A progressive damage model for matrix compression is complemented with matrix tension in a physically based manner. The interaction of damage mechanisms undergoes a preliminary validation using single elements. The crushing response is validated with two different flat specimens with the fibres oriented transversely and at 45 degrees to the load. The model combines friction with damage to model the shear response accurately, which is necessary for reliable crush simulations. The behaviour in tension is history dependent, i.e. the model accounts for the stiffness reduction and strength to carry load in tension when previously damaged occurs in compression. The validation is performed against different tests showing the reliability of the mod...
A mesoscale model for fibre kinking onset and growth in a three-dimensional framework is developed a...
Compressive mechanical testing was performed on continuous fiber Flax/Epoxy laminate specimens, capt...
The crashworthiness capability of an aircraft structure is dependent on its ability to attenuate cra...
Crush tests have been performed on flat unidirectional non-crimp fabric (NCF) coupons with different...
The crushing response of fiber-reinforced composite structures under compressive loading is investig...
none4noDOI volume: 10.15651/978-88-9385-029-2In this work, the validation of the Finite Element (FE)...
The in-plane compressive strength of fibre reinforced composite materials is known to be less than t...
This paper details a complete crush model for composite materials with focus on shear dominated crus...
This paper details the theory and implementation of a composite damage model, addressing damage with...
This paper details a complete crush model for composite materials with focus on shear dominated crus...
Fibre reinforced polymers are progressively substituting metallic materials in many aerospace struct...
A newly developed physically based model for the longitudinal response of laminated fibre-reinforced...
\ua9 2016, European Conference on Composite Materials, ECCM. All rights reserved. A model for the lo...
Despite great strides made in understanding and modelling Fiber-Reinforced Polymers (FRPs), their fu...
The high specific stiffness and strength of composites makes it advantageous for load carrying struc...
A mesoscale model for fibre kinking onset and growth in a three-dimensional framework is developed a...
Compressive mechanical testing was performed on continuous fiber Flax/Epoxy laminate specimens, capt...
The crashworthiness capability of an aircraft structure is dependent on its ability to attenuate cra...
Crush tests have been performed on flat unidirectional non-crimp fabric (NCF) coupons with different...
The crushing response of fiber-reinforced composite structures under compressive loading is investig...
none4noDOI volume: 10.15651/978-88-9385-029-2In this work, the validation of the Finite Element (FE)...
The in-plane compressive strength of fibre reinforced composite materials is known to be less than t...
This paper details a complete crush model for composite materials with focus on shear dominated crus...
This paper details the theory and implementation of a composite damage model, addressing damage with...
This paper details a complete crush model for composite materials with focus on shear dominated crus...
Fibre reinforced polymers are progressively substituting metallic materials in many aerospace struct...
A newly developed physically based model for the longitudinal response of laminated fibre-reinforced...
\ua9 2016, European Conference on Composite Materials, ECCM. All rights reserved. A model for the lo...
Despite great strides made in understanding and modelling Fiber-Reinforced Polymers (FRPs), their fu...
The high specific stiffness and strength of composites makes it advantageous for load carrying struc...
A mesoscale model for fibre kinking onset and growth in a three-dimensional framework is developed a...
Compressive mechanical testing was performed on continuous fiber Flax/Epoxy laminate specimens, capt...
The crashworthiness capability of an aircraft structure is dependent on its ability to attenuate cra...