  In aircraft design, structural optimization and uncertainty quantification
concerning transonic aeroelastic issues are computationally impractical,
because the iterative process requires great number of aeroelastic analysis.
Emerging Reduced-Order Model (ROM) method is convenient for transonic
aeroelastic analysis. However, current ROMs cannot be reused during iteration,
thus time cost is still way too large. This study proposed an improved ROM
suitable for Arbitrary Mode Shapes (ROM-AMS), which is reusable regardless the
variation of design variables. By adopting Principal Component Analysis,
ROM-AMS method can significantly reduce the number of basis mode shapes and
improve the accuracy of flutter analysis. In an optimization case, the weight
of cropped delta wing is reduced by 28.46%, and the efficiency is 900 times
higher than traditional ROM method, which demonstrates the feasibility of this
method in iterative design process.
