Rapid Evaluation of Structural Concepts in Preliminary Design of Trailing-Edge High-Lift Devices

Kurzfassung

This article introduces a rapid, mechanically informed design workflow for preliminary structural trade studies of control surfaces with composite materials. Developed to address the challenges of designing slender trailing-edge devices for high-aspect-ratio wings, the workflow enables systematic early-phase evaluation of alternative structural concepts. Flaperon geometries, parameterised with CPACS, are idealised using an efficient beam element solver, allowing simultaneous consideration of nominal aerodynamic loads and off-nominal kinematic failure loads. Structural responses under these loads are used to size the structure, ensuring compliance with strain, buckling, and deflection constraints. The workflow’s utility is demonstrated through trade studies on representative inboard and outboard flaperons of the DLR-F25 research configuration. Mass sensitivities associated with support-station placement, number of spars, and their geometric layout are quantified to identify favourable design regions. Distinct optimal configurations emerge for bulky inboard and slender outboard flaperons, highlighting the geometry-dependent nature of structural decisions. As such, the presented workflow enables the rapid evaluation of structural concepts, supports cross-disciplinary exchanges, and facilitates context-specific decision-making in preliminary high-lift system design.