电轴法在超精密电容式传感器中的应用

在电场理论中电轴法的基础上 ,导出了局部场域的电容计算式 ,为电容传感器在精密测量中的应用提供了理论依据 ,这为经典的电轴法开辟了新的应用领域并给出了几种粗糙度等级的被测表面的近似值与精确计算结果的对比。     

卫星无线传能系统主动电场屏蔽效能分析

针对无线传能系统宽频段电场辐射屏蔽的需求,建立了采用主动屏蔽方式的无线传能系统屏蔽效能分析电路模型。推导出主动屏蔽激励源可由无线传能系统电压激励源控制。给出了空间点位置和面位置屏蔽效能计算公式,通过对激励电压源进行傅里叶变换后提取关注频段电压分量可实现对宽频段屏蔽效能的分析。通过仿真分析证明了方法的有效性,屏蔽效能与空间位置有关,同时受限于传输效率的约束。通过调节压控电压源的压控系数可以在传输效率损失相对较小的情况下实现关注位置电场辐射的有效屏蔽。最后通过实验验证了无线传能系统主动屏蔽方式屏蔽效能分析方法的正确性和工程可应用性。     

管路加热带安装工艺试验研究

针对推进剂管路加热带缠绕工艺流程复杂、工艺参数不定量的问题开展试验研究,结合工程实践经验,采用试验矩阵方法研究获取绝缘膜包覆状态、涂胶厚度以及气泡对加热效果的影响。结果表明,内绝缘膜无交叠缠绕、外绝缘膜间隙缠绕、利用专用刮胶板控制涂胶厚度约0.2 mm等工艺方法可以减少气泡的产生,有效提升加热带对管路的加热效果,满足产品质量要求,该试验结论可为后续管路加热带缠绕及其他加热片安装提供参考。     

电推进羽流诊断中阻滞势分析器的快速处理算法

介绍了一种基于统计方法分析阻滞势分析器响应曲线的数据处理算法. 该算法可以在电推进诊断中快速提取待测粒子的环境参数. 通过对阻滞势分析器测量得到的U-I响应曲线物理性质的分析, 推导出以曲线中所有测量值为基础提取粒子温度和密度的统计处理算法. 以具体卫星电推进诊断中对阻滞势分析器的测量要求以及工程参数为例, 设计并进行了仿真模拟实验. 在设计要求的测量范围内, 利用本文算法得到的离子密度的平均误差为6.62 %, 粒子温度的平均误差为7.45 %. 通过分析算法运算量, 在实际工程中采用12 MHz主频的8031处理器可以在0.5 s内完成本算法全部处理过程.     

An internal power angle control strategy for high-speed sensorless brushless DC motors

High-speed Brushless DC Motors(BLDCMs) usually adopt a sensorless control strategy and operate in three-phase six-state drive mode. However, the sampling errors of the rotor position and the driving method increase the Internal Power Angle(IPA), resulting in a decrease in the efficiency of the system. Conventional IPA reduction strategies are either sensitive to motor parameters, or ignore diode freewheeling during the commutation process, or require additional current sensors. In this paper, a ...     

自旋平台双球型电场仪数据校正方法

双球型电场仪通过测量两探针的电势差和间距获得空间电场.当电场仪应用于自旋平台时,因柔性伸杆扰动带来的双球位置偏差会影响电场计算结果.本文提出一种利用自旋平台上两个电探针的电场探测自洽特性对探针位置进行校正的方法,实现了对双球型电场仪在轨数据的校正.对探空火箭电场仪的实测数据处理过程是在消除平台对电场仪的干扰后,使用所提出的校正方法对测量电场的矢量大小和方向进行校正.通过将修正结果与未校正数据和理论模型数据进行对比,验证了方法的有效性.     

ICME期间磁暴的太阳风参数和极光沉降能量

基于1995-2004年ICME驱动的强烈磁暴（SA型）、强磁暴（SB型）和延迟型主相暴（SC型）三种磁暴类型,对1AU处太阳风动压、太阳风速度、行星际磁场、E_K-L电场以及极光沉降能量进行时序叠加分析,并分别与-vB_z耦合函数和Newell耦合函数进行对比.结果表明,三种磁暴在ICME到达前期的太阳风动压较稳定,背景太阳风、极光沉降能量、行星际磁场和磁层存在相对平静期.ICME到达前期SA型磁暴的背景太阳风速度、行星际磁场南向分量以及极光沉降能量的均值高于另外两种磁暴类型,这说明大型日冕物质抛射在ICME到达前就对行星际磁场、背景太阳风和HP产生了影响.磁暴急始后,SC型磁暴的E_K-L电场斜率小,峰值延后且行星际磁场北向分量增强,这些都是磁暴主相延迟的表现,极光沉降能量随着行星际磁场转为南向而增加.     

嫦娥四号着陆区织女陨坑电场环境数值模拟

由于太阳紫外、X射线和太阳风粒子作用,近月表形成尘埃等离子体环境,而月表陨坑地形使得这种尘埃等离子体环境更为复杂.本文以位于嫦娥四号着陆区的织女陨坑为研究对象,基于高程数据构造了该陨坑的三维模型.根据太阳-月球关系和陨坑地理坐标信息,计算了陨坑白天任意时刻的有效太阳辐照度分布,探讨了不同时刻陨坑内外的光照面积占比,得到陨坑随地方时而发生的遮蔽效应特征.同时,基于月表充电方程计算了织女陨坑在不同地方时条件下的平衡表面电势、德拜鞘高度和电场强度分布,发现陨坑自身遮蔽效应对坑内电场环境影响十分明显.以坑底中心为例,讨论了地方时和纬度对类织女陨坑的平衡表面电势、德拜鞘高度及电场强度的影响,结果表明三者变化特征均以正午时刻及赤道为界呈对称分布,越接近12：00LT或者越接近赤道,坑底中心的平衡表面电势和电场强度越高,德拜鞘高度越低.     

Ionospheric response to the storm-time disturbance of 29 May, 2010

The Ionospheric F2-layer peak parameters response to a magnetic storm had been investigated over Ilorin, Nigeria (Lat. 8:53°N, Long. 4.5°E, dip angle, −2.96°), Jicamarca, Peru (11.95°S, 76.87°W, dip angle, 0.8°) and Hermanus, South Africa (34.42°S, 19.22°E, dip angle, −60.77°), using percentage enhancement/depletion values. Our results showed an enhancement in NmF2 at all of these stations. Averagely, pre-noon and post-noon peaks are highest at Ilorin during quiet time. The similar pattern observed for quiet condition between Ilorin and Jicamarca was due to their latitudinal positions. For disturbed NmF2 condition, Jicamarca and Ilorin recorded higher peaks at nighttime than during the daytime for the storms main phase, and the reverse over Hermanus. The nighttime and daytime increases were observed respectively at Ilorin and Hermanus during the recovery period. The hmF2 variation recorded higher enhancement at Jicamarca during the daytime and at Hermanus at nighttime during the main phase. During the recovery phase, the highest enhancement was recorded during the daytime at Jicamarca, and over Hermanus at nighttime. These observations find their explanation in the magnetospheric current, solar wind and E × B drift.     

Use of coated silicon field emitters as neutralisers for fundamental physics space missions

Spacecraft neutralisers are required as part of the ion propulsion system for accurate station keeping in fundamental physics missions. This paper describes the use of thin layers of insulating materials as coatings for the gated silicon field emitter array structure used in a spacecraft neutraliser. These thin coatings are postulated to reduce power consumption and reduce overheating. The power consumption and lifetime of aluminium nitride and amorphous hydrogenated diamond-like carbon coatings have been tested by current–voltage and endurance tests. Diamond-like carbon coatings were promising, performing better in endurance tests than uncoated samples, but further work is required to characterise the coating’s physical properties and its effects on field emission. The thermal conductivity of the coating material had little effect on measured sample lifetimes. Aluminium nitride had reduced power consumption compared to diamond-like carbon coated and uncoated samples. A thin (∼5 nm) layer of aluminium nitride was found to be optimal, meeting European Space Agency specifications for the neutraliser engineering model.