Aeroelastic Design of a Highly-Flexible Wing Using a Simplified Composite Optimization Approach within cpacs-MONA

Kurzfassung

Since composite structures have shown a growing utilization in the aircraft structural design, as a first step, a simplified implementation for composite optimization has been implemented into cpacs-MONA. Thereby the material properties of a composite lay-up are converted to a linear anisotropic material definition to be used for two-dimensional elements (MSC Nastran PSHELL/MAT2-combination). This calculation is done by using the generically known ABD-matrix formulation. For this publication cpacs-MONA sets up an aircraft configuration with three different material specifications, resulting in different flexibilities of the load-carrying wing structures: - Model A: Aluminum material definition for the structural wing components (ribs, spars and skin) - Model B: Composite material definitions for the wing components (reference model) - Model C: Model B with increased strain allowables (highly-flexible wing) Since cpacs-MONA comprises of an iterative loads analysis and structural optimization loop, the question on how the different wing flexibilities effect the loads, the structural mass, the dynamic behavior and the resulting aeroelastic stability of the complete aircraft is addressed within this paper.