Hypersonic plane hot structure thermal protection system.

摘要

This thesis is to examine the thermal protection system capable of operating on an airframe without the thermal insulation tile (block of silica) being used on the Shuttle outer skin at extreme temperatures, in hostile aero-thermo-chemical environments, and at extreme stress as the Hypersonic Flight Vehicle will be exposed to during acceleration to orbit or during re-entry maneuvering. One way of thermal management is to circulate heat-absorbing fluid in hybrid heat-pipes which actively cools the three-dimensional oxidized protective coated carbon-carbon composite exterior skin and internally cool the adjacent airframe structure with hydrogen fuel. This concept will slow or stop the skin and airframe structure from reaching its critical temperature when the structure material begins to lose its material characteristics.; A leading edge model was used to represent the hot structures. It features chordwise and spanwise refractory metal heat pipes embedded within a carbon-carbon primary structure. A nonlinear thermal and a linear structure three-dimensional finite element analyses proved the concept to be feasible within the limits of assumptions made in the analyses when internal radiative cooling is used during ascent. However, internal radiative cooling was found to be unnecessary during re-entry (descent). The linear stress analysis showed large thermal stress on the model's refractory heat pipe walls.