Analysis of Unconventional Wing Structures of a Hyper-X Hypersonic Flight Research Vehicle for the Mach 7 Mission

Abstract

Heat transfer, thermal stresses analyses were performed on the unconventional wing structures of a Hyper-X hypersonic flight research vehicle (designated as X-43) subjected to nominal Mach 7 aerodynamic heating. A wing mid span cross section was selected for the heat transfer and thermal stress analyses. Thermal stress analysis was performed on three regions of the upper wing skin; 1) a fore wing panel, 2) an aft wing panel, and 3) a unit panel at the middle of the aft wing panel. A fourth thermal stress analysis was performed on a mid-span wing segment. Thermal stress analysis and panel deformation results are presented.