The Influence of Longitudinal and Transversal Beams on Grid Structure Design Optimization Using GA and FEM, Case: Stiffened Panel

Abstract

Abstract. The stiffened panel is a simple model of an aircraft wing structure that has a complex structural response phenomenon. In general, the aircraft's wing structure consists of skin and reinforcement attached straight along the wingspan.The grid structure that is popular in space vehicles such as rockets, in this study is applied to the wing structure panel that can be used to build aircraft wing boxes. This paper presented the results of the optimization of the grid structure design for the stiffened panel model using geneticalgorithmsand finite element method with limited optimization variables namely skin thickness and reinforcement thickness.Static analysis with the optimization target of minimum structural weight for basic structure configuration, basic structure with additional transversal beams, and basic structure with additional longitudinal beams showed a significant reduction in structural weight compared to the initial weight. The optimum results for static analysis still need to be tested from the aspect of structural stability in this case the buckling factor so that the panel structure becomes safe if it receives a compression load. The results of the buckling factor correction indicate the need to increase the thickness of the skin and the thickness of the reinforcement significantly to obtain a buckling factor greater than or equal to one, as required in the buckling theory.

Keywords: Stiffened panel;grid structure; GA;FEM;buckling