离子推力器双阶栅极系统引出性能研究

针对基于最优导流工况设计的双阶四栅栅极系统在多工况下的引出性能,采用浸入式有限元和粒子云算法(IFE-PIC)对其聚焦和引出过程进行了研究.研究结果表明,相较于相同聚焦电压下的传统栅极系统,基于最优导流工况设计的双阶四栅栅极系统由过聚焦进入正常聚焦的拐点右移,栅极系统的引出性能变差.因此建议双阶栅极离子推力器在设计时使...     

A Carbon Nano Tube electron impact ionisation source for low-power,compact spacecraft mass spectrometers

A novel ionisation source which uses commercially available Carbon Nano Tube devices is demonstrated as a replacement for a filament based ionisation source in an ion trap mass spectrometer. The carbon nanotube ion source electron emission was characterised and exhibited typical emission of 30 ± 1.7 μA with an applied voltage differential of 300 V between the carbon nanotube tips and the extraction grid. The ion source was tested for longevity and operated under a condition of continuous emission for a period of 44 h; there was an observed reduction in emission current of 26.5% during operation. Spectra were generated by installing the ion source into a Finnigan Mat ITD700 ion trap mass spectrometer; the spectra recorded showed all of the characteristic m/z peaks from m/z 69 to m/z 219. Perfluorotributylamine spectra were collected and averaged contiguously for a period of 48 h with no significant signal loss or peak mass allocation shift. The low power requirements and low mass of this novel ionisation source are considered be of great value to future space missions where mass spectrometric technology will be employed.     

Reconstruction of topside density profile by using the topside sounder model profiler and digisonde data

To improve the accuracy of the real time topside electron density profiles given by the Digisonde software a new model-assisted technique is used. This technique uses the Topside Sounder Model (TSM), which provides the plasma scale height (H_s), O⁺–H⁺ transition height (H_T), and their ratio Rt = H_s/H_T, derived from topside sounder data of Alouette and ISIS satellites. The Topside Sounder Model Profiler (TSMP) incorporates TSM and uses the model quantities as anchor points in construction of topside density (Ne) profiles. For any particular location, TSMP calculates topside Ne profiles by specifying the values of foF2 and hmF2. In the present version, TSMP takes the F2 peak characteristics – foF2, hmF2, and the scale height at hmF2 – from the Digisonde measurements. The paper shows results for the Digisonde stations Athens and Juliusruh. It is found that the topside scale height used in Digisonde reconstruction is less than that extracted from topside sounder profiles. Rough comparison of their bulk distributions showed that they differ by an average factor of 1.25 for locations of Athens and Juliusruh. When the Digisonde scale heights are adjusted by this factor, the reconstructed topside profiles are close to those provided by TSM. Compared with CHAMP reconstruction profiles in two cases, TSMP/Digisonde profiles show lower density between 400 and 2000 km.     

PEM水电解技术在航天上的应用现状与发展趋势

介绍了质子交换膜(PEM)水电解技术的特点及其在国内外航天领域的应用现状,在分析空间任务的发展趋势,以及能源、动力、环境控制与生命保障系统需求变化的基础上,认为在未来载人航天任务中,能源、动力、生保物质互用的解决方法是摆脱依赖地面支持、实现自主和可持续保障的最优途径,并指出了PEM水电解技术作为实现这一技术途径的关键环节所面临的挑战。     

基于IGES标准的NURBS虚拟仿真模型生成方法

为了生成光滑表面的虚拟模型,提出了一种基于IGES标准的NURBS虚拟仿真模型生成方法。文中详细讨论了该方法的实现过程,通过分析IGES标准,从中总结出NURBS实体模型的层次结构;设计了符合该标准的数据结构,给出了正确绘制NURBS虚拟模型的方法,最后使用实例验证提出的方法是切实可行的。     

磁等离子体发动机中离子回旋共振天线参数优化

磁等离子体发动机(Magnetoplasma Rocket Engine,MPRE)的离子回旋共振加热(Ion Cy?clotron Resonance Heating,ICRH)单元中射频天线是能量注入元件,其参数直接影响能量耦合效率.为优化ICRH天线参数,建立了ICRH中粒子模拟(Particle In Cell...     

回热式工质驱动分布式推进系统参数研究

为研究以回热后的压气机引气驱动推进器风扇的工质驱动分布式推进系统（Recuperated Gas-Driven Distributed Propulsion,RGDDP）,对其热力循环过程和能量流动展开研究。基于部件法建立了推进系统的设计点计算模型,分析了引气参数和推进器风扇压比对推进系统耗油率的影响,在此基础上,分析了推进系统耗油率对部件效率的敏感性。在不同循环参数下与涡轮电分布式推进系统（Turbo-electric Distributed Propulsion,TeDP）的耗油率进行了对比,得到了RGDDP的热力循环特征。结果表明,引气参数存在最优组合使得推进系统的耗油率最低,同时耗油率对能量传输相关的部件效率敏感性最高;与TeDP相比,涡轮前温度对推进系统的耗油率影响更大,而总压比的影响较小;总涵道比为20时,相对于TeDP,RGDDP具有一定耗油率收益,随着总压比的升高收益降低,总压比为66时仍有3%左右的收益。提高RGDDP总体效率的关键在于降低能量传输过程中的损失并提高换热效率。     

驱动卫星捕获碎片的电子回旋共振离子推力器系统优化

近年来空间碎片数量急剧增加,已经对空间飞行器造成了严重的威胁。为此提出在碎片密集区域轨道(700km～1000km高度)的碎片处理方案,即利用微小卫星在电子回旋共振(ECR)离子微推进连续切向力作用下,不断进行轨道提升并进行碎片收集。基于此,进一步对电推进系统方案进行优化设计计算,在设计寿命1年的条件下,以推进系统质量最低作为优化目标,以加速电压和工质流量为变量,对电推进系统方案进行优化。最终得到的优化结果为工质流量0.25sccm (0.0244mg/s)、加速电压2488V时,推进系统总体最优,总质量7.288kg,推力器比冲2216s,推力535μN。     

三栅极离子推力器电子反流失效影响参数的敏感性研究

电子反流失效模式是离子推力器关键失效模式之一,决定推力器工作寿命。为明确各参数对电子反流失效模式的影响程度,确定加速应力,为地面加速寿命实验验证方案和长寿命优化设计提供数据支持,采用Hybrid-PIC-MCC (Particle in Cell-Monte Carlo Collision)方法,构建了三栅极系统数值仿真模型。采用模型研究了地面真空舱本底压力、屏栅电压、加速栅电压、屏栅与加速栅间距、屏栅上游等离子体密度和放电室工质利用率等参数的影响敏感度对比。研究结果显示,真空舱本底压力可以作为加速寿命试验的首选加速应力,在推力器结构和工作本征参数中工质利用率为最敏感应力,其次是屏栅电压、屏栅上游等离子体密度、加速栅电压、屏栅和加速栅间距。     

射频离子推力器多元工质束流调节试验研究

为了获得射频离子推力器离子束流随放电参数的变化规律,采用试验研究的方法,就推力器引出束流与射频功率强度、工质种类、工质流量之间的调节规律开展了研究,搭建了射频离子推力器束流调节试验系统。研究结果表明:屏栅电压1200V,加速电压-250V,射频功率200W～700W,工质流量0.2mg/s～4.76mg/s,Xe,Ar,O_2,N_2四种工质下能够可靠放电并稳定引出,实现束流从54mA～467mA的调节,电离效率XeArO_2N_2,离子束流随射频功率和工质流量线性增加,在1.01mg/s的氙工质下,推力、比冲随射频功率从100W～400W线性增加实现推力7.35mN～27.5mN,比冲1191s～3696s大范围连续可调,工质利用率为21.1%～78.8%,并在射频功率为276W时工质利用率和功耗之间存在明显拐点,在应用中要根据任务选择最佳工作区间,合理控制工作参数可以提高推力器工作性能和效率。