Impacted area description effect on strength of laminate determined by calculation

Linearization of Composite Material Damage Model Results and Its Impact on the Subsequent Stress–Strain Analysis

“…Strength parameters respecting the rules of Hashin’s violation in the Abaqus system are shown in Table 6 . Parameters describing the progressive development of the violation are given in Table 7 [ 14 ].…”

“…Thus, the order of calculations, which are based on different calculation schemes, cannot be created completely arbitrarily. A good example is the sequence of analyses to determine the stiffness of a composite part before and after failure [ 14 ], which is the focus of this article, because changes in stiffness can be based on a structural condition monitoring (SHM) system that can determine the damage location of a local stiffness change. First, a linear approach following the implicit scheme is used, then a nonlinear analysis with violation is performed using the explicit solver, and then again, a linear analysis with the implicit scheme follows.…”

Bird strike analysis of new composite inlet for tilt rotor aircraft

“…The material of the projectile simulating the replacement of a real bird can be described by the socalled "elastic-plastic-hydrodynamic" material model. The hydrodynamic material model is defined in ABAQUS FE software [12] by a tabulated equation of state using Hugoniot curves for water-like homogenized bird materials [13,14]. The projectile nodes representing the bird from the ABAQUS finite element (FE) model were charged with an initial velocity, and a combination of tensile failure and shear failure criteria was used.…”

“…The fabric material model is based on the assumption, that the resulting mechanical properties are determined by the principle of superposition of warp and weft layers. The response of the fabric material in terms of elasticity and strength is the result of the optimization process described in [13]. Layup contains n layers in terms of fabric, while the FE model has 2n layers.…”

“…The testing program was established to assist in the selection of composite material and optimized lay-up from the point of view of energy absorption from bird impacts on the composite inlet for a new generation of tilt-rotor aircraft. The flat and simple curved test specimens, which were used in the high-speed impact resistance verification tests, were designed also to provide confirmation of the performance of the selected composite material and to assist in the finite element modelling of the global structure [13]. Figure 1 shows the proposed building block diagram (BBD) for demonstrating the durability of a VTOL aircraft composite air inlet.…”