Structural optimization of wing skin considering requirement of continuity of thickness

Based on the finite element, a method based on full stress rule is proposed for the thickness optimization of wing skin. Firstly based on full stress rule, the thickness of each element is updated. Then in order to meet the requirement of continuity, the thickness of each element is modified by weighted average method. After performing the weighted average method, an overall modification is implemented for skin thickness distribution to ensure that all elements satisfies the stress constraints. This method is applicable to problems involving with metal skin and composite skin. Finally, numerical examples demonstrate the feasibility and effectiveness of the proposed method.