Thermal protection mechanism of heat pipe in leading edge under hypersonic conditions |
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Authors: | Peng Wengen He Yurong Wang Xinzhi Zhu Jiaqi Han Jiecai |
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Institution: | a School of Energy Science &; Engineering, Harbin Institute of Technology, Harbin 150001, China;
b Center for Composite Materials, Harbin Institute of Technology, Harbin 150001, China |
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Abstract: | Sharp local structure, like the leading edge of hypersonic aircraft, confronts a severe aerodynamic heating environment at a Mach number greater than 5. To eliminate the danger of a material failure, a semi-active thermal protection system is proposed by integrating a metallic heat pipe into the structure of the leading edge. An analytical heat-balance model is established from traditional aerodynamic theories, and then thermal and mechanical characteristics of the structure are studied at Mach number 6-8 for three refractory alloys, Inconel 625, C-103, and T-111. The feasibility of this simple analytical method as an initial design tool for hypersonic aircraft is assessed through numerical simulations using a finite element method. The results indicate that both the isothermal and the maximum temperatures fall but the von Mises stress increases with a longer design length of the leading edge. These two temperatures and the stress rise remarkably at a higher Mach number. Under all investigated hypersonic conditions, with a 3 mm leading edge radius and a 0.15 m design length, the maximum stress exceeds the yield strength of Inconel 625 at Mach numbers greater than 6, which means a material failure. Moreover, both C-103 and T-111 meet all requirements at Mach number 6-8. |
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Keywords: | Aerodynamic heating Hypersonic vehicles Metallic heat pipe Thermal protection Thermoanalysis |
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