04.2 - Aerostructures Design, Structural Dynamics, Aeroelasticity
EXPLORING MULTI-FIDELITY AEROELASTIC TAILORING: PROSPECT AND MODEL ASSESSMENT
H.F. Maathuis¹, S.G.P. Castro¹, R. De Breuker¹; ¹Delft University of Technology, Netherlands
In the pursuit of a more sustainable aviation industry, the development of high-performance and eco-friendly aircraft is crucial. However, the push for lighter, more slender wings brings forth challenges in structural integrity and aeroelasticity, especially with the increasing use of composite materials. This paper addresses these challenges through a Multi-Disciplinary Optimisation (MDO) framework, focusing on aeroelastic tailoring while optimising lamination parameters and thicknesses of structural parts. While employing the Classical Laminate Theory (CLT), this study formulates a weight minimization problem while ensuring feasibility through multiple constraints, incorporating diverse disciplines such as structural integrity and dynamic aeroelastic stability. The complexity of this high-dimensional problem often necessitates a sequential optimisation approach across design phases, limiting the exploration of superior designs. To overcome this limitation, the paper proposes a concurrent optimisation strategy utilizing models of varying fidelity — ranging from low-fidelity beam models to high-fidelity shell models — employing multi-fidelity approaches. The work aims to bridge the gap between design stages, allowing for the exchange of crucial information while maintaining computational efficiency. The envisioned design cycle, contrasting past practices with future strategies, highlights the shift from empirical knowledge reliance to physics-based insights, particularly crucial for novel aircraft configurations. By integrating high-fidelity information early in the design process, this work strives to expand design freedom and foster more optimal and structurally feasible aircraft designs.