地球同步轨道卫星结构爆炸解体碎片的轨道仿真

为快速确定与预报卫星在轨爆炸解体产生的大量空间碎片的轨道,提出了一种基于ANSYS/AUTODYN、MATLAB、STK等多软件平台联合仿真分析卫星结构爆炸解体碎片运行轨道的方法。利用ANSYS/AUTODYN对典型薄壁圆柱模拟地球同步轨道卫星结构进行爆炸数值分析,得到碎片的数量、质量分布和速度特性信息。再利用MATLAB软件对卫星爆炸仿真得到的碎片参数进行处理,将处理后的数据导入到STK软件的通用摄动SGP4模型中,得出卫星爆炸碎片的早期轨道数据。最后对爆炸碎片的轨道分布、速度增量、轨道演化等进行分析。结果表明:该方法能满足大量爆炸碎片的轨道仿真要求,能有效提高碎片轨道信息转换效率,对目前难以跟踪的cm级以下碎片,也能提供相应的初始轨道数据,使用方便,通用性好。研究结果可为快速捕获卫星爆炸碎片,及时规避航天器碰撞风险提供参考。     

GOCE star tracker attitude quaternion calibration and combination

We analyse the inter-boresight angles (IBA) measured by the star trackers on board the GOCE satellite and find that they exhibit small offsets of 7–9″ with respect to the ones calculated from the rotation of the star tracker reference frames to the satellite reference frame. Further, we find small variations in the offsets with a peak-to-peak amplitude of up to 8″, which correlate with variations of the star trackers’ temperatures. Motivated by these findings, we present a method for combining the attitude quaternions measured by two or more star trackers that includes an estimation of relative attitude offsets between star trackers as a linear function of temperature. The method was used to correct and combine the star tracker attitude quaternions within the reprocessing of GOCE data performed in 2018. We demonstrate that the IBA calculated from the corrected star tracker attitude quaternions show no significant offsets with respect to the reference frame information. Finally, we show that neglecting the star tracker attitude offsets in the processing would result in perturbations in the gravity gradients that are visible at frequencies below 2?mHz and have a magnitude of up to 90?mE. The presented method avoids such perturbations to a large extent.     

“忠诚僚机”式有人/ 无人机协同作战概念 与任务管理技术研究

“忠诚僚机”式作战概念定义了有人机与无人机协同作战的新理念，颠覆了传统作战模式。在有人/ 无人机协同作战过程中，有人机以指挥者的角色，对作战任务进行分解、分配与管理。实现有人/ 无人机编队 之间在时间、空间上的协同与配合，而无人机在有人机的指挥下完成侦察与打击等任务。     

面向全月球探测的天基中继测控系统设计

中继测控是月球探测任务中必须解决的关键问题，特别是月球背面和两极地区的着陆和巡视探测任务以及载人登月任务。本文首先对国内外月球中继测控卫星的研究和发展情况进行了调研，分析了未来全月球探测对中继测控的需求。在此基础上，重点给出了面向全月球探测任务的天基中继测控系统设计方案，并仿真分析了该方案的中继测控性能。最后给出了简要的卫星设计方案。     

Investigation on surface integrity of electron beam melted Ti-6Al-4 V by precision grinding and electropolishing

Electron beam melting (EBM), as an excellent Additive Manufacturing (AM) technology, enables the printing of Ti-6Al-4 V alloy for a wide range of applications such as aerospace and biomechanical industries. It improves functionality and integrity of components and negates complexities in assembly processes. However, due to the poor surface and sub-surface integrity represented by the rough surface finish and low dimensional accuracy, achieving a favorable surface condition is quite challenging. Therefore, post processing becomes essential for these electron beam melted (EBM-ed) Ti-6Al-4 V alloys. Being the most common technique to improve such parts, milling of Ti-6Al-4 V alloy is very challenging and resulting tool wear issues, due to its unique material properties. Thus, this paper presents a comprehensive study on the surface integrity of EBM-ed Ti-6Al-4 V parts processed by precision grinding and electropolishing, aiming to qualitatively and quantitatively clarify the interrelation between process parameters and processed surface quality. The surface and subsurface characteristics such as profile accuracy, surface roughness, microstructure, defective layer and residual stress before and after post processing were compared and evaluated. The results show that by precision grinding, the profile accuracy was improved from over 300 µm PV to 7 µm PV, while surface roughness (R_a) was reduced from 30 µm to about 2 µm. The layer with partially melt particles was removed, but introduced a deformed subsurface layer with more residual stress. Then by applying electropolishing, the residual stress was released and the deformed layer was removed. In addition, R_a was further reduced to 0.65 µm. The research can serve as a reference for the integration of post machining processes with AM.     

嫦娥五号探测器多圈调相地月转移应急轨道设计与分析

针对嫦娥五号任务上升段末期火箭二级发动机可能出现的提前关机故障造成入轨半长轴偏差较大和中途修正速度增量超限问题,提出了多圈调相地月转移轨道应急控制策略.首先,分析了不同入轨半长轴偏差、中途修正时刻与中途修正速度增量消耗之间的关系;其次,针对半长轴偏差较大问题,基于微分改正算法与B平面参数,设计了解析窗口搜索与多圈调相地...     

磁等离子体推力器工作机理与应用前景研究

研究了发动机能量输入、工质电离、等离子体加速及能量转换过程及机理,同时分析了磁等离子体推力器在空间推进任务中的应用前景.研究表明磁等离子体推力器主要利用电磁力加速和磁喷管的能量转换作用来实现加速,这种方式在大功率条件下,能够获得大推力、高功率和较长工作时间,在大功率轨道航天器和深空任务中有广阔的应用前景.     

METHIS: Mercury thermal infrared spectrometer

The BepiColombo mission to Mercury is devoted to the thorough exploration of Mercury and its environment, with the aim to understand the processes of planetary formation and evolution in the hottest part of the protoplanetary nebula. This mission represents an unique opportunity for the European community to extend the understanding of the Solar Nebula evolution from its outer edge – ideally represented by comets – to its inner and warmer edge. Obviously this exploration asks for a detailed knowledge of the main constituents of the matter present in the different Solar System areas. Spectroscopy is a powerful tool to acquire this knowledge. We have participated with a large consortium of European researchers to the development of the Rosetta imaging spectrometer. We propose here to use our experience to develop a newly designed spectrometer to investigate the mineralogical composition of the Mercurial surface. Given the particular thermodynamical situation of the Mercurial surface, we have developed a concept that combines a medium IR low spectral resolution imager with a moderate spectral resolution NIR point spectrometer. The main goal of METHIS is to provide the mineralogical characterisation of the surface with sufficient spectral resolution in a scientifically diagnostic spectral range.     

滑转条件下月球车轮沉陷模型研究

 月球车在月面行驶时,为保证月球车的通过性能,应尽量避免沉陷。然而传统车辆沉陷量数学模型不适用于动态滑转条件下的月球车,为此对月球车行驶时车轮沉陷量的计算模型进行了研究。基于车辆地面力学理论,从模拟月壤力学参数和滑转率两个方面,在适合于刚性轮静态沉陷计算模型基础上建立了适用于滑转条件下月球车轮的沉陷计算模型。通过轮壤土槽试验,将试验测得的月球车轮沉陷量与模型计算得到的沉陷量进行比较,验证了修正模型的正确性。所研究的模型能够为滑转条件下月球车沉陷量的预测提供理论技术基础。     

基于动态气象预报数据的4D航迹预测

高精度4D航迹预测是新一代航迹空管自动化的技术基础以及空管科技领域亟需的核心问题,考虑气象环境因素的影响则能明显提高航空器航迹预测的精度.利用世界区域预报系统的数字格点数据,首先对高度层进行垂直插值以获取某一剖面的气象信息,采用二次拉格朗日插值确定航段上某一点的温度场和风场的预报值,进而讨论温度场和风场预报值对飞行的影响,修正航空器真空速及地速,利用递推仿真方式求解航空器4D航迹.