Publisher's Synopsis
This paper examines the aeroelastic stability of an on-orbit installable Space Shuttle patch panel. CFD flutter solutions were obtained for thick and thin boundary layers at a free stream Mach number of 2.0 and several Mach numbers near sonic speed. The effect of structural damping on these flutter solutions was also examined, and the effect of structural nonlinearities associated with in-plane forces in the panel was considered on the worst case linear flutter solution. The results of the study indicated that adequate flutter margins exist for the panel at the Mach numbers examined. The addition of structural damping improved flutter margins as did the inclusion of nonlinear effects associated with a static pressure difference across the panel. Scott, Robert C. and Bartels, Robert E. Langley Research Center AEROELASTICITY; BOUNDARY LAYERS; COMPUTATIONAL FLUID DYNAMICS; DYNAMIC STRUCTURAL ANALYSIS; SPACE SHUTTLES; STRUCTURAL VIBRATION; TILES; VIBRATION DAMPING; NONLINEARITY; MACH NUMBER
