共查询到18条相似文献,搜索用时 125 毫秒
1.
2.
3.
离子推力器挡板通道结构对放电室性能至关重要,通道尺寸严重影响进入放电室的原初电子能量和速度分布。离子推力器通过设置阴极挡板可有效提高离子光学系统引出束流分布的均匀性,进而改善推力器的连续工作稳定性。介绍了Brophy关于发散场离子推力器挡板通道附近等离子体模型原理研究推导过程,以及通过实验测量卡夫曼型离子推力器挡板通道等离子体参数的分布情况,通过采用朗缪尔探针测量技术,获得挡板通道附近等离子体参数分布图,对将来10 cm离子推力器挡板通道等离子体参数分布研究起到理论指导作用。 相似文献
4.
5.
6.
7.
8.
相对于大型卫星,微纳卫星具有模块化、发射灵活、可编队飞行等特点。微阴极电弧推力器(μ-CAT)是一种适用于微纳卫星的推进装置,具有体积小、质量轻、功耗小等特点。本文分析了μ-CAT的工作原理,对推力器结构进行了设计,并利用高真空电推进实验平台,完成了对推力器放电特性实验装置的搭建。在高真空条件下对μ-CAT进行了点火试验,测试了推力器放电时的伏安特性曲线,分析了单脉冲周期的电压电流变化规律。随后分别在有无外加磁场的条件下,采用法拉第探针测量了μ-CAT等离子体离子电流空间分布情况,实验结果表明磁场具有减小等离子体羽流发散角的作用。研究工作可为后续推力器放电参数优化设计和羽流测量工作提供理论指导。 相似文献
9.
《真空科学与技术学报》2019,(1)
相对于大型卫星,微纳卫星具有模块化、发射灵活、可编队飞行等特点。微阴极电弧推力器(μ-CAT)是一种适用于微纳卫星的推进装置,具有体积小、质量轻、功耗小等特点。本文分析了μ-CAT的工作原理,对推力器结构进行了设计,并利用高真空电推进实验平台,完成了对推力器放电特性实验装置的搭建。在高真空条件下对μ-CAT进行了点火试验,测试了推力器放电时的伏安特性曲线,分析了单脉冲周期的电压电流变化规律。随后分别在有无外加磁场的条件下,采用法拉第探针测量了μ-CAT等离子体离子电流空间分布情况,实验结果表明磁场具有减小等离子体羽流发散角的作用。研究工作可为后续推力器放电参数优化设计和羽流测量工作提供理论指导。 相似文献
10.
为测量气体放电磁化等离子体离子参数,建立了一套静电离子探针诊断系统,进行了从近芯部到边缘区的离子温度分布的测量,结果与常规朗缪尔探针对电子参数的测量结果吻合。 相似文献
11.
详细介绍了当前国外在离子推力器放电室理论分析模型和数值计算模型方面的研究进展。并就每种模型的特点、应用范围、前景及所采用的模拟方法进行了叙述。 相似文献
12.
13.
离子推力器放电室内永久磁铁产生的磁场大小及分布对提高放电室放电效率和约束等离子体起着非常重要的作用。利用离子推力器性能模型并结合试验测得的束流离子生产成本,分析放电室内磁感强度大小对LIPS-200离子推力器放电室性能的影响。数值计算结果显示永久磁铁厚度增加1mm,放电室内的磁感强度从原来的5.0×10^-3~3.0×10^-2T增加至1.0×10^-2-5.0×10^-2T。理论分析结果显示磁感强度增加50%,原初电子平均约束时间增加49.9%、原初电子和中性气体之间的碰撞概率增加6.9%、离子损耗减小64%、束流离子生产成本降低18.1%、推进剂利用率提高7.4%。放电损耗、推进剂利用率与磁感强度大小呈线性关系。该研究能够为今后离子推力器设计提供一定的参考。 相似文献
14.
A new approach to the real-time diagnostics of the erosion of walls in the discharge chamber of a plasma accelerator (thruster) with closed electron drift (CED) is described. The proposed method is based on the measurement of intensities of (i) the spectral lines of atoms sputtered from the discharge chamber walls and (ii) the reference lines of the neutral working gas component. The rate of erosion of the dielectric walls in a discharge chamber of a CED thruster has been measured for the discharge voltage increased from 300 to 700 V. An experimental relationship is established that takes into account changes in the velocities and charge states of the sputtered species and allows the proposed method to be used for various discharge voltages. 相似文献
15.
We propose a new method for the analysis of the efficiency of ion generation and acceleration, which can be used to determine the ion current in a plasma accelerator (thruster) with closed electron drift. The method is based on the measurement of the energy and angular distributions of ions in the plasma jet, the discharge power, and the jet thrust. The laws of variation of the plasma thruster efficiency as a function of the discharge voltage in the interval of 300–1000 V have been studied. 相似文献
16.
Dependence of the rate of insulator erosion on the walls of discharge chamber of a Hall thruster on the propellant supply rate and magnetic field configuration at a constant discharge voltage has been studied. The regime of thruster operation was controlled by varying the propellant mass flow rate. The magnetic field configuration was optimized by monitoring the intensity of the spectral line of sputtered boron atoms. It is established that the rate of insulator erosion in the discharge chamber significantly decreases upon optimization of the magnetic field configuration, while the integral characteristics of the thruster change rather insignificantly. With the optimum magnetic field configuration, the rate of erosion of discharge chamber walls depends rather insignificantly on the propellant supply rate. 相似文献
17.
A. I. Bugrova A. V. Desyatskov Yu. V. Korobkin A. S. Lipatov V. K. Kharchevnikov 《Technical Physics Letters》2010,36(10):889-891
Integral and local characteristics of the laboratory model of a low-power plasma thruster operating in a pulsed regime have
been experimentally studied. Rectangular pulses of discharge current with the leading and trailing fronts not exceeding 1
ms have been obtained. At an average supplied electric power of ∼150 W, the propulsion efficiency amounted to 35%. The plasma
concentration, electron temperature, and potential distributions in the output plasma jet have been measured using an electric
probe. These measurements showed that a well formed plasma jet with a small divergence angle exists behind the thruster edge. 相似文献