Design and Fabrication of a Stringer Stiffened Discrete- Tube Actively Cooled Panel for a Hypersonic Aircraft,
BELL AEROSPACE TEXTRON BUFFALO NY
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This report presents the results of a program which optimized the design of a full-scale 0.61 x 6.1 m 2 x 20 ft actively cooled panel for minimum panel mass. Design conditions and requirements were representative of those for a hypersonic transport. Details of the panel design were finalized on the basis of results from static and fatigue test specimens which incorporated major design features. Six large fatigue specimens, 0.1 x 0.2 m 4 x 8 in. were tested by the Langley Research Center of NASA. A 0.61 x 1.22 m 2 x 4 ft test panel was fabricated and delivered to the Langley Research Center for assessment of the thermal and structural features of the optimized panel design. The panel concept incorporated an unshielded skin actively cooled by a network of discrete, redundant, counterflow passages interconnected with appropriate manifolding, and assembled by adhesive bonding. The cooled skin was stiffened with a mechanically fastened conventional substructure of stringers and frames. The cooling passages were parallel to the stringers. A 40 water60 glycol solution was the coolant.
- Structural Engineering and Building Technology