基于数据拟合的雷达高度表告警信号测试方法

阐述了雷达高度表自动测试系统软硬件组成和原雷达高度表告警信号测试方法,指出原测试方法存在的测试效率低下问题,针对该问题提出了基于最小二乘数据拟合的雷达高度表告警信号测试方法,并给出了测试数据和实验结果.该测试方法首先应用少数激励和输出数据进行数据拟合,应用拟合函数确定发出告警信号的激励电压初始电压值,再以小电压幅度逐次调整激励电压,以完成精确测量,应用该方法可在保证测试精度的前提下大大提高测试效率.     

利用半导体二极管伏安特性进行朗缪尔探针性能测试研究

研究讨论了一种利用半导体二极管伏安特性进行朗缪尔探针性能测试的方法. 设计的朗缪尔探针性能测试方法对外界因素要求较低,在常温常压的通常实 验室环境下即可进行,其测试结果可作为利用地面等离子体环境进行定标测试 前的初步性能验证. 通过实验室环境下的测试试验, 验证了该方法的有效性和 可行性.      

探针特性曲线的初级电子修正及用离子声波速度测电子温度的研究

在Te》Ti,且存在两种电子能量的等离子体中,讨论了正确进行朗缪尔探针特性曲线修正——初级电子修正方法;用朗缪尔探针方法得到的等离子体电子温度与离子声波速度测量得到的电子温度分布实验结果比较证明,提出的初级电子修正方法是正确的．实验结果还表明,用离子声波速度测量得到的电子温度误差较小,平均测量误差△Te大约只有0．1eV,有望成为一种可行的电子温度测量方法．     

磁层电场仪前端信号处理电路研究

针对磁层稀薄等离子体环境中的电场测量,设计了一种电场仪前端信号处理电路方案.双探针电场仪通过向等离子体输出驱动电流,测量两探针间的电位差,从而测量空间电场的探测仪器.在磁层稀薄等离子体环境下,等离子体阻抗较高,电场仪探针将工作在较高的工作电压上.若探针电压接近或超过电路耐压值,则可能会影响探测结果,甚至损坏电场仪.本文结合低偏置电流的电压跟随方案和反馈悬浮电源控制方案,解决了稀薄等离子体环境中电场测量的弱电流采样和高动态电位处理问题,并采用低噪声元件和特殊电路设计,控制电路噪声.测试结果显示,本方案可使探针适应±100V的悬浮电位,实现150kHz带宽的电场信号测量,且噪声小于14nV·mHz-1/2,满足目前空间电场仪测量精度需求.      

用一对PNP/NPN晶体管组成高压放大器

这个简单的高压放大器线路提供的输出电压变动范围宽、功耗低,且只用很少的组件。用280伏的稳压电源,能产生高达260伏     

直流毫微伏电压测试方法

本文主要介绍用标准电阻组成分压器,配合精密分压箱及一般的高精度数字电压表,组成离精度毫微伏电压源,检定毫微伏数字电压表或毫微伏放大器,灵敏度达1nV,线性度达0.01％。说明测试装置的组合、测试方法以及注意事项。     

0.13μm部分耗尽SOI工艺反相器链SET脉宽传播

基于0.13 μm部分耗尽绝缘体上硅（PD-SOI）工艺,设计了一款片上反相器链（DFF）单粒子瞬态（SET）脉宽测试电路并流片实现,SET脉宽测试范围为105~3 150 ps,精度为±52.5 ps。利用重离子加速器和脉冲激光模拟单粒子效应试验装置对器件进行了SET脉宽试验。采用线性能量传输（LET值）为37.6 MeV·cm2/mg的86Kr离子触发了反相器链的三级脉宽传播,利用脉冲激光正面测试器件触发了相同级数的脉宽,同时,激光能量值为5 500 pJ时触发了反相器链的双极放大效应,脉宽展宽32.4%。通过对比激光与重离子的试验结果,以及明确激光到达有源区的有效能量的影响因子,建立了激光有效能量与重离子LET值的对应关系,分析了两者对应关系偏差的原因。研究结果可为其他种类芯片单粒子效应试验建立激光有效能量与重离子LET值的对应关系提供参考。      

自动和半自动探针台的载片台水平位移测量方法研究

为解决自动和半自动探针台的载片台水平方向位移发生偏差时,导致探针压点位置不准,从而使测试结果不可靠,甚至伤及芯片和探针的问题。根据实际工艺和溯源机构的标准器具特性,设计了标准尺的图形,在苏打玻璃上电镀5μm宽的金线条,制作成152.4mm×20mm的长方形标准尺,其测量范围为(0~150)mm。对标准尺进行了定标,定标不确定度为1.0μm。在测量范围内,进行了试验分析,评定了测量不确定度。结果表明:标准尺测量的水平位移偏差小于4μm,满足测试需求。     

火工品电参数测试技术研究

介绍了火工品电参数测试方法，搭建了火工品电参数测试系统。设计了火工品电容放电式点火电路，阐述了电容充放电原理和充放电电路的参数计算方法，实现了点火回路电流的测试。采用“四线”制测试方法实现对火工品桥路直流阻值瞬态变化特性的测试，通过点火回路电压值的变化进行了火工品桥丝熔断时间的测试，证明了采用本测试系统进行火工品电参数测试的可靠性和正确性，为火工品电参数测试的研究提供了有效的测试方法。     

火工品电参数测试技术研究

介绍了火工品电参数测试方法，搭建了火工品电参数测试系统。设计了火工品电容放电式点火电路，阐述了电容充放电原理和充放电电路的参数计算方法，实现了点火回路电流的测试。采用“四线”制测试方法实现对火工品桥路直流阻值瞬态变化特性的测试，通过点火回路电压值的变化进行了火工品桥丝熔断时间的测试，证明了采用本测试系统进行火工品电参数测试的可靠性和正确性，为火工品电参数测试的研究提供了有效的测试方法。     

Evaluation of a combined electrostatic and magnetostatic configuration for active space-radiation shielding

Developing successful and optimal solutions to mitigating the hazards of severe space radiation in deep space long duration missions is critical for the success of deep-space explorations. A recent report (Tripathi et al., 2008) had explored the feasibility of using electrostatic shielding. Here, we continue to extend the electrostatic shielding strategy and examine a hybrid configuration that utilizes both electrostatic and magnetostatic fields. The main advantages of this system are shown to be: (i) a much better shielding and repulsion of incident ions from both solar particle events (SPE) and galactic cosmic rays (GCR), (ii) reductions in the power requirement for re-charging the electrostatic sub-system, and (iii) low requirements of the magnetic fields that are well below the thresholds set for health and safety for long-term exposures. Furthermore, our results show transmission levels reduced to levels as low as 30% for energies around 1000 MeV, and near total elimination of SPE radiation by these hybrid configurations. It is also shown that the power needed to replenish the electrostatic charges due to particle hits from the GCR and SPE radiation is minimal.     

Effective Coulomb force modeling for spacecraft in Earth orbit plasmas

Coulomb formation flight is a concept that utilizes electrostatic forces to control the separations of close proximity spacecraft. The Coulomb force between charged bodies is a product of their size, separation, potential and interaction with the local plasma environment. A fast and accurate analytic method of capturing the interaction of a charged body in a plasma is shown. The Debye–Hückel analytic model of the electrostatic field about a charged sphere in a plasma is expanded to analytically compute the forces. This model is fitted to numerical simulations with representative geosynchronous and low Earth orbit (GEO and LEO) plasma environments using an effective Debye length. This effective Debye length, which more accurately captures the charge partial shielding, can be up to 7 times larger at GEO, and as great as 100 times larger at LEO. The force between a sphere and point charge is accurately captured with the effective Debye length, as opposed to the electron Debye length solutions that have errors exceeding 50%. One notable finding is that the effective Debye lengths in LEO plasmas about a charged body are increased from centimeters to meters. This is a promising outcome, as the reduced shielding at increased potentials provides sufficient force levels for operating the electrostatically inflated membrane structures concept at these dense plasma altitudes.     

三同轴屏蔽效能测试装置的研制

对国内外射频同轴连接器的屏蔽效能测试方法进行了对比研究,通过仿真、设计,研制加工了活塞式三同轴法测量屏蔽效能的测试装置,对测试系统进行了测量结果比对。通过搭建的三同轴法测试系统,建立了射频至微波频段射频同轴连接器的屏蔽效能参数测试平台。     

载人深空探测磁场主动辐射防护技术研究

基于单粒子轨道理论和蒙特卡洛方法建立了一种磁场主动屏蔽防护分析方法,针对理想磁场构型分析了屏蔽磁场强度、厚度和结构对屏蔽效果的影响。研究结果表明：屏蔽效率随磁刚度BL增大且当磁刚度BL一定时,增加磁场强度B比增加磁场厚度L更有效;对于有限长屏蔽磁场构型,端盖区需加强防护;桶状区与端盖区采用直线型屏蔽磁场的构型防护效果最好,能够对典型银河宇宙线能谱屏蔽90%的高能粒子。     

Electrostatic space radiation shielding

For the success of NASA’s new vision for space exploration to Moon, Mars and beyond, exposures from the hazards of severe space radiation in deep space long duration missions is ‘a must solve’ problem. The payload penalty demands a very stringent requirement on the design of the spacecrafts for human deep space missions. The exploration beyond low Earth orbit (LEO) to enable routine access of space will require protection from the hazards of the accumulated exposures of space radiation, Galactic Cosmic Rays (GCR) and Solar Particle Events (SPE), and minimizing the production of secondary radiation is a great advantage. There is a need to look to new horizons for newer technologies. The present investigation revisits electrostatic active radiation shielding and explores the feasibility of using the electrostatic shielding in concert with the state-of-the-art materials shielding and protection technologies. The full space radiation environment has been used, for the first time, to explore the feasibility of electrostatic shielding. The goal is to repel enough positive charge ions so that they miss the spacecraft without attracting thermal electrons. Conclusions are drawn for the future directions of space radiation protection.     

电离总剂量复合屏蔽模拟仿真及验证试验

空间环境中辐射粒子的电离总剂量效应对卫星电子器件危害严重,需要采用合适的材料进行屏蔽防护.本文采用蒙特卡罗方法模拟材料对电子的屏蔽,将双层复合屏蔽方法与单质屏蔽方法进行对比,结果表明对电子而言,复合屏蔽在屏蔽厚度足够大时比单质屏蔽效果更好.利用90Sr-90Y电子放射源进行了复合屏蔽效果的验证试验,试验结果与模拟结果规律相符,研究结果可为辐射防护的优化设计提供参考.      

Materials selection for electronic enclosures in space environment considering electromagnetic interference effect

Using low power electronic devices for space applications to reduce the mass and energy consumption has lead to electromagnetic interference (EMI) problem. Electronic enclosures are used to shield electronic devices against EMI. In the past, electromagnetic shielding has been mainly the only criteria considered in electronic enclosure design. However, there are several structural and thermal requirements for selection of shielding materials which should also be taken into account. In this research work, three quantitative materials selection methods, i.e. Digital Logic (DL), Modified Digital Logic (MDL), and Z-transformation, are employed to select the best material from among a list of candidate materials. Composite and metallic electronic enclosures are explored and the best material is selected. Z-transformation method is applicable to both of the considered case studies while DL and MDL can only be used for solving one of them. Z-transformation method ranks aluminum as the first choice among various metallic materials. The wide range of Z-transformation application and its practical results confirm the superiority of Z-transformation method over DL and MDL methods.     

基于SIMION软件的空间等离子体探测器的数值仿真

空间等离子体探测器采用带偏转板的柱形静电分析器作为传感器,具有大于320°探测视场,可探测约10eV～30keV的热等离子体。利用SIMION软件采用均匀随机抽样建立粒子源的方法仿真探测器的基本特性参数:静电分析器因子、能量分辨率、偏转板因子和偏转角。仿真结果与实测结果吻合很好。静电分析器因子的仿真与实测结果偏差为3.2%,能量分辨率仿真与实测结果偏差为1.5%,偏转角-偏转板因子的关系式与实测结果的相关系数为0.999 4。仿真结果可以有效地应用于该类仪器的设计和定标过程中。     

降噪技术在瞬态应变测试中的应用研究

主要研究在瞬态环境下应变测试的干扰问题。文章从硬、软两个方面入手,讨论了在爆轰环境下出现的一些典型的干扰现象,分析了干扰源及干扰引入途径,并通过设计改进电路、系统的接地、屏蔽等方法提出了抗干扰措施。采用了小波分析和数字滤波等数字信号处理方法来解决信号的降噪问题。     

屏蔽材料对木星轨道卫星内部介质充电效应的影响研究

在木星轨道的空间辐射环境中,占主导地位的粒子是能量大于1MeV（甚至高于100MeV）的高能电子,这可能会产生卫星内部介质充电效应。在卫星的防辐射设计中,通常需要一定厚度的材料来屏蔽这些电子,使得进入卫星内部的电子通量达到安全的水平。利用所建立的GEANT4-RIC（radiation induced conductivity）方法,研究了运行于木星轨道的卫星对高能电子的最佳屏蔽材料设计。研究了铝、钛、铁、铜、钽和铅作为卫星屏蔽材料的可能性。研究结果表明,在木星探测任务中,为了减轻卫星内部介质充电效应,高原子序数材料比低原子序数材料在相同质量下提供的屏蔽效果更好。因此,用钛、铁、铜、钽或铅代替地球轨道卫星上常用的屏蔽材料铝,可以节省屏蔽质量。