04.2 - Aerostructures Design, Structural Dynamics, Aeroelasticity

CRITICAL LOAD-CASE AND CONSTRAINT IDENTIFICATION FOR PRELIMINARY COMPOSITE WING SIZING USING RAPID DESIGN TOOLS

Y. Pan¹, M. Alam¹; ¹Cranfield University, United Kingdom

A methodology is presented for identifying critical load cases and governing structural constraints for preliminary composite wing sizing using a rapid multidisciplinary optimisation framework. The approach is demonstrated on a NASA Common Research Model wing using parametric wing-box discretisation and sensitivity analysis to quantify impacts on mass, stiffness, and aeroelastic response. Results show that refined discretisation improves torsional stiffness prediction while preserving global deflection accuracy.

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DOI: 10.71945/icas2026_0628