Paper number 1349

STRESS-STRAIN STATE INVESTIGATION OF ADHESIVE LAYER IN SANDWICH STRUCTURE OF FLYING VEHICLE

Huang Song-Jeng¹, Dr. Kobelev V.N.², and Dr. Kobelev V.V.³

1Department of Flying Vehicle Manufacture, Moscow State Aviation Technology University, K8 D19 Str.Krasnokazamennaya, Moscow, 111250, RUSSIA
2Department of Flying Vehicle Manufacture, Moscow State Aviation Technology University, 27, Petrovka St., Moscow K-31, 103767 RUSSIA
3Department of Research and Development CAD/CAE/Optimization, Fa. Muhr und Bender,
P.O. 360, Attnedorn, GERMANY

Summary

Sandwich structure has high bending stiffness characteristics with little resultant weight penalty. It is why sandwich panels and shells have widely been used in aerospace, ship building and other industries. Experimental investigation and testing of sandwich structure reveal that structural deterioration begins at different places for the two construction methods. In glued structures deterioration starts at the interface between the core and the facing. For brazed structures the core material closest the brazing deteriorates first. This rises interest in investigation of adhesive layer to know the theoretical and experimental stress-strain distribution of adhesive layers under particular load conditions.

Keywords

adhesive layer, core, facing sheet, stress-strain state, and deterioration.