Parametric optimisation of composite shell structures for an aircraft Krueger flap

This paper details the conceptual design previous term optimisation next term of the configuration and previous term composite next term lay-ups used to replace the conventional honeycomb stiffened previous term structure next term of a previous term Krueger flap.next term The multiple previous term composite next term laminates selected for redesigning the lay-ups within an initial symmetrical quasi-isotropic ply configuration of [0/45/-45/90]s, had to demonstrate full orthotropic characteristics. In order to construct a numerical process to optimise the required multi-layered previous term composite shells,next term a commercial finite element code, Ansys, was used to develop a previous term parametric next term analysis file. This analysis subroutine was then integrated into an Ansys previous term Parametric next term Design Language code embedding the objective of the previous term optimisation next term process "mass minimisation" as well as all the constraints and the allowable domains of the parameters. The paper, in its conclusion, presents a comparison between the original product and the optimal design, and reviews the advantages of the future implementation of this design.