Preliminary design of morphing flaperon using optimization by genetic algorithm

Abstract

Purpose This article presents an approach to morphing flaperon design. The presented design workflow attempts a simple structural arrangement of trailing edge morphing for applicability in the short term. The purpose of this paper is to test the optimization of the geometry built in for future multidisciplinary flaperon optimization techniques.Design/methodology/approach To meet the contrary requirements on stiffness and compliance of the morphing structure, the design is performed as a multi-objective optimization problem solved using a genetic algorithm. The objective function for optimization incorporates the failure index, target deflection and actuation force for both upper and lower deflection. To produce the single objective value a weighting is used. The constraints and conditions are used to reduce the resulting dependency on weighting factors selection. The described problem was solved using Matlab scripting, combined with a structural Nastran finite element method solver to determine individual's properties for evaluation and selection.Findings The problem formulation and design workflow fulfill the goal. The obtained set of parameters defines the morphing flaperon geometry, that allows achieving the described deflections with the required failure indexes and with minimal actuation force, therefore verifying the morphing mechanism. The design workflow proved feasible and will be further developed.Originality/value The presented workflow allows to find the geometry for specified material properties and airfoil shape. Therefore, an engineering approach is offered to assess the combination structurally for the specified deflection range with minimal actuation force. The morphing trailing edge in combination with a laminar airfoil has not been given much attention yet.

Purpose This article presents an approach to morphing flaperon design. The presented design workflow attempts a simple structural arrangement of trailing edge morphing for applicability in the short term. The purpose of this paper is to test the optimization of the geometry built in for future multidisciplinary flaperon optimization techniques.Design/methodology/approach To meet the contrary requirements on stiffness and compliance of the morphing structure, the design is performed as a multi-objective optimization problem solved using a genetic algorithm. The objective function for optimization incorporates the failure index, target deflection and actuation force for both upper and lower deflection. To produce the single objective value a weighting is used. The constraints and conditions are used to reduce the resulting dependency on weighting factors selection. The described problem was solved using Matlab scripting, combined with a structural Nastran finite element method solver to determine individual's properties for evaluation and selection.Findings The problem formulation and design workflow fulfill the goal. The obtained set of parameters defines the morphing flaperon geometry, that allows achieving the described deflections with the required failure indexes and with minimal actuation force, therefore verifying the morphing mechanism. The design workflow proved feasible and will be further developed.Originality/value The presented workflow allows to find the geometry for specified material properties and airfoil shape. Therefore, an engineering approach is offered to assess the combination structurally for the specified deflection range with minimal actuation force. The morphing trailing edge in combination with a laminar airfoil has not been given much attention yet.