Aircraft wing structural design optimization based on automated finite element modelling and ground structure approach

Abstract

An optimization procedure combining an automated finite element modelling (AFEM) technique with a ground structure approach (GSA) is proposed for structural layout and sizing design of aircraft wings. The AFEM technique, based on CATIA VBA scripting and PCL programming, is used to generate models automatically considering the arrangement of inner systems. GSA is used for local structural topology optimization. The design procedure is applied to a high-aspect-ratio wing. The arrangement of the integral fuel tank, landing gear and control surfaces is considered. For the landing gear region, a non-conventional initial structural layout is adopted. The positions of components, the number of ribs and local topology in the wing box and landing gear region are optimized to obtain a minimum structural weight. Constraints include tank volume, strength, buckling and aeroelastic parameters. The results show that the combined approach leads to a greater weight saving, i.e. 26.5%, compared with three additional optimizations based on individual design approaches.

Keywords:

• aircraft wing
• structural optimization
• automated finite element modelling
• ground structure approach

Funding

This work was supported by the National Natural Science Foundation of China [grant number 51305351], [grant number 51205315], [grant number 51210008]; Science Foundation of Aeronautics of China [grant number 2012ZB53012]; Fundamental Research Foundation of NPU [grant number JCY20130126], [grant number 13GH014610].