Geometrical Optimisation of a Wing Strut Joint. Part I.

This paper provides the result of the geometrical optimisation of a wing strut joint of an aircraft. The objective of the geometrical optimisation was to modify the geometry of the wing strut joint components to meet an optimisation criterion defined as yield strength determined by static tensile testing. The geometrical optimisation was processed on a computer model of the wing strut joint using FEM (finite element method). The design variables assumed in this geometrical optimisation were the load option and boundary conditions of interaction between the wing strut joint components. An analysis carried out as part of the geometrical optimisation was based on proposing modifications to the geometry of the joint features at their maximum stress levels. The geometry optimisation results will be applied in the preparation and performance of validation strength testing of the wing strut joint assembly. [ABSTRACT FROM AUTHOR]