Buckling analysis of composite sandwich panels used in satellite payload fairing structure

In this paper, buckling analysis of a composite sandwich panel used in payload fairing structure is done and effects of various parameters on the structure buckling are investigated using finite element method. To this end, first, finite element model is validated for an aluminum honeycomb core and carbon/epoxy facesheets by the experimental results presented in literatures. Then, the effect of various parameters such as the core and facesheets thicknesses, material and structure of core, hybrid composite facesheets and facesheets layouts on the critical buckling load of panel is investigated. The composite panel is modeled as a 1/16th sector of thin cylindrical shell and is meshed using 6 mm linear cubic elements. The panel is considered without initial geometrical imperfections and cracks. According to the results, panel with hybrid facesheets consisting of titanium alloy and carbon/epoxy has the best buckling strength, 78% increase in critical buckling load compared to the basic panel.