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

By National Aeronautics and Space Administration

Heat transfer, thermal stresses, and thermal buckling 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 midspan cross section was selected for the heat transfer and thermal stress analyses. Thermal buckling analysis was performed on three regions of the wing skin (lower or upper); 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 buckling analysis was performed on a midspan wing segment. The unit panel region is identified as the potential thermal buckling initiation zone. Therefore, thermal buckling analysis of the Hyper-X wing panels could be reduced to the thermal buckling analysis of that unit panel. "Buckling temperature magnification factors" were established. Structural temperature-time histories are presented. The results show that the concerns of shear failure at wing and spar welded sites, and of thermal buckling of Hyper-X wing panels, may not arise under Mach 7 conditions.Ko, William L. and Gong, LeslieArmstrong Flight Research CenterHYPERSONIC VEHICLES; TEMPERATURE EFFECTS; STRUCTURAL ANALYSIS; STRESS ANALYSIS; HEAT TRANSFER; X WING ROTORS; WING PANELS; THERMAL BUCKLING; FAILURE; AERODYNAMIC HEATING

• Format: Paperback
• Language: English
• ISBN: 1723901423
• ISBN13: 9781723901423
• Release Date: January 1
• Publisher: Independently Published
• Length: 46 Pages
• Weight: 0.29 lbs.
• Dimensions: 0.1" x 8.5" x 11.0"