoset and the corresponding UFRT composite with long E-glass fibres. All the modelling hypotheses are confirmed.

3

Influence of Honeycomb Core Stabilization on Composite Sandwich Structure Geometry

Michalski Mateusz, Krauze Wojciech

Transactions on Aerospace Research

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2019

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Nr 3 (256)

1--13

EN

Authors showed the influence of stabilization of the honeycomb core on shape of the composite sandwich test panel. Adhesive film laid on core ramps and cured with suitable cure cycle served as core stabilizer. Test panel geometry included different ramp angles (20° and 30°). To verify stabilization process a technology trial was performed. Three test panels were manufactured (3-stage, 1-stage and 1-stage with stabilized core). All test panels were manufactured in OoA process (Out of Autoclave). Panel surfaces were scanned with 3D scanner and compared with the reference CAD model. Both outer skin and inner skin were manufactured in Automated Fiber Placement Laboratory of Warsaw Institute of Aviation.

PL

W artykule przedstawiono wpływ stabilizacji wypełniacza komórkowego na kształt utwardzonej części kompozytowej w postaci przekładkowego panelu testowego o różnych kątach pochylenia ramp (20° oraz 30°). Jako stabilizator wypełniacza posłużył klej błonkowy położony na rampach wypełniacza i następnie utwardzony w odpowiednim cyklu termicznym. Po przeprowadzeniu pozytywnej próby technologicznej stabilizacji wypełniacza zostały wykonane 3 panele w różnych technologiach (1 oraz 3 etapowym). Panel ze stabilizowanym wypełniaczem został utwardzony w procesie 1 etapowym. Wszystkie panele wytworzone zostały w procesie bez użycia autoklawu (OOA – Out of Autoclave). Porównaniu metodą skanowania 3D została poddana powierzchnia wynikowa paneli po utwardzeniu. Jako referencję do porównania został przyjęty model CAD panelu. Zarówno warstwa zewnętrzna jak i wewnętrzna zostały ułożone w Laboratorium Zrobotyzowanego Układania Taśm Kompozytowych Instytutu Lotnictwa za pomocą robota AFP (Automated Fiber Placement).