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用于非平衡热等离子体数值模拟的物理数学模型 被引量:8
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作者 张晓宁 李和平 +1 位作者 a.b.murphy 夏维东 《高电压技术》 EI CAS CSCD 北大核心 2013年第7期1640-1648,共9页
准确的物理数学模型,包括基本控制方程及与其相应的等离子体热力学与输运性质计算公式,是采用数值模拟方法深入研究非平衡热等离子体体系中传热、流动及其他复杂物理化学过程的基础。为此从Boltzmann方程出发,首先推导出描述等离子体中... 准确的物理数学模型,包括基本控制方程及与其相应的等离子体热力学与输运性质计算公式,是采用数值模拟方法深入研究非平衡热等离子体体系中传热、流动及其他复杂物理化学过程的基础。为此从Boltzmann方程出发,首先推导出描述等离子体中不同组分质量守恒、动量守恒和能量守恒方程以及电流连续性方程等基本控制方程,然后采用修正的Chapman-Enskog方法推导出等离子体输运性质参数,包括扩散系数、粘性系数、电子和重粒子平动热导率和电导率等的表达式。不仅在保证等离子体体系质量、动量、能量和电荷通量自洽的前提下封闭了控制方程,而且与现有广泛采用的描述平衡态热等离子体特性的模型间的自洽性也得到了保证。另外,采用所提出的方法推导出的非平衡热等离子体物理数学模型可以避免对目前仍存在争议的定压比热、反应热导率等参数的定义和计算。 展开更多
关键词 热等离子体 非平衡特性 控制方程 输运性质 Chapman-Enskog方法 数值模拟 自洽性
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Modelling Study to Compare the Flow and Heat Transfer Characteristics of Low-Power Hydrogen,Nitrogen and Argon Arc-Heated Thrusters 被引量:5
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作者 王海兴 陈熙 +3 位作者 潘文霞 a.b.murphy 耿金越 贾少霞 《Plasma Science and Technology》 SCIE EI CAS CSCD 2010年第6期692-701,共10页
A modelling study is performed to compare the plasma flow and heat transfer characteristics of low-power arc-heated thrusters (arcjets) for three different propellants: hydrogen, nitrogen and argon. The all-speed S... A modelling study is performed to compare the plasma flow and heat transfer characteristics of low-power arc-heated thrusters (arcjets) for three different propellants: hydrogen, nitrogen and argon. The all-speed SIMPLE algorithm is employed to solve the governing equations, which take into account the effects of compressibility, Lorentz force and Joule heating, as well as the temperature- and pressure-dependence of the gas properties. The temperature, velocity and Mach number distributions calculated within the thruster nozzle obtained with different propellant gases are compared for the same thruster structure, dimensions, inlet-gas stagnant pressure and arc currents. The temperature distributions in the solid region of the anode-nozzle wall are also given. It is found that the flow and energy conversion processes in the thruster nozzle show many similar features for all three propellants. For example, the propellant is heated mainly in the near-cathode and constrictor region, with the highest plasma temperature appearing near the cathode tip; the flow transition from the subsonic to supersonic regime occurs within the constrictor region; the highest axial velocity appears inside the nozzle; and most of the input propellant flows towards the thruster exit through the cooler gas region near the anode-nozzle wall. However, since the properties of hydrogen, nitrogen and argon, especially their molecular weights, specific enthMpies and thermal conductivities, are different, there are appreciable differences in arcjet performance. For example, compared to the other two propellants, the hydrogen arcjet thruster shows a higher plasma temperature in the arc region, and higher axial velocity but lower temperature at the thruster exit. Correspondingly, the hydrogen arcjet thruster has the highest specific impulse and arc voltage for the same inlet stagnant pressure and arc current. The predictions of the modelling are compared favourably with available experimental results. 展开更多
关键词 low-power arcjet plasma flow and heat transfer numerical modelling propellant-type effects
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