离子注入已被证明是改善蓝宝石光学和机械表面性能的一种可靠方法。本文选择不同能量和剂量的镁/钛离子注入蓝宝石。利用TRIM(Transport of Ion Matter)程序分析了镁/钛离子在蓝宝石晶体中的射程分布。利用拉曼光谱和掠入射X射线衍射分...离子注入已被证明是改善蓝宝石光学和机械表面性能的一种可靠方法。本文选择不同能量和剂量的镁/钛离子注入蓝宝石。利用TRIM(Transport of Ion Matter)程序分析了镁/钛离子在蓝宝石晶体中的射程分布。利用拉曼光谱和掠入射X射线衍射分析了损伤层深度和微结构变化。离子注入结果显示,蓝宝石的纳米硬度、纳米划痕和红外性能等均呈现出可调节的特性。展开更多
This paper studies the thermoelastic fracture in a solid under non-classical Fourier heat conduction.The temperature field and the associated thermal stresses are solved by the dual integral equation technique.Both th...This paper studies the thermoelastic fracture in a solid under non-classical Fourier heat conduction.The temperature field and the associated thermal stresses are solved by the dual integral equation technique.Both thermally insulated crack and heated crack are considered.It is found that the crack tip thermal stress is singular and can be expressed in terms of the thermal stress intensity factor in a closed-form.Numerical results show that the crack considerably amplifies the local thermal stresses,confirming the significance of the effect of non-classical heat conduction on the thermoelastic fracture mechanics of materials.展开更多
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 the...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 a0.15 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.展开更多
基金National Natural Science Foundation of China(11002043)Fundamental Research Funds for the Central Universities(HIT.KLOF.2010028)。
文摘离子注入已被证明是改善蓝宝石光学和机械表面性能的一种可靠方法。本文选择不同能量和剂量的镁/钛离子注入蓝宝石。利用TRIM(Transport of Ion Matter)程序分析了镁/钛离子在蓝宝石晶体中的射程分布。利用拉曼光谱和掠入射X射线衍射分析了损伤层深度和微结构变化。离子注入结果显示,蓝宝石的纳米硬度、纳米划痕和红外性能等均呈现出可调节的特性。
基金supported by the National Natural Science Foundation of China (Grant Nos. 10972067 and 11172081)
文摘This paper studies the thermoelastic fracture in a solid under non-classical Fourier heat conduction.The temperature field and the associated thermal stresses are solved by the dual integral equation technique.Both thermally insulated crack and heated crack are considered.It is found that the crack tip thermal stress is singular and can be expressed in terms of the thermal stress intensity factor in a closed-form.Numerical results show that the crack considerably amplifies the local thermal stresses,confirming the significance of the effect of non-classical heat conduction on the thermoelastic fracture mechanics of materials.
基金financially supported by the Foundation for Innovative Research Groups of the National Natural Science Foundation of China(No.51121004)the Fundamental Research Funds for the Central Universities(No.HIT.BRETIV.201315)
文摘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 a0.15 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.
