Structural Stability of Aerospace Structures

Dear Colleagues,

Aerospace structures, be it a launcher, aircraft, or a space satellite, are lightweight structures, aimed at carrying the flight loads at minimal mass, to enable a viable economical usage. Under compression and/or shear forces, those structures are liable to buckling, changing their load carrying capacity.

Those structures are built from basic components, like beams (columns), plates, shells (cylindrical, conical, spherical) and panels. Other advanced components would include stiffened panels and stiffened shells, to increase their load carrying capacity at a relatively low addition of mass. While plates have a stable post-buckling behavior, shells would present a non-stable one, with a relatively large difference between the calculated and experimental buckling loads.

From the material point of view, Aerospace Structures have evolved from metal structures to laminated composite and/or sandwich-based structures, with the latest advancement being the variable angle tow (VAT) composites structures aimed at providing an optimal layup for increased load carrying capability at a reduced weight. The proposed Special Issue addresses this broad range of topics, and would welcome manuscripts on: (i) analytical and computational stability of aerospace structures, (ii) experimental results and procedures to increase the accuracy of the predicted buckling loads, (iii) numerical and experimental results of VAT composite structures, (iv) stability of lightweight structures in the presence of cutouts; and (v) behavior of aerospace structures under combined loadings. Any other related topics will also be most welcomed.

Prof. Haim Abramovich
Guest Editor

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