N2���������ŵ���΢���������ŵ�ת���PIC/MCģ��

开发了氮空心阴极放电PIC/MC二维自洽模型。研究了N2传统空心阴极向微空心阴极放电转变过程中电势和电场的变化。结果表明,不同尺寸的空心阴极放电的电势及电场分布规律几乎类似,但空心阴极孔径减小且气压增加时,电场近似线性增加;典型微空心阴极电场比传统空心阴极放电电场约大3个量级;微空心阴极放电产生的电子,氮分子离子和氮原子离子的密度比传统空心阴极放电约大3个量级,且微空心阴极放电中,N2+密度比N+密度大8倍以上。     

N_2空心阴极放电向微空心阴极放电转变的PIC/MC模拟

开发了氮空心阴极放电PIC/MC二维自洽模型。研究了N2传统空心阴极向微空心阴极放电转变过程中电势和电场的变化。结果表明,不同尺寸的空心阴极放电的电势及电场分布规律几乎类似,但空心阴极孔径减小且气压增加时,电场近似线性增加;典型微空心阴极电场比传统空心阴极放电电场约大3个量级;微空心阴极放电产生的电子,氮分子离子和氮原子离子的密度比传统空心阴极放电约大3个量级,且微空心阴极放电中,N2+密度比N+密度大8倍以上。     

大气压微等离子体射流电子密度研究

采用微空心阴极放电装置,利用光学方法和电学方法研究了大气压流动Ar和N₂混合气体中产生的微等离子体射流特性。研究发现,随着电源输入功率增大到一定数值,微空心阴极装置中两个电极间气体发生击穿,通过击穿气隙气体的流动会沿着气流方向产生最大为4 mm的等离子体射流。放电电流为准连续的脉冲放电形式,其中放电电流脉冲宽度约为0.1 μs。分别利用爱因斯坦方程和等离子体发射光谱中谱线的Stark展宽方法计算了电子密度。结果发现,2种计算方法得出的微等离子体射流的电子密度均在1015·cm-3的量级。研究还发现,功率对微等离子体射流电子密度影响不大。利用气体击穿理论,对以上结论进行了定性分析。     

大气压氩直流微放电光谱研究

微空心阴极放电或微放电是一种能够实现高气压下放电的有效方法。利用不锈钢空心针作阴极,不锈钢网作阳极,进行了大气压氩直流微放电实验研究。测量了大气压氩微放电光谱,发现氩气的发 射谱线主要集中在690～860 nm范围,且全部为氩原子4p—4s的跃迁。实验研究了不同放电电流、气体压强、气体流量与谱线强度之间的关系,发现谱线强度随放电电流、气体流量增加均增加,而谱线强 度随压强变化呈现不同特征：谱线强度随压强的增加先增加后降低,在13.3 kPa时强度最大。此外,选用跃迁波长为763.51和772.42 nm的两条光谱线,利用发射谱线强度比值法测量了氩气微放电等离子 体的电子激发温度。结果显示,其电子激发温度处于2 000～2 800 K之间,且随放电电流的增加而增加,随气体压强和气体流量的增加而降低。     

N2微空心阴极放电特性及其阴极溅射的PIC/MC模拟

采用两维PIC/MCC模型模拟了氮气微空心阴极放电以及轰击离子 (N₂⁺,N⁺) 的钛阴极溅射. 主要计算了氮气微空心阴极放电离子 (N₂⁺,N⁺) 及溅射原子Ti的行为分布, 并研究了溅射Ti 原子的热化过程. 结果表明: 在模拟条件下, 空心阴极效应是负辉区叠加的电子震荡; 在对应条件下, 微空心较传统空心放电两种离子 (N₂⁺,N⁺) 密度均大两个量级, 两种离子的平均能量的分布及大小几乎相同; 在放电空间N⁺的密度约为N₂⁺的1/6, 最大能量约大2倍; 在不同参数 (P, T, V)下, 轰击阴极内表面的氮离子(N₂⁺,N⁺)的密度近似均匀, 其平均能量几乎相等; 从阴极溅射出的Ti原子的初始平均能量约6.8 eV, 离开阴极约0.15 mm处几乎完全被热化. 模拟结果为N₂微空心阴极放电等离子体特性的认识提供了参考依据. 关键词： 微空心阴极放电 PIC/MC模拟 2等离子体')" href="#">N₂等离子体     

加速电压和阳极流率对离子推力器性能的影响

为了研究离子推力器输入参数对工作性能的影响,采用试验研究和理论分析的方法研究了离子推力器加速电压和阳极流率对离子推力器性能的影响.研究结果表明:一定范围内离子束流随着加速电压绝对值的减小不断减小,然后突然增大,大、小推力模式下的电子返流极限电压分别为–140 V和–115 V,放电电压、放电损耗随阳极流率减小单调增大,减速电流单调减小,通过调节阳极电流、栅间电压、工质气体流量,功率为300—4850 W下,推力为11—188 m N,比冲为1800—3567 s,效率为34%—67%,在3000 W时推力器最高效率达到67%,该转折点对推力器设计和应用有关键意义,应用要结合在轨任务剖面选择合理的工作参数区间.     

20cm离子推力器放电室流场计算模拟

为了优化20cm离子推力器放电室内部推进剂供气方式,研究了在不发生气体放电时,推力器阳极和主阴极供气接口处的流体速度和压强,并以此开展推力器放电室内部的流场计算。结果表明:采用单阳极供气管方式,阳极出口处压强为4~158Pa,气流出口速度为0.1~47m/s;阴极小孔出口处的压强约为33.1Pa,出口速度约为12m/s;考虑真空系统的返流作用时,单阳极供气管方式下放电室内部压强为0.001~0.4Pa,大部分区域Xe原子数密度为(0.2~3)×1018/m3,在靠近栅极的部分区域数密度达到9×1019/m3左右;在增加阳极组件的供气管数量后,阳极的气体出口速度为18~40m/s,放电室压强为0.03~0.1Pa,大部分区域Xe原子数密度为(0.72~2.4)×1019/m3,靠近阳极与主阴极进气端的小部分区域原子数密度约2×1017/m3,且放电室内部原子密度整体分布较为均匀。     

激光烧蚀掺杂金属粉工质的推进性能

 为结合金属高比冲和聚合物工质高冲量耦合系数的优点,为激光推进光船优选工质,对掺入金属粉末的聚甲醛(POM)工质在CO₂激光辐照下的推进性能开展了实验研究。结果表明：在一定的条件下金属粉末能提高工质的推进性能。掺入微米铝粉的聚甲醛工质的冲量耦合系数最大值由12×^-5 N/W提高到21.72×10^-5 N/W,在直筒结构的约束下,最高冲量耦合系数和比冲分别提高到61.64×^-5 N/W和727.32 s,能量利用率超过了100%,表明工质参与了化学反应。     

用于太阳能推进的可折叠展开式伞状龙骨聚光器

为有效提高空间太阳能聚光器的聚光效率,提出了一种用于太阳能热推进器的具有伞状龙骨结构的可折叠展开式抛物面太阳能聚光器设计方案,该方案可以克服充气展开式抛物面聚光器和刚性固定抛物面聚光器具有的技术难题。设计了一个聚光功率100 kW,开口圆半径4.9 m的可折叠展开式伞状龙骨结构正焦抛物面聚光器,利用Fluent软件,对太阳能热推进器进行了模拟和性能预示,以氢气为工质气体,得到系统的推力和比冲可以分别到达10.23 N和701.4 s。结果表明:这种推进器具有比冲高、推力适中的特点,可以用于微小卫星、纳卫星的轨道转换及姿态控制。     

一种新型微空阴极结构的大气压射频冷等离子体源

介绍微空阴极的结构和物理机理，着重介绍一种新型大气压下射频激励的大面积冷等离子体源——融合空心阴极(fused hollow cathodes，FHC).结合应用和与之有关的研究，简单介绍空心阴极的放电特性，以及影响其放电特性的因素，如阴极材料、气体种类、频率、气体流速、气压、阴极内径等.另外提到了其他两种相关的微空阴极系统. 关键词： 微空阴极 大气压 冷等离子体 射频     

Microhollow cathode sustained discharges: comparative studies in micro- and equivalent macro-cell geometries

We present an experimental study of discharge initiation in a three-electrode configuration consisting of a microhollow cathode discharge (MHCD) and a third planar electrode, biased positively and placed some distance away. This work is based on the microcathode sustained (MCS) configuration where the MHCD acts as a plasma cathode and enables the generation of a stable, non-equilibrium plasma at high pressure in the volume between the MHCD and the third electrode. Our experiments were carried out in two different set-ups, one using a MHCD as a cathode and another in an “equivalent” macrocell geometry, easier to implement and operating at lower pressure in which the same phenomena are observed. Consistent with previous modeling results, we find that the plasma column in the volume between the MHCD and the third electrode is characterized by a low reduced electric field, with values similar to those expected for a positive column. The ignition voltage of the plasma column depends on the voltage difference between the MHCD and the third electrode, the MHCD current, and the gas pressure and gap spacing.     

Spectroscopic measurements and electrical diagnostics of microhollow cathode discharges in argon flow at atmospheric pressure

This paper is dedicated to the study of the electrical and optical characteristics of direct current microhollow cathode discharges (MHCD) in argon flow. Experiments have been carried out in order to determine the so-called Paschen’s curves in a static open MHCD. Current-voltage characteristics were obtained as a function of the pressure and hole diameter. MHCD enable stable direct current discharge operation, which could be ignited for pressures ranging from 12 to 800 Torr, in a very wide range of current densities and electrodes materials. Optical emission spectroscopy and analysis of the spectral line broadening of plasma line emissions were performed in order to measure parameters such as electron number density (2–4 × 10¹⁴ cm^-3)^{-3}), gas temperature (460–640 K), excitation temperature (~ 7000 K) and electron temperature (~ 8500 K), for current ranging from 7 to 15 mA. Lower gas temperature was measured compared to the static MHCD ones.     

Characterization of electrospray beams for micro-spacecraft electric propulsion applications

Electric propulsion for spacecraft offers many advantages compared to other traditional counterparts such as chemical propulsion. An electrostatic colloid thruster, well suited for small spacecrafts due to its inherent small size, is investigated. The underlying phenomena governing the plume, namely collisions and focusing are parameterized. The determining properties of the electrospray-based thruster, such as specific impulse, are measured for several propellants and demonstrated to be higher than cold-gas thrusters even for singly charged droplet mode. Moreover, the interesting concept of a dual colloid system with positively and negatively charged cone-jet beams was shown to be feasible by simulations and experiments.     

A 200-W permanent magnet Hall thruster discharge with graphite channel wall

A 200-W Hall thruster was designed using permanent magnets placing the axial maximum magnetic field outside of the channel, and the anode/gas distributor as an integrated U-shaped structure. A split structure is adopted for the discharge channel to conveniently change the wall material. With the initial conditions that the anode mass flow is maintained at 0.8 mg/s, 1.0 mg/s and 1.2 mg/s over a voltage range of 150–400 V (at 50 V intervals), the discharge properties were determined for the two thruster models with the channel walls composed of graphite and boron nitride (BN). The results demonstrate that under identical operating parameters, the properties of the thruster with the graphite channel walls are similar to the properties of the thruster with the BN channel walls. The maximum difference of the discharge current between the two wall materials is 6.2%; the maximum difference of the thrust and the specific impulse is 3.3%, and that of the anode efficiency is 1.7% (absolute value). These differences are smaller than the corresponding parameter differences observed from changing wall materials in other common Hall thrusters.     

外磁场作用下的磁等离子体动力学过程仿真

磁等离子体动力学推力器是空间高功率电推进装置的典型代表,磁等离子体动力学过程是其核心工作机制.为深入理解外磁场对其工作特性的影响,本文采用粒子云(particle in cell,PIC)方法结合基于自相似准则的缩比模型,进行外加磁场作用下磁等离子体动力学推力器工作过程的建模仿真,通过与实验结果对比验证模型和方法的可靠性,并重点分析推力器点火启动过程的等离子特性参数分布,以及外磁场和阴极电流对推力器工作性能的影响.研究结果表明:阴阳极放电电弧构建是推力器启动和高效工作的关键步骤;外磁场强度较低工况不利于构建稳定放电电弧,等离子体束流集中于轴线附近,推力主要产生机制是自身场加速;外磁场强度较高时,阴阳极放电电弧稳定,推力产生主要机制是涡旋加速,推力、比冲随外磁场强度线性增大;推力器效率随阴极电流和外磁场强度增大而增大;放电电压随阴极电流增大而增大,但随外磁场强度的增大表现出先减小后增大的趋势.     

外磁场作用下的磁等离子体动力学过程仿真

磁等离子体动力学推力器是空间高功率电推进装置的典型代表,磁等离子体动力学过程是其核心工作机制.为深入理解外磁场对其工作特性的影响,本文采用粒子云(particle in cell,PIC)方法结合基于自相似准则的缩比模型,进行外加磁场作用下磁等离子体动力学推力器工作过程的建模仿真,通过与实验结果对比验证模型和方法的可靠性,并重点分析推力器点火启动过程的等离子特性参数分布,以及外磁场和阴极电流对推力器工作性能的影响.研究结果表明:阴阳极放电电弧构建是推力器启动和高效工作的关键步骤;外磁场强度较低工况不利于构建稳定放电电弧,等离子体束流集中于轴线附近,推力主要产生机制是自身场加速;外磁场强度较高时,阴阳极放电电弧稳定,推力产生主要机制是涡旋加速,推力、比冲随外磁场强度线性增大;推力器效率随阴极电流和外磁场强度增大而增大;放电电压随阴极电流增大而增大,但随外磁场强度的增大表现出先减小后增大的趋势.     

Field Emission Electric Propulsion: Emission Site Distribution of Slit Emitters

Field emission electric propulsion is the technological application of the principle of liquid metal ion sources as thrusters in electric space propulsion. Research work sponsored by the European Space Agency (ESA) on a slit-type field ion thruster is reported and discussed. The most significant new features of its emission performance are as follows: For the first time, a slit emitter with a closed propellant supply system was fired in any optional direction, requiring, in principle, no gravitational forces. Quantitative data relating the constituents of the residual gas atmosphere to the wetting behavior of the liquid metal propellant and the emission site distribution were obtained. A homogeneous distribution of equally spaced emission sites was observed; the measured spacing is in good agreement with a simple hydrostatic model of wavelike instabilities on electrically stressed surfaces of fluids.     

微型电子回旋共振离子推力器离子源结构优化实验研究

微型电子回旋共振(ECR)离子推力器可满足微小航天器空间探测的推进需求. 为此, 本文开展直径20 mm的微型ECR离子源结构优化实验研究. 根据放电室内静磁场和ECR谐振区的分布特点, 研究不同微波耦合输入位置对离子源性能的影响, 结果表明环形天线处在高于ECR谐振强度的强磁场区域时, 微波与等离子体实现无损耦合, 电子共振加热效果显著, 引出离子束流较大. 根据放电室电磁截止特性, 结合微波电场计算, 研究放电容积对离子源性能的影响, 实验表明过长或过短的腔体长度会导致引出离子束流下降甚至等离子体熄灭. 经优化后离子源性能测试表明, 在入射微波功率2.1 W、氩气流量14.9 μg/s下, 可引出离子束流5.4 mA, 气体放电损耗和利用率分别为389 W/A和15%.     

Particle-in-cell simulation for the effect of magnetic cusp on discharge characteristics in a cylindrical Hall thruster

The cylindrical Hall thruster has the good prospect of serving as a miniaturized electric propulsion device.A 2 D-3 V particle-in-cell plus Monte Carlo(PIC-MCC) method is used to study the effect of the magnetic cusp on discharge characteristics of a cylindrical Hall thruster.The simulation results show that the main ionization region and the main potential drop of the thruster are located at the upstream of the discharge channel.When the magnetic cusp moves toward the anode side,the main ionization region is compressed and weakened,moving upstream correspondingly.The ionization near the cusp is enhanced,and the interaction between the plasma and the wall increases.The simulation results suggest that the magnetic cusp should be located near the channel exit.