Exploring an aeroelastic tailoring design method for composite backswept wing

We propose a hybrid multilevel structural optimization algorithm to carry out the aeroelastic tailoring design of a high-aspect-ratio composite backswept wing. First, under the precondition that the constraints for strength and displacement are met, we use the thicknesses of beam, rib and skin as design variables to minimize the structural weight of the composite wing. Second, we try to lighten its structural weight by optimizing the proportions of skin plies under the condition that the constraintg for the flutter speed of the composite wing are met and then analyze the effects of the proportions of skin plies on the flutter speed. Finally, in order to increase the flutter speed, we use the hybrid multilevel structural optimization algorithm to optimize the order of skin plies and carry out the aeroelastic tailoring design of the high-aspect-ratio backswept composite wing. The optimization results, given in Tables 1, 2 and 3 and Fig. 3, and their analysis show preliminarily that: (1) the use of the hybrid multilevel structural optimization algorithm can not only lighten the structural weight but also increase the flutter speed; (2) the wing skin with the lighter ply proportion of ±45° has a more efficient and reasonable stiffness distribution.