为了解及评估山东省临沂地区土壤侵蚀现状,在地理信息系统(geographic information system,简称GIS)技术支持下,应用中国土壤侵蚀方程(Chinese soil loss equation,简称CSLE)模型,中分辨率成像光谱仪[moderate-resolution imaging spect...为了解及评估山东省临沂地区土壤侵蚀现状,在地理信息系统(geographic information system,简称GIS)技术支持下,应用中国土壤侵蚀方程(Chinese soil loss equation,简称CSLE)模型,中分辨率成像光谱仪[moderate-resolution imaging spectroradiometer,简称MODIS(250 m)]与航天飞机雷达地形测绘[shuttle radar topography mission,简称SRTM(90 m)]影像,测量研究区10个气象站点降水量数据及土壤类型图等数据,结合临沂地区特征,定量估算了研究区土壤侵蚀量。结果表明:(1)研究区土壤的微度侵蚀占总面积的80.83%,轻度侵蚀占15.62%;(2)在地形起伏较大的山区、丘陵地带存在非常明显的中、强度侵蚀,土壤侵蚀较为严重的地区主要分布在山区周围,平原地区侵蚀强度较轻;(3)山区周围的侵蚀以山脚为主,越往上的区域,侵蚀程度越低。展开更多
针对二进制描述算法(Oriented fast and Rotated Brief,ORB)尺度性配准误差大,配准率低的问题,提出一种尺度和方向改进的ORB特征匹配算法。该算法以二进制描述算法ORB为基础,构建金字塔式尺度空间,改进尺度空间结构,简化尺度空间层数和...针对二进制描述算法(Oriented fast and Rotated Brief,ORB)尺度性配准误差大,配准率低的问题,提出一种尺度和方向改进的ORB特征匹配算法。该算法以二进制描述算法ORB为基础,构建金字塔式尺度空间,改进尺度空间结构,简化尺度空间层数和采样图像数目,使提取特征点的过程更加效率,并采用Harris函数检测特征,消除边缘特征点的影响,提取具有尺度信息的特征点;然后采用梯度方向统计方法改进传统ORB算法中通过灰度质心法计算主方向的方式,优化求解主方向邻域范围,以提高图像特征主方向的准确性。实验结果表明,改进后的ORB算法在尺度和旋转配准方面性能有很大提高,并且配准的精度较传统ORB更高,更能满足复杂图像快速精确配准的要求。展开更多
磁等离子体动力学推力器是空间高功率电推进装置的典型代表,磁等离子体动力学过程是其核心工作机制.为深入理解外磁场对其工作特性的影响,本文采用粒子云(particle in cell,PIC)方法结合基于自相似准则的缩比模型,进行外加磁场作用下磁...磁等离子体动力学推力器是空间高功率电推进装置的典型代表,磁等离子体动力学过程是其核心工作机制.为深入理解外磁场对其工作特性的影响,本文采用粒子云(particle in cell,PIC)方法结合基于自相似准则的缩比模型,进行外加磁场作用下磁等离子体动力学推力器工作过程的建模仿真,通过与实验结果对比验证模型和方法的可靠性,并重点分析推力器点火启动过程的等离子特性参数分布,以及外磁场和阴极电流对推力器工作性能的影响.研究结果表明:阴阳极放电电弧构建是推力器启动和高效工作的关键步骤;外磁场强度较低工况不利于构建稳定放电电弧,等离子体束流集中于轴线附近,推力主要产生机制是自身场加速;外磁场强度较高时,阴阳极放电电弧稳定,推力产生主要机制是涡旋加速,推力、比冲随外磁场强度线性增大;推力器效率随阴极电流和外磁场强度增大而增大;放电电压随阴极电流增大而增大,但随外磁场强度的增大表现出先减小后增大的趋势.展开更多
The electrospray thruster is becoming popular in space propulsion due to its low power and high specific impulse.Before this work,an electrospray thruster based on a porous emitter was developed.In order to achieve la...The electrospray thruster is becoming popular in space propulsion due to its low power and high specific impulse.Before this work,an electrospray thruster based on a porous emitter was developed.In order to achieve larger and more stable thrust,the thruster was redesigned,and the influence of the space between strips on thrust was studied.Four types of emitter were tested,and they had 1,3,4 and 14 emitter-strips on the emission surface of the same size respectively.According to the experimental results,the maximum extraction voltage and emission current of the four thrusters are different under stable operational conditions.The measured stable emission currents and extraction voltages were-500μA/-5000 V,-1570μA/-3800 V,-1200μA/-3800 V,and-650μA/-4500 V,respectively.Increasing the number of strips may not result in the emission current increasing,but changing the stable operational range of the emission current per strip and the extraction voltage.The maximum stable operational extraction voltages of 3 and 4 emitter-strips are lower than those of 1 and 14 emitter-strips,but the emission currents are higher than those of 1 and 14 emitter-strips.Time-of-flight mass spectrometry was used to analyze the mass distribution and obtain the performance of the thruster in the case of thrusters with 1 and 3 emitter-strips.Both of their plumes were composed of very small ion cluster(the pure-ion regime),and their thrusts were 80.1μN,219.2μN with specific impulses of 5774 s,5047 s,respectively.展开更多
文摘针对二进制描述算法(Oriented fast and Rotated Brief,ORB)尺度性配准误差大,配准率低的问题,提出一种尺度和方向改进的ORB特征匹配算法。该算法以二进制描述算法ORB为基础,构建金字塔式尺度空间,改进尺度空间结构,简化尺度空间层数和采样图像数目,使提取特征点的过程更加效率,并采用Harris函数检测特征,消除边缘特征点的影响,提取具有尺度信息的特征点;然后采用梯度方向统计方法改进传统ORB算法中通过灰度质心法计算主方向的方式,优化求解主方向邻域范围,以提高图像特征主方向的准确性。实验结果表明,改进后的ORB算法在尺度和旋转配准方面性能有很大提高,并且配准的精度较传统ORB更高,更能满足复杂图像快速精确配准的要求。
文摘磁等离子体动力学推力器是空间高功率电推进装置的典型代表,磁等离子体动力学过程是其核心工作机制.为深入理解外磁场对其工作特性的影响,本文采用粒子云(particle in cell,PIC)方法结合基于自相似准则的缩比模型,进行外加磁场作用下磁等离子体动力学推力器工作过程的建模仿真,通过与实验结果对比验证模型和方法的可靠性,并重点分析推力器点火启动过程的等离子特性参数分布,以及外磁场和阴极电流对推力器工作性能的影响.研究结果表明:阴阳极放电电弧构建是推力器启动和高效工作的关键步骤;外磁场强度较低工况不利于构建稳定放电电弧,等离子体束流集中于轴线附近,推力主要产生机制是自身场加速;外磁场强度较高时,阴阳极放电电弧稳定,推力产生主要机制是涡旋加速,推力、比冲随外磁场强度线性增大;推力器效率随阴极电流和外磁场强度增大而增大;放电电压随阴极电流增大而增大,但随外磁场强度的增大表现出先减小后增大的趋势.
文摘The electrospray thruster is becoming popular in space propulsion due to its low power and high specific impulse.Before this work,an electrospray thruster based on a porous emitter was developed.In order to achieve larger and more stable thrust,the thruster was redesigned,and the influence of the space between strips on thrust was studied.Four types of emitter were tested,and they had 1,3,4 and 14 emitter-strips on the emission surface of the same size respectively.According to the experimental results,the maximum extraction voltage and emission current of the four thrusters are different under stable operational conditions.The measured stable emission currents and extraction voltages were-500μA/-5000 V,-1570μA/-3800 V,-1200μA/-3800 V,and-650μA/-4500 V,respectively.Increasing the number of strips may not result in the emission current increasing,but changing the stable operational range of the emission current per strip and the extraction voltage.The maximum stable operational extraction voltages of 3 and 4 emitter-strips are lower than those of 1 and 14 emitter-strips,but the emission currents are higher than those of 1 and 14 emitter-strips.Time-of-flight mass spectrometry was used to analyze the mass distribution and obtain the performance of the thruster in the case of thrusters with 1 and 3 emitter-strips.Both of their plumes were composed of very small ion cluster(the pure-ion regime),and their thrusts were 80.1μN,219.2μN with specific impulses of 5774 s,5047 s,respectively.
