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In aircraft design, structural optimization and uncertainty quantificationconcerning 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 transonicaeroelastic analysis. However, current ROMs cannot be reused during iteration,thus time cost is still way too large. This study proposed an improved ROMsuitable for Arbitrary Mode Shapes (ROM-AMS), which is reusable regardless thevariation of design variables. By adopting Principal Component Analysis,ROM-AMS method can significantly reduce the number of basis mode shapes andimprove the accuracy of flutter analysis. In an optimization case, the weightof cropped delta wing is reduced by 28.46%, and the efficiency is 900 timeshigher than traditional ROM method, which demonstrates the feasibility of thismethod in iterative design process.

A novel unsteady aerodynamic Reduced-Order Modeling method for transonic aeroelastic optimization