加速度计的静态校准

介绍了静态校准加速度计的方法 :地球重力法、负载法和离心机法。在用离心机法校准加速度计时 ,为了消除测量R的系统误差 ,可以采用径向R差值法。分析了这种方法的原理和误差。     

直线度误差最小条件评定不同算法的比较

本文介绍了直线度误差最小评定的0.618法和凸多边形法,并给出了这两种方法的高级语言程序。对0.618法、基准旋转法和凸多边形法等不同算法的比较进行了尝试。     

结合多种剩余推进剂测量方法的应用研究

基于＂十一五＂期间对多种航天器剩余推进剂测量方法的研究成果,分析了气体注入（压力激励）法、超声波流量计法、加速度计法、热容法以及压力-体积-温度（PVT）法和簿记（BK）法的适用范围,对这些剩余推进剂测量方法在航天器整个寿命期间不同时期的应用方案进行了研究,提出了3种典型的测量方法组合方案和应用策略.     

几种大平面平面度测量方法比较

叙述了几种大平面平面度的测量方法,分析了间接测量法、激光双光束扫描法、激光准直扫射法、衍射平面基准法、液面法等几种方法的特点及其测量误差。     

试验测定DFR的升降法方法

提出了试验测定结构件细节疲劳额定值(DFR)的升降法方法,可以充分估计并节约总试验时间.通过数值模拟比较了升降法数据处理的半子样极大似然法和马尔可夫方法.为满足可靠度要求,对半子样极大似然法估计的疲劳强度标准差进行了修正,并给出了保证95％可靠度的疲劳强度的置信度要求的最少试件数.最后给出了升降法确定DFR的表达式.      

大气延迟误差对InSAR数据处理影响的定量分析

从重复轨道InSAR测量基本原理出发, 详细给出了相位测量误差对InSAR测高、 双轨法D-InSAR形变测量、三轨法D-InSAR形变测量、四轨法D-InSAR形变测量影响的近似关系式以及大气延迟误差对相位测量影响的近似关系式; 以此为基础分别推导出了大气延迟误差对InSAR测高、双轨法D-InSAR形变测量、三轨法D-InSAR形变测量和四轨法D-InSAR形变测量影响的近似关系式, 同时以ERS-1星载系统为例进行模拟实验, 分析讨论了大气延迟误差对InSAR测高、双轨法D-InSAR形变测量、三轨法D-InSAR形变测量以及四轨法D-InSAR形变测量的影响, 从而得出了大气延迟误差对InSAR数据处理影响的结论.      

介质材料电磁参数测量综述

扼要介绍了近２０年来介质材料电磁参数测试方法的概况、趋势及技术特点。这些方法包括传输／反射法、多状态法、多厚度法、谐振腔法、自由空间法等。     

基于TIRP法的铝基复合材料均匀性检测

为检测碳化硅颗粒增强铝基复合材料的均匀性,利用与厚度无关声反射板(TIRP,Thickness Independent Reflector Plate)法对材料声速进行成像,排除了材料厚度的影响,提高了检测精度.介绍了TIRP法的基本原理和试验系统的结构,提出了一种基于双次扫描方式的TIRP实时成像方法,进一步提高了精度.利用底面反射回波法、单次扫描TIRP法和双次扫描TIRP法进行了试验,并对成像结果进行了比较,能够看出基于双次扫描的TIRP法可获得更准确清晰的声速图像.最后对误差来源进行了分析,指出了改进的方向.     

热容法测量推进剂剩余量的地面试验

摘要： 热容法作为一种新的推进剂剩余量测量方法,由于具有实施方便、测量精度高等优点,适用于卫星在轨寿命末期的推进剂测量.为了验证热容法的可行性,考察热容法的测量精度,并对星上热容法方案给出实施建议,对某贮箱进行了热容法试验验证研究.在不同加热工况下,对不同试液装填量进行试验,采集不同测温点的热响应数据,通过对试验数据的分析,得出了热容法的测量精度,验证了热容法的可行性,并且提出了具体的实施建议,为热容法的后续在轨应用提供参考.     

管芯微波参数提取技术

阐述了实际工作点下的小信号Ｓ参数提取的微波探针直接提取法和等效模型法、级联矩阵法，专用载体法等间接提取法。简述了大信号模型建立和参数提取的几种主要方法，介绍了解决管芯微波参数提取的几项关键技术，及管芯微波参数提取的几个应用实例。     

Mars ultraviolet imaging spectrometer experiment on the PLANET-B mission

An ultraviolet imaging spectrometer (UVS) has been developed for the PLANET-B spacecraft. The UVS instrument is composed of a grating spectrometer (UVS-G) and a D/H absorption cell photometer (UVS-P). The UVS-G is a flat-field type spectrometer measuring optical emissions in the FUV and MUV range between 115 nm and 310 nm with a spectral resolution of 2 – 3 nm. The UVS-P is a photometer detecting hydrogen (H) and deuterium (D) Lyman α emissions separately by an absorption cell technique. Scientific targets of the UVS experiment are the investigation of (1) hydrogen and oxygen coronas around Mars, (2) the D/H ratio in the upper atmosphere, (3) dayglow, (4) aurora and nightglow, (5) dust, clouds and ozone, and (6) the surface composition of Phobos and Deimos.     

滤环上微局部化模的正则奇点

滤环R上的模在微局部化下的性质是许多文献讨论的问题.Essen证明了Zariski滤环R上的模M若具有正则奇点,则它的微局部化Q\+μ\-S(M)作为Q\+μ\-S(R) 模仍具有正则奇点,但Q\+μ\-S(M)作为R 模是否仍具有正则奇点则不知道.对这一问题进行了讨论,并证明了若M是有正则奇点的R 模且M上的局部滤是良滤,则Q\+μ\-S(M)作为R 模是具正则奇点的模.在一定条件下解决了该问题.      

A fast satellite selection algorithm with floating high cut-off elevation angle based on ADOP for instantaneous multi-GNSS single-frequency relative positioning

With the Global Navigation Satellite System (GNSS) developing, the single-frequency single-epoch multiple GNSSs (multi-GNSS) relative positioning has become feasible. Since a larger number of the observed satellites make the instantaneous (single-epoch) positioning time-consuming, a proper satellite selection is necessary. Among the present methods, the satellite selection with a fixed high cut-off elevation angle (CEA) is least time-consuming. However, there is no criterion how large a fixed high CEA should be to achieve a high success rate and less time consumption. Besides, a fixed high CEA makes the number of visible satellites largely variable, which affects the success rate. Hence, a satellite selection strategy based on ambiguity dilution of precision (ADOP) is proposed. Firstly, the theoretical proof that the ADOP increases the least when removing satellites are all low-elevation-angle satellites is given, which is important to achieve the fast positioning with a high success rate. Then, the threshold $\beta$ is calculated for a different number of satellites and a given ADOP. The satellites are selected based on their elevation angles from high to low until $\beta$ of the selected satellites becomes smaller than the corresponding threshold; this method is called the extended floating CEA multi-GNSS (EF-multi-GNSS). The comparison of the single-frequency single-epoch positioning performance of the EF-multi-GNSS with the satellite selections based on a fixed low CEA (L-multi-GNSS) and a fixed high CEA (H-multi-GNSS) via the relative positioning experiments shows that: (1) the EF-multi-GNSS with a minimal number of satellites can achieve the fast positioning and a high success rate close to 100%. It can greatly reduce the time consumption of the L-multi-GNSS, by about 64.0%, by selecting 12.6 satellites of 23.4 satellites; (2) the floating CEA of EF-multi-GNSS eliminates the consideration how large a fixed high CEA should be, and a CEA larger than the fixed high CEA of the H-multi-GNSS makes it more suitable for different conditions.     

对异面椭圆轨道目标航天器的长期绕飞轨迹设计与控制

研究了绕飞卫星对异面椭圆轨道目标航天器进行长时间绕飞观测的轨道设计与控制问题。首先建立了适用于目标航天器运行在椭圆轨道上的长期绕飞轨迹设计模型;得到了绕飞轨迹以目标航天器为中心且保持封闭的条件。然后,考虑绕飞轨迹安全性和完成任务的相对距离需求,针对具体目标设计了长期绕飞观测轨道。绕飞过程中存在的摄动和误差影响会使绕飞轨迹不能保持封闭,不满足任务需求,为此采用双脉冲方法对绕飞轨迹进行控制。仿真结果表明,对运行在异面椭圆轨道上的目标航天器,所建立的绕飞轨迹设计模型和轨迹控制方法可以用于长期绕飞轨迹设计与控制中。     

鲁棒干扰解耦问题的几何方法

本文研究了有限离散扰动系统的鲁棒干扰解耦问题(RDDPD)。建立了I_k(A_i,B_i)—不变子空间和I_k~F(A_i,B_i)—不变子空间两个新的几何概念,并给出了这两种子空间集合的最大元(Supremal element)的几何描述。它们是Wonham(A,B)—不变子空间概念的一般化。主要结果表明:这两个新概念在RDDPD的求解中是非常重要的。文章最后还讨论了连续扰动系统的鲁棒干扰解耦问题(RDDPC),揭示了RDDPD与RDDPC之间的关系。     

The mass spectrum analyzer (MSA) onboard BEPI COLOMBO MMO: Scientific objectives and prototype results

BEPI COLOMBO is a joint mission between ESA and JAXA that is scheduled for launch in 2014 and arrival at Mercury in 2020. A comprehensive set of ion sensors will be flown onboard the two probes that form BEPI COLOMBO. These ion sensors combined with electron analyzers will allow a detailed investigation of the structure and dynamics of the charged particle environment at Mercury. Among the ion sensors, the Mass Spectrum Analyzer (MSA) is the experiment dedicated to composition analysis onboard the Mercury Magnetospheric Orbiter (MMO). It consists of a top-hat for energy analysis followed by a Time-Of-Flight (TOF) section to derive the ion mass. A notable feature of MSA is that the TOF section is polarized with a linear electric field that provides an enhanced mass resolution, a capability that is of importance at Mercury since a variety of species originating from the planet surface and exosphere is expected. MSA exhibits two detection planes: (i) one with moderate mass resolution but a high count rate making MSA appropriate for plasma analysis, (ii) another with a high (above 40) mass resolution though a low count rate making it appropriate for planetology science. Taking advantage of the spacecraft rotation, MSA will provide three-dimensional distribution functions of magnetospheric ions, from energies characteristic of exospheric populations (a few eVs or a few tens of eVs) up to the plasma sheet energy range (up to ∼40 keV/q) in one spin (4 s).     

带电粒子在中性线磁场中运动的解析轨道

本文我们计算了带电粒子在中性线磁场中运动的解析轨道。其结果是:(1)带电粒子在中性片磁场中的运动是粒子在中性线磁场或在具有北向分量的中性片磁场中的第一级近似形式。(2)带电粒子在中性片磁场中的解析轨道的第三级近似形式与电子计算机计算的数值轨道基本相同。它们仅仅在小扰动区与非小扰动区的交界线上出现一些偏差。(3)带电粒子在整个中性片磁场的运动可以分成三种形式。粒子一方面在垂直于磁场的平面上作闭合的周期性轨道运动, 同时闭合轨道的中心还沿着垂直于磁场平行于中性线方向漂移。另一方面粒子还沿磁力线方向做等速运动。(4)在小扰动区中粒子的闭合轨道是一个圆轨道, 但在非小扰动区中却是一个“8”字形轨道, 其漂移速度与小扰动区漂移方向相反, 其大小也比小扰动区漂移大很多。以上结果本文都给出一个完整的解析形式。      

Motion-planning and pose-tracking based rendezvous and docking with a tumbling target

Rendezvous and docking (RVD) with a tumbling target is challenging. In this paper, a novel control scheme based on motion planning and pose (position and attitude) tracking is proposed to solve the pose control of a chaser docking with a tumbling target in the phase of close range rendezvous. Firstly, the current desired motion of the chaser is planned according to the motion of the target. In planning the desired motion, the “approach path constraint” is considered to avoid collisions between the chaser and the target, and the “field-of-view constraint” is considered to make sure the vision sensors on the chaser to obtain tight relative pose knowledge of the target with respect to the chaser. Then, the difference between the chaser’s motion and the desired motion is gradually reduced by a pose tracking controller. This controller is based on the non-singular terminal sliding mode (NTSM) method to make the tracking error converge to zero in finite time. Since the chaser nearly moves along the desired motion and the motion is reasonable, (1) it could safely arrive at the docking port of the target with a suitable relative attitude, (2) it will be always suitably oriented to observe the target well, and (3) the magnitude of the needed control inputs are less than that in existing literatures. The numerical results demonstrate the above three advantages of the proposed method.     

Detection of the ionospheric disturbances on GPS-TEC using Differential Rate Of TEC (DROT) algorithm

The solar, geomagnetic, gravitational and seismic activities can cause spatial and temporal (hourly, diurnal, seasonal and annual) variabilities of the ionosphere. Main observable ionospheric parameters such as Total Electron Content (TEC) can be used to quantify these. TEC is the total number of electrons on a ray path crossing the atmosphere. The network of world-wide Global Positioning System (GPS) receivers provide a cost-effective solution in estimating TEC over a significant proportion of global land mass. This study is focused on the analysis of the variations of ionosphere over a midlatitude region using GPS-TEC estimates for three Sun Spot Numbers (SSN) periods. The investigation is based on a fast and automatic variability detection algorithm, Differential Rate Of TEC (DROT). The algorithm is tested using literature data on disturbances generated by a geomagnetic activity, a Solar Flare, a Medium Scale Travelling Ionospheric Disturbance (MSTID), a Large Scale TID (LSTID) and an earthquake. Very good agreement with the results in the literature is found. DROT is applied to IONOLAB-TEC estimates from nine Turkish National Permanent GPS Network (TNPGN Active) stations over Turkey to detect the any wave-like oscillations, sudden disturbances and other irregularities during December, March, June, September months for 2010, 2011, 2012 years. It is observed that DROT algorithm is capable of detecting both small and large scale variability due to climatic, gravitational, geomagnetic and solar activities in all layers of ionosphere. The highest DROT values are observed in 2010 during winter months. In higher solar activity years of 2011 and 2012, DROT is able to indicate both seasonal variability and severe changes in ionosphere due to increased number of geomagnetic storms and local seismic activities.     

Low-altitude field-aligned currents used to diagnose plasma distribution and magnetic topology in the outer magnetosphere

Field-aligned currents (FAC) can be used to determine changes in the total plasma content (TPC) of convecting flux tubes. The observed steady-state FAC system is combined with the observed equipotential pattern to determine contours of TPC as mapped to the ionosphere. Criteria for a qualitative mapping of the FAC, equipotentials and TCP contours along magnetic field lines to the equatorial plane are set up and the result is shown in figure 3. Some interesting features are: (1) There is a considerable distortion, which is most obvious near midnight, due to the existence of FAC; (2) There is a dusk to dawn component of convection across the tail; (3) The reversal of this component in the pre-midnight quadrant produces the Harang discontinuity. A discussion of time-dependent flows suggests that both plasma depletion associated with FAC and neutral lines may be necessary in a substorm expansion. Between substorm expansions, convection is faster than FAC-produced collapse of flux tubes. Finally it is pointed out that the current and electric field are probably not parallel in the tail, requiring a rethinking of tail models.