АНАЛІЗ МЕТОДІВ ПРОЄКТУВАННЯ КРИЛ ЛЕГКИХ ЦИВІЛЬНИХ ЛІТАКІВ У КОНТЕКСТІ ІНТЕГРОВАНОГО ПРОЄКТУВАННЯ

This study focuses on current methodologies for designing wings for light civil aircraft (LCA), detailing design concepts within an integrated design framework. The study outlines the historical development of design concepts, starting from conventional statistical-analytical methods, sequential finite element method (FEM) analysis, and moving towards advanced multidisciplinary design optimization (MDO) and parametric 3D design in CAD/CAM/CAE/PLM (Computer-Aided Design/Computer-Aided Manufacturing/Computer-Aided Engineering/Product Lifecycle Management) frameworks. The methodologies have specific strengths and weaknesses The statistical-analytical technique provides a quick first estimate, but its estimate is based on general empirical correlations, resulting in an accuracy of only 10-20%. Aerodynamic optimization, based on the adjoint sensitivity method, can be used to manage several shape variables;

however, its effectiveness depends on the choice of the initial geometry and is very computationally intensive. Using the SIMP (Solid Isotropic Material with Penalization) method, topology optimization can reduce the mass of the wing by 7-15% and requires a rational interpretation of material distribution. The combined use of topology optimization and polymer composite materials with optimized fiber layups (e.g. [0°/±45°/90°]) can lead to a significant reduction (up to one-third in some cases) in the mass of the wing. The study identifies incorporating a master geometry into CAD/CAE/PLM as a significant means of harmonizing disciplinary trade-offs, thus facilitating the design process and decreasing the number of iterative cycles in ongoing projects.

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