Curved Shear Panel Theory as an Enabler for Gradient-Based Wing Optimization
Abstract
In the preliminary design of aircraft structures, efficient modelling techniques are essential to balance accuracy and computational cost. Shear Panel Theory (SPT) offers a simple yet effective idealisation of thin-walled, stiffened structures such as wings. It captures more structural detail—like ribs, sweep and taper—than traditional beam idealisation and would otherwise require detailed finite element analysis. However, compared to a finite element model, the degrees of freedom of the structure as well as the meshing effort are significantly reduced, as SPT idealisation uses a structural element approach. This improves mass estimation and structural response calculation and makes SPT particularly well-suited for optimisation tasks in early design phases. This work presents a methodology to derive structural properties of wing segments based on NACA airfoils using SPT. This offers adjustment of the wing’s geometry for use in aeroelastic analysis and enables fast evaluation of structural behaviour and gradient computation, supporting integration into multidisciplinary design optimisation frameworks. The proposed methodology advances the use of idealised structural models in aircraft design by bridging the gap between high-fidelity analysis and system-level aeroelastic simulations, supporting faster and more informed early design iterations.
Authors 3
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Affiliation as printed
Institute of Structural Mechanics and Lightweight Design, RWTH Aachen University, 52066 Aachen, Germany
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Affiliation as printed
Institute of Structural Mechanics and Lightweight Design, RWTH Aachen University, 52066 Aachen, Germany
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Affiliation as printed
Institute of Structural Mechanics and Lightweight Design, RWTH Aachen University, 52066 Aachen, Germany
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