応答曲面法を用いた空力弾性特性に関する翼型複合材積層板の最適設計

抄録

The present study minimizes the number of layers of wing shaped plates fabricated by laminated composite (CFRP) under aeroelastic constraint which keeps stable flutter speed. The finite element analysis for the aeroelastic characteristics requires considerable calculation effort. Therefore, the response surface method (RSM) is utilized to reduce the computational time for optimization where an approximate expression uses bending rigidity of composite plates as input and flutter speed as output. Then, the distributed genetic algorithm (DGA) is employed as an optimizer to minimize the numbers of layers of composite plates by designing fiber orientation angles. The optimized wing model shows weight reduction and enough flutter speed in less computational time than without RSM.