氩气感应耦合等离子体速度与温度数值模拟

为了获得用于研究再入飞行器热防护系统的感应耦合等离子体风洞流场数据，基于流场、电磁场和化学场的多场耦合建立了非平衡态感应耦合等离子体数值模型。利用该模型对不同入口质量流率和不同工作压力下的感应耦合等离子体进行了数值模拟，得到了相应工作参数下感应耦合等离子体温度与速度的分布特性。计算结果表明：等离子体中心线上的速度随着入口质量流率的增大而增大，而随着工作压力的增大而减小；同时，等离子体中心线上的温度随着入口质量流率的增大而减小，而随着压力的增大先减小后增大。这些结果可为感应耦合等离子体风洞优化设计及其工业应用提供理论指导。     

Numerical simulation of the thermal non-equilibrium flow-field characteristics of a hypersonic Apollo-like vehicle

In order to investigate the relationship between the flow-field parameters outside the vehicle and the altitude, this paper takes the Atmospheric Reentry Demonstrator (ARD) with an angle of attack of -20° as the research object and adopts a two-temperature model coupled with the shear-stress transport k-ω turbulence model to focus on the variation of flow-field parameters including flow-field pressure, Mach number and temperature with the reentry altitude. It is found that the flow-field high-pressure region and low-Mach region both appear in the shock layer near the head of the ARD, while the maximum pressure of the surface appears on the windward side of the ARD's head with a toroidal distribution, and the numerical magnitude is inversely proportional to the radius of the torus. With fluid through the shoulder of the ARD flow expansion plays a dominant role, the airflow velocity increases, the Mach number of the windward side of the rear cone increases and the flow-field pressure and surface pressure rapidly decrease. When the fluid passes through the shock layer, the translational-rotation temperature will increase before the vibration-electron temperature, there is a thermal non-equilibrium effect and the two temperatures will rapidly decrease again when approaching the surface of the ARD due to the existence of temperature gradient. At the same time, both the windward side of the shoulder and the back cover of the ARD suffer from a large thermal load and require thermal protection.     

非平衡感应耦合等离子体流场与电磁场作用机理的数值模拟

以航天领域中研究再入飞行器热防护系统的感应耦合等离子体(inductively coupled plasma, ICP)风洞为研究对象,通过流场-电磁场-化学场-热力场-湍流场多场耦合求解研究ICP风洞流场与电磁场的分布特性及其相互作用机理.数值模拟中,基于热化学非平衡等离子体磁流体动力学模型准确模拟了空气ICP的高频放电、焦耳加热、能量转化、粒子内能交换等过程,通过多物理场耦合计算模拟得到了100 kW级ICP风洞内空气等离子体的电子温度、粒子数密度、洛伦兹力、焦耳加热率、速度、压强、电场强度的分布规律.研究结果表明:在感应线圈区靠近等离子体炬壁附近,等离子体流动处于热力学非平衡状态;洛伦兹力对感应线圈区空气粒子的动量传递和电子热运动起着控制作用.