This work presents results of the research assessing application advantages of intrinsically self-healing FRP composites over conventional FRP composite materials in typical airframe structures. The previously developed multiscale constitutive model for intrinsically self-healing FRP composites has been validated for the cases of static loading conditions (3PB test) in [1], and dynamic loading conditions (LVI) in [2]. The model is implemented in Abaqus/Explicit and Abaqus/Standard user material subroutines VUMAT and UMAT, respectively. Experimental and numerical analysis results of bird strike in FRP composite wing are taken from [3] and used as a reference. Inhere, for analysis purposes, the conventional epoxy resin is replaced with a self-healing polymer blend of Epon™ 828EL epoxy resin with 25vol% of PCL, poly(ε-caprolactone) and it is combined with T700 UD fibres to obtain intrinsically self-healing FRP composite. In the conclusions, the critical assessment of the obtained results is performed, and advantages of the new material systems are validated.

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