High performance metallic compression panels: assessment of weight reduction obtained by using advanced aluminum alloys and optimum geometry

Frederic Bron
2011 52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference   unpublished
Integrally stiffened panels for upper wing application made of aluminum alloys are subjected to pure compression loading. A numerical procedure based on finite-element and analytical simulations is set to determine the optimum shape and therefore minimum weight of the structure. The influence of the material compression behavior, the stringer shape, the stringer pitch and a longitudinal friction stir weld is assessed by simulations and experiments. The axial compressive load flow (load per unit
more » ... flow (load per unit width) is either 1750 N/mm or 4400 N/mm which covers up to short range aircrafts. Use of AIRWARE™ ™ ™ ™ materials combined with optimized designs makes it possible to reach a weight reduction of 24% compared with standard design with 7050 T7451 material on both load flows. Based on ten tests, a fair agreement is obtained between simulations and experiments. Test results are very reproducible. A longitudinal friction stir weld has no influence on the collapse load. At low load flow, design has the largest impact on weight reduction, in particular reduced stringer pitch. On the contrary, at high load flow, the largest gain comes from the use of high strength, low density alloy (AIRWARE™ ™ ™ ™).
doi:10.2514/6.2011-1718 fatcat:fk2vplmr6jc7jogs5fbw67bt6i