悬摆法测量气体推进剂激光推进冲量耦合系数

 给出了悬摆法测量激光推进冲量耦合系数的原理，分别以空气、氩气、氮气和氦气为推进剂，用悬摆法测量了抛物形推力器在能量不同的单脉冲TEA CO₂激光辐照下的冲量耦合系数。实验结果表明：氩气的冲量耦合系数最高，氦气的冲量耦合系数最低；在实验测试的激光能量范围内，4种推进剂气体的激光推进冲量耦合系数基本上都随着激光能量的增加而线性增大，冲量耦合系数的相对误差为5.4%~6.4%。实验结果与国外相关实验结论一致。     

微小卫星贮箱内两相流界面变形定位及控制管理

液化气推进技术是微小伴随卫星在轨飞行采用的一种新型推进技术。微小伴星空间调姿、变轨过程需精确的推力控制,因此必须了解卫星推进系统中推进剂的形位分布。本文理论分析了空间微重力环境下液化气推进剂气/液界面的形位分布及变化,并通过落塔实验验证了微重力环境下有效控制液体推进剂的管理方法。     

电弧加热发动机尾流的光谱诊断

电弧加热发动机是一种为航天器提供机动和控制推力的装置。由于比冲远高于传统的使用化学推进剂的发动机,近年来,电弧加热发动机引起了愈来愈多的关注。为了了解电弧加热发动机的工作过程机理,讨论了电弧加热发动机尾流的诊断方法并设计了一套光谱诊断系统。在此系统上,以氩气为工作气体,设定气流量和电流,在模拟空间环境下对电弧加热发动机尾流的光谱信号进行了采集。实验结果表明系统具有较高的信噪比,可以忽略噪音对光谱信号强度的影响,采集到的数据能够真实地反映物理过程。通过对采集到的谱线强度信号进行分析和处理,得到了尾流中氩的谱线发射系数的径向分布,并进一步得到了尾流平均激发温度的径向分布。实验结果表明电弧加热发动机的尾流处在热力学非平衡态下,因而用谱线强度法测温时选用不同的谱线,得到的温度值是不同的。     

Emission of Ions from a Nonequilibrium Plasma

A model of a plasma ion emitter is considered for two types of velocity distribution of plasma electrons: the sum of two Maxwellian velocity distributions with different temperatures and the sum of a Maxwellian distribution and a directed flux. Criteria for the formation of a plasma emission surface are derived. The effect of the parameters of the electron distribution on the magnitude of the perturbation of the quasi-neutral emitting plasma by the external electric field of the negative electrode and on the emission current density is considered. A comparison with the Bohm case is performed.     

Miniaturized liquid metal ion sources (MILMIS)

Introductory remarks are given on ion sources, and basic features of liquid-metal ion sources (LMISs) are outlined. A special by-product of field-emission electric space propulsion by a liquid metal ion thruster is the slit emitter, which may be qualified as a semiminiaturized LMIS. The state-of-the-art technology of field-emitter arrays common in vacuum microelectronics is presented in view of the fabrication of miniaturized, integrated, liquid-metal ion sources (MILMISs). The possibility of operation of these devices even in the field-emission mode as miniaturized liquid-metal electron sources (MILMESs) is discussed. An outlook is given on prospective applications of MILMISs and MILMESs, including micromachining and microelectronic device technology (e.g., focused ion-beam techniques), space technology (e.g., ion thrusters with integrated neutralizers), and pulsed power technology (e.g., high-power switching and ion beam sources for inertial confinement fusion)     

Electron and ion emission from liquid metal surfaces

The application of positive or negative electric fields to small-area liquid metal surfaces leads to very high brightness DC ion or pulsed electron emission. The stabilization of a cone-shaped structure by the balance of electrostatic and surface tensions forces is described. Electron and ion emission occurs by field emission and field evaporation mechanisms     

Computer simulation of liquid metal ion source optics

A numerical calculation of the electric field and current density distribution for a liquid metal ion (LMI) source has been carried out. If a field evaporation mechanism for ion formation is assumed an elongated Taylor cone shape emitter is required to account for the observed total currents. Trajectory calculations including the effect of uniform space charge have been carried out as a function of total current and particle mass. The predicted emission characteristics compare favorably with experimental results for Ga, however the homogeneous space charge model is unable to account for all of the experimentally observed increase in beam divergence with increasing mass and current.     

液态电极等离子体发射光谱技术检测金属离子的研究应用

快速准确的金属离子检测是涉及多个学科领域及检测技术的研究课题,文章综述了液体电极等离子体发射光谱技术在金属离子检测领域的研究及应用。首先介绍了基于电化学原理的电极法,包括离子选择性电极及阳极溶出法,及基于原子吸收或发射光谱等检测金属离子常用方法技术的原理及优缺点;然后阐述了基于等离子体的液体电极光谱技术的原理及特点,包括等离子体的产生机理、光谱特点以及其检测技术的优势;并按照液态电极数目及放电系统结构分成单液态电极及双液态电极放电系统两类,重点介绍了液态电极发射光谱技术的发展历程及研究进展,其中详细说明了ELCAD、SCGD、LS-APGD及毛细管放电等电解质放电系统的结构及特点;利用液态电极等离子体发射光谱技术,对铜、汞、银等重金属以及钠、钾、镁等活泼金属离子的检测限可达μg·L-1。最后探讨了该技术应用于检测金属离子的优势及存在的问题,并展望了其应用前景。     

Global Numerical Model for the Assessment of the Effect of Geometry and Operation Conditions on Insert and Orifice Region Plasmas of a Thermionic Hollow Cathode Electron Source

Thermionic hollow cathodes have been widely used in wide variety of areas such as spacecraft electric propulsion systems, material processing and lasers for more than half a century as efficient electron sources. Especially in electric propulsion systems, hollow cathodes are being used as electron sources for propellant ionization and ion beam neutralization. Moreover, it is also a promising candidate for utilization as a stand‐alone propulsion system in microsatellites or nanosatellites due to its small physical size, low power consumption and ease of operation. On the other hand, the small geometry of the typical orificed hollow cathodes makes the plasma diagnostics difficult which is why numerical studies become important for understanding the driving physical processes behind their operation, and the effects of the geometry and the operation parameters on cathode performance. In this paper, a global numerical model for the insert and orifice plasma of a hollow cathode is presented where volume averaged plasma parameters are considered for both regions. The results of this study show that the developed model can be used for designing and sizing orificed hollow cathodes as comparisons with the results of experimental and other numerical studies are in good agreement with the ones obtained from the developed model. (© 2014 WILEY‐VCH Verlag GmbH & Co. KGaA, Weinheim)     

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%.     

The State of Arts of Hall Thruster

Electric propulsion is broadly defined as the acceleration of a working fluid for propulsion by electrical heating and/or by electric and magnetic body forces. Compared with chemical propulsion, electric propulsion has the characteristic of higher specific impulse, lower thrust, lighter weight and longer lifetime. So electric propulsion is generally suitable for satellite attitude control, the orbit transfer and raising, orbit correction, resistance compensate, position keeping, reposi- tion, space exploration and interplanetary flight.     

场致爆炸发射阴极表面微凸起热效应的数值研究

研究场致发射电流密度与阴极表面微凸起顶部的温度之间的高度非线性关系,用数值方法计算在外加宏观电场条件下,不同顶底半径比微凸起的热效应.结果表明:当微凸起顶底半径比值不同时,由于微凸起的微观电场增强因子不同,当微凸起顶部温度达到阴极材料的熔点时,微凸起内部温度分布差异显著;当外加宏观电场相同时,微凸起的顶底半径比越小,爆炸发射延迟时间越短;对于顶底半径比确定的微凸起而言,爆炸电子发射延迟时间随外加宏观电场强度的减小而成指数规律增长.     

Flowing and Nonflowing Liquid Electrode Discharge Microplasma for Metal Ion Detection by Optical Emission Spectrometry

Abstract

Liquid electrode discharge microplasma offers a simple, portable, and small platform for fast spectrochemical determination of metal ions in solution samples with lower consumption of consumables (e.g., working gases, electric current, and cooling water). Various liquid electrode discharge devices for metal ions determination with optical emission spectrometry have been developed in the past 20 years. We aim here to provide an overview of this field and to show the similarities and differences, and strengths and weaknesses of different flowing liquid electrode discharge systems and nonflowing liquid electrode discharge systems. We also discuss sample flow rates in flowing systems, required sample volume in nonflowing systems, and the two systems’ applications to real complex samples in this review.     

高频感应等离子体流动模型与微型电推进器流场特性分析

微型射频离子推力器具有结构简单、工作寿命长、推力动态范围大、性能调节响应灵敏等特点,是国际微电推进领域的研究热点之一.射频离子推力器电离室内的感性耦合放电等离子体特性和推力器的性能密切相关.为此,文章建立了低气压、小尺寸微型射频离子推力器电离室内感性耦合等离子体流体模型,开展了电磁场、流场、化学反应浓度场的多物理场耦合仿真分析,并研究了等离子体放电特征参数随推进剂工质气压、放电吸收功率、射频频率以及线圈匝数等因素的变化规律.结果表明,推进剂工质气压、放电吸收功率是调节微型射频离子推力器性能的主要因素,该研究为综合调控微型射频离子推力器的工作性能奠定了良好的基础.      

Spatial and Temporal Characteristics of an Excimer Laser-Induced Lead Plasma Emission

A laser-induced plasma was generated from a lead target using an ArF excimer laser (λ = 193 nm) and characterized by time-resolved and time-integrated spatially resolved spectrometry. The ambient atmosphere (gas composition and pressure) influenced the emission intensity for both atomic and ionic lines. The emission of laser-induced lead plasma varied with time as well as the location in the plasma. Lead ion emission decayed more rapidly than lead atomic line emission. High excitation temperatures and nonlinear optical phenomena were observed in the laser-induced lead plasma. Gas breakdown and the subsequent shielding effect of the incident laser beam in different ambient gas compositions and pressures were discussed to explain the different efficiency of metal ion for matioa in the plasma. The experimental results show that spatial discrimination of the laser-induced plasma emission is desirable for direct spectrochemical analysis.     

含石墨烯二维金属结构中的自发辐射研究

研究原子在金属结构中的自发辐射时引入单层石墨烯薄膜,利用石墨烯特殊的光电特性来调控原子的自发辐射率.推导了局态密度与自发辐射率的格林函数表示形式,并结合频域有限差分方法进行了数值模拟.分析结果表明:随着化学势的增大,自发辐射波峰出现蓝移现象,且自发辐射率波峰得到增强,理论上实现了原子自发辐射率峰值位置与幅度的调制.研究结果可以为新型纳米器件及光电子设备的制造和优化提供参考.     

基于Kr工质的离子推力器栅极PIC仿真

Kr是新型低成本离子推力器的优选工质之一。采用三维PIC粒子模拟方法对Kr等离子体在栅极系统中的输运过程进行仿真,并与Xe工质仿真结果进行对比,分析工质类型对束流分布、离子通过率、发散角损失和推力等参数特性和分布的影响。结果表明:相比于Xe工质,Kr工质条件下,屏栅上游鞘层区域更大,屏栅离子通过率略有上升;Kr+在加速栅孔轴向速度较大,径向位移小,撞击加速栅几率小,加速栅电流相对较小;Kr工质和Xe工质的发散角损失相当,但Kr工质工作电流区域更高;相比于Xe工质,相同功率条件下Kr工质的推力值约降低20%。     

Space electric propulsion plasmas

Electric thrusters offer the promise of a substantial improvement in performance over that of conventional chemical rockets currently used in space propulsion applications. There are three basically different ways in which electrical power and propellant inputs might be combined to produce thrust: (1) propellant can be heated electrically and then expanded through a nozzle; (2) electromagnetic body forces can be applied to accelerate a plasma to the desired exhaust velocity; or (3) electrostatic body forces can be applied to accelerate charged particles. Electric thrusters are classified in accordance with the mechanism by which they induce thrust as electrothermal, electromagnetic, and electrostatic. The characteristics of plasmas in electric thrusters along these lines are considered     

Electrical and piezoresistive properties of ion beam deposited DLC films

In present study diamond like carbon (DLC) films were deposited by closed drift ion source from the acetylene gas. The electrical and piezoresistive properties of ion beam synthesized DLC films were investigated. Diode-like current–voltage characteristics were observed both for DLC/nSi and DLC/pSi heterostructures. This fact was explained by high density of the irradiation-induced defects at the DLC/Si interface. Ohmic conductivity was observed for DLC/nSi heterostructure and metal/DLC/metal structure at low electric fields. At higher electric fields forward current transport was explained by Schottky emission and Poole–Frenkel emission for the DLC/nSi heterostructures and by Schottky emission and/or space charge limited currents for the DLC/pSi heterostructures. Strong dependence of the diamond like carbon film resistivity on temperature has been observed. Variable range hopping current transport mechanism at low electric field was revealed. Diamond like carbon piezoresistive elements with a gauge factor in 12–19 range were fabricated.     

Solid-like ablation propulsion generation in nanosecond pulsed laser interaction with carbon-doped glycerol

A solid-like propellant of carbon-doped glycerol ablated by a nanosecond pulsed laser is investigated. The results show that the specific impulse increases with increasing carbon content, and a maximum value of 228s is obtained. The high specific impulse is attributed to the low ablated mass loss that occurs at high carbon content. More importantly, with increasing carbon content, the properties of the doped glycerol approach to those of a solid. These results indicate that propulsion at the required coupling coefficient and specific impulse can be realized by doping a liquid propellant with an absorber.