用双色激光多卜勒风速仪研究燃烧室的复杂流场

 本文总结了双色激光多卜勒风速仪系统在航空发动机蒸发管式模型燃烧室流场测量中取得的一些结果及应用经验。并与用常规方法测得的结果作了比较。     

月球卫星的精密定轨

发射月球卫星是探测月球的一个重要途径,而且为了找水,多采用极轨方式.由于作为中心天体的月球与地球有所不同,导致月球卫星的运动及其相应的轨道摄动解亦有明显差异.在这种背景下,本文选择采用一组适用于0≤e<1和0°≤i<180°的无奇点根数、充分利用数值法和分析法各自特点的定轨方法,给出月球卫星的精密定轨方案,并以测距的模拟资料进行了实算,计算结果与理论分析相符,有实用前景.     

Evolution of coronal mass ejections in the early stage

This work reports the investigation of two coronal mass ejections (CME) observed in white light, H, EUV and X-ray by various instruments both in space and on ground on February 18, 2003 and January 19, 2005, respectively. The white light coronal images show that the first CME began with the rarefaction of a region above the solar limb and was followed by the formation of its leading edge at the boundary of the rarefying region at altitude of 0.46 R from the solar surface. The rarefaction coincided the slow rising phase of the filament eruption, and the CME leading edge was observed to form as the filament eruption started to accelerate apparently. In the early stage of the second CME, a bright loop was first observed above the solar limb with height of 0.37 R in EUV images. We found that the more gradual CMEs initial process, the larger the timing difference between CMEs and their associated flares. The lower part of the filament brightened in H images as the filament rose to a certain height. These brightenings imply that the filament may be heated by magnetic reconnection below the filament in the early stage of the eruption. We suggest that the possible mechanism which led to the formation of the CME leading edge and cavity is magnetic reconnection which occurred under the filament when it reached a certain height.     

动态测量不确定度A类评定

综述动态测量误差与不确定度评定的基本特点、一般评定指标与评定方法。着重概述对动态测量数据作统计分析的不确定度Ａ类评定方法。列举各种常用动态测量数据处理方案及其基本假定条件和测量误差分离原理及测量不确定度Ａ类评定的基本算法。     

面向综合环境监测的星载SAR技术发展

针对中国微波遥感对地观测在信息维度、反演精度、观测效率和体系架构等方面存在的问题,基于国家重点研发计划“星载新体制SAR综合环境监测技术”的研究内容与成果,探讨了面向综合环境监测的若干未来星载SAR技术发展。在超大幅宽成像方面,提出分段渐变重频时序设计方案和基于最优线性无偏估计的低过采样变重频数据处理算法,实现了跨盲区大幅宽星载SAR成像;在宽幅星载SAR高灵敏度成像方面,提出中频数字波束合成高效星上实时处理架构和加权因子快速生成算法,采用16通道机载飞行试验数据验证,图像信噪比提升约112dB;在多极化星载SAR成像方面,分别提出一种简缩极化分解算法及混合全极化方位模糊抑制方法,在P/L波段机载飞行试验中得到验证;在高精度干涉SAR技术方面,提出基于改进相位补偿方案的层析SAR处理方法,利用P波段全极化层析SAR数据验证,获得优于0.9m的森林高度反演精度;在综合环境监测星座架构设计方面,针对广域地表高程、地表形变、海浪谱能量、洋流速度和生物量应用,完成品质因数达100的高分宽幅SAR卫星方案,其观测效能和观测维度较目前在轨SAR卫星有大幅提升。     

基于点集合并的修正Hough变换TBD算法

在低信噪比条件下,基于Hough变换的检测前跟踪算法是进行强杂波背景下目标航迹检测的一种手段。本文针对Hough变换后一个目标产生多条可能航迹以及航迹内可能存在杂波点的问题,提出了一种基于能量最大点和点集合并的修正Hough变换检测前跟踪算法。该算法利用量测点时序、能量信息及目标速度先验信息对Hough变换后点迹进行关联和剔除,能够有效的对目标原始航迹进行回溯。针对高斯噪声背景下的飞行目标,仿真结果表明该算法能够对微弱目标进行有效检测,在目标数目、杂波密度、信噪比发生变化的条件下仍能保持较高的检测概率。     

基于光度曲线的弱特征空间目标姿态估计

针对暗弱空间光度曲线波动不明显的弱特征目标姿态难以估计的问题，本文基于不同观测站所得到的目标光度曲线具有差异的特点提出以空间换取精度的设想，并据此设计了多站联合光度观测并行融合的解决方案。通过分析站点位置以及站点数量对弱特征空间目标姿态估计的影响，验证了该解决方案的可行性与有效性，发现了站点的布置有规律可循。仿真表明，站点之间距离的增加以及站点数量的增加都可以减小姿态估计误差，而通过沿空间目标对太阳光线反射的相对方向布置站点可以得到更好的姿态估计结果。     

Design and analysis of a direct transfer trajectory from a near rectilinear halo orbit to a low lunar orbit

A near rectilinear halo orbit (NRHO) is regarded as a potential orbit for a future deep space station that can effectively support sustainable crewed lunar exploration missions. In this paper, the L₂ southern NRHOs are selected as the research object, and a direct transfer trajectory from an NRHO to a low lunar orbit (LLO) is designed and analyzed. First, based on the circular restricted three-body problem, the characteristics of NRHOs are discussed including geometric behaviour, stability and synodic resonance. Second, optimal direct transfer trajectories are obtained by combining a local gradient optimization with a numerical continuation strategy. A reachable domain calculation model is established. Finally, simulations are carried out to verify the feasibility of the trajectory design method. The relationship between the velocity change and the reachable domain is further analysed through simulation calculations.     

Experimental study on ceramic membrane technology for onboard oxygen generation

The ceramic membrane oxygen generation technology has advantages of high concentra-tion of produced oxygen and potential nuclear and biochemical protection capability. The present paper studies the ceramic membrane technology for onboard oxygen generation. Comparisons are made to have knowledge of the effects of two kinds of ceramic membrane separation technologies on oxygen generation, namely electricity driven ceramic membrane separation oxygen generation technology (EDCMSOGT) and pressure driven ceramic membrane separation oxygen generation technology (PDCMSOGT). Experiments were conducted under different temperatures, pressures of feed air and produced oxygen flow rates. On the basis of these experiments, the flow rate of feed air, electric power provided, oxygen recovery rate and concentration of produced oxygen are compared under each working condition. It is concluded that the EDCMSOGT is the oxygen generation means more suitable for onboard conditions.     

面向签派的飞行燃油消耗估计方法

航班的燃油加载量决定了航空公司运行成本。本文提出了基于飞机性能的燃油消耗估计模型及其动态修正方法。以飞机性能手册参数为依据,根据各飞行阶段的性能特点,建立基于神经网络的燃油消耗原始模型。利用积累的飞行数据(QAR数据)修正模型,消除因飞机性能衰减对燃油消耗的影响,弥补飞机性能手册中飞行气象条件样本量较少的不足。以某次北京—成都航班飞行计划数据为验证数据源,按照签派流程进行了模型的验证测试,对比本次航班实际燃油消耗量,误差为2.38%,达到现阶段国内外航空公司现有商业软件估计精度水平。