Abstract
The purpose of this research is to develop a mathematical model between the specified certain parameters related to laminated composite design and the corresponding critical buckling load (CBL) of the structure. Therefore, Response Surface Method (RSM) based on the central composite design (CCD) is utilized as the experimental design approach. The CBLs are determined using the validated differential quadrature model (DQM) based on the classical plate theory for 30 different combinations determined by CCD. For the uniaxial loading case, statistical indicators of the simplified model are determined as 0.96, 0.95 and 0.91 for R2, Adj- R2 and Pred-R2, respectively. ANOVA results of the reduced quadratic regression model show that the most significant parameter is length-to-width ratio with a contribution of 32.23%, whereas the least is the fiber orientation angle of the central layer with a contribution ratio of 1.06%. Another significant outcome of the research is that an increment in the fiber angle from 0° to 90° has a very dominant effect (49.83%) on buckling load for a constant value of the length-to-width ratio of 0.5. Comparing the response surface results for biaxial loading to uniaxial loading reveals a similar overall trend, but a significant percentage change in the fiber angle for outer layers is observed when the length-to-width ratio is constant, as evident from the analysis of the obtained results.
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