The short wavelength deflections of the shuttle orbiter skin panels when subjected to in-plane compressive forces

摘要

The Space Shuttle Orbiter's forward fuselage outer shell is an aluminum skin and hat section stringer design. The skin panels support a thermal protection system where the short wave length deflections of the skin panels are inputs to the stress analysis. The skin panel buckling characteristics control the short wave length deflections characterized by the deflected shape wave length and wave amplitude. A computer program based on an energy solution to the panel buckling problem calcualtes the buckling load and wave lengths of interest. A strain analysis of the panel defines the deflected shape amplitudes. Test panels loaded with in plane loads through their post buckling regime verified the strength, wave form and post buckling amplitude. the analysis techniques include adjustments to match the experimental data. Presented are the deflection analysis techniques for general and local buckling for both flat and curved panels.