Exact(7)
Specimens of each laminate are tested after 14, 28, 56 and 84 days, respectively.
The elastic engineering constants of each laminate were predicted based on both micromechanics and classical laminate theory (CLT) and analytical results were verified using experimental results.
Therefore, the focus is on a new short-time procedure for fatigue life calculation of composites based on several cyclic load increase tests of each laminate.
The derivation of the governing equations of equilibrium of the joint is based on the virtual work principle, where the kinematics of each laminate are approximated by local and global functions and the bolt kinematics is assumed in terms of cubic Hermitian polynomials.
Also, the temperature field changes according to the equivalent EC tensor of each laminate and the second methodology was utilized in order to elucidate the validity of equivalent EC tensor indirectly, comparing the temperature field of the electro-thermal numerical models and the measured temperature field.
A thin layer of adhesive primer was painted on the surface of each laminate.
Similar(53)
A numerical example is presented which illustrates the failure of each component-laminate and the mechanism as a whole.
The analysis includes consideration of bending, extension and transverse shear deformations in each of the laminate layers and also includes its rotary, meridional and circumferential translatory and transverse inertias.
Each type of laminate was attached to the steel beams using bonded reinforcement (BR) and un-bonded reinforcement (UR) systems.
Three panels, one for each type of laminate, are built from thermoset prepreg material using automated fibre placement.
The damping parameters for each type of laminate analyzed, although initially determined empirically, are found to have a unique relationship to the energy dissipated at the time of maximum contact force.
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