Benchmark of wrinkling formulae and methods for pre-sizing of aircraft lightweight sandwich structures

Sandwich structures are widely used in many industrial applications and especially light aviation. The local buckling phenomenon named “wrinkling” is one of the primary causes compressive failure such structures. Its calculation a difficult practical problem since this cannot be captured by GFEM (Global Finite Element Model) classically for aircraft structure sizing. Therefore, pre-sizing involves use wrinkling model, which can found literature. In practice, models with high safety factors industry. This paper proposes an evaluation analytical formulas setting. Realistic involve framework (3D stress state, orthotropy, skin asymmetry) far from assumptions on most formulations based. case study sandwich composite beam subjected to uni-axial load. Limitations studied quantified discussion relevance using simple design structured composites developed.