一种深度学习分割遥感影像道路的损失函数

传统的根据光谱特征或形态学算法来分割道路,存在精度低、阈值难确定等缺点,而深度学习中已有的方法并未考虑道路的特性,只是利用通用方法来分割道路.针对上述不足,提出了一种针对道路特有形态的深度学习损失函数——形态损失函数.首先使用连通性算法将预测结果划分为若干个相互分离的连通区域,分别计算这些区域的面积与外接圆面积的比值,...     

三维动态非结构重叠网格Navier-Stokes方程并行算法

 提出了一种三维动态非结构重叠网格Navier-Stokes(N-S)方程的并行计算方法。N-S方程的空间离散采用格点有限体积方法,时间离散采用隐式的双时间步长方法。应用一方程Spalart-Allmaras(S-A)模型来计算湍流黏性。并行计算采用动态的区域分裂方法,在每一物理时间步利用METIS网格分区系统对网格进行分区。为了实现各CPU之间的负载均衡,每块网格都按CPU个数进行分区并对活动节点和非活动节点进行了加权处理。最后,通过对外挂物投放无黏流动的数值模拟和内埋武器弹舱开启黏性流动的数值模拟,验证了该并行程序的准确性、高性能并行计算以及处理复杂几何外形的能力。     

乘波飞行器的优化设计和气动热计算研究

以高超声速技术为研究背景,开展高超声速乘波飞行器设计方法研究.在已有乘波构型生成方法基础上,采用相交楔锥生成多级压缩的乘波构形.并通过对乘波器的前缘进行钝化,进行了气动热特性数值研究.使乘波体在气动力层面上具有尖前缘,保持高升阻比特性,而在气动热层面上具有钝前缘,降低气动加热强度.结果表明,这为高超声速飞行器的气动防热设计开辟了新途径.     

初始环境温度对真空管道高速列车气动特性的影响

伴随着激波、膨胀波等波系的综合作用,真空管道高速列车诱发的气动热效应十分明显.初始环境直接关系到管内列车气动性能的好坏,研究环境初始温度对真空管道高速列车气动特性的影响对未来真空管道列车运输系统的研发具有重要意义.在建立含动边界的准二维非定常数值计算模型的基础上,通过分子动理论描述气流物性变化,利用SST?k-ω转捩模型预测层流-湍流的混合流动状态,结合动网格技术实现了管内列车的跨音速运动,研究了273.15?K、300?K、350?K、400?K的初始环境温度下列车的气动特性变化.结果表明,随着初始环境温度增大,整车阻力减小,尾流扰动区发展过程减缓而车前扰动区发展过程加快,整个流场扰动区长度变化不大;在不同初始环境温度下,尽管尾流伴随着涡流脱落,但其温度波动的主频很低,约为0.76?Hz,波动幅度不超过2?K.     

Fast calibration of between-receiver GPS/Galileo/BDS differential phase bias with millimeter accuracy based on short baseline mode

The differential code and phase biases induced by the receiver hardware (including receiver, antenna, firmware, etc.) of the Global Navigation Satellite System (GNSS) have significant effects on precise timing and ionosphere sensing, thus deserve careful treatment. In this contribution, we propose an approach to fast fix the single-difference ambiguity to finally obtain the unbiased estimates of between-receiver differential phase bias (BR-DPB) and between-receiver differential code-phase bias (BR-DCPB) based on the short baseline mode. The key to this method is that the error sources can be significantly eliminated due to the length of the baseline is very short. At the same time, the empirical constraints and random characteristics of BR-DPB/BR-DCPB were considered, which is conducive to the resolution of single-difference ambiguity. Several sets of GNSS data (GPS L1/L2, Galileo E1/E5b, and BDS B1/B3), recorded by the short baselines in an interval of 30 s and covered a broad range of receiver/antenna types (JAVA, SEPT, LEIC, and TRIM), were used to verify the effectiveness of the proposed method. The numerical tests show that the proposed method is capable of fast fixing the single-difference ambiguity successfully within a few epochs and then providing the unbiased estimates of BR-DPB and BR-DCPB in an epoch-by-epoch manner. Experiments show that the estimated BR-DPB is in millimeter accuracy, which is of great significance for the millimeter-accuracy phase time transfer and ionospheric delay estimation. Furthermore, the calibrated BR-DPB/BR-DCPB can be treated as the known products for long-distance precise timing and ionosphere sensing based on the inter-station single-difference model.     

NB-IoT模块与电信物联网开放平台的通信研究

中国电信物联网开放平台实现对各种NB-IoT设备数据的统一管理,同时向第三方应用系统开发接口,让各种应用能快速构建自己的物联网业务。本文构建物联网系统,终端利用DS18B20温度传感器采集环境温度,通过BC35-G模块以CoAP协议将温度传输至电信物联网开放平台。     

Comparison of RO tropopause height based on different tropopause determination methods

The tropopause is an important boundary in the Earth’s atmosphere, and has been the subject of close attention from atmosphere and climate researchers. To monitor the global tropopause using radio occultation (RO) data, there are two primary methods, one is the widely used temperature lapse rate method, and the other is the bending angle covariance transform method which is unique to RO data. We use FengYun3-C (FY3C) and Meteorological Operational Satellite Program (MetOp) RO data and European Centre for Medium-Range Weather Forecasts (ECMWF) operational analysis data to determine differences in RO tropopause height calculated by these two methods. We compute biases of the RO lapse rate tropopause height (LRTH) and the RO bending angle tropopause height (BATH) relative to the ECMWF LRTH. The dependences of the tropopause height biases on tropopause height (TPH) retrieval method, latitude, season and RO mission are investigated. The results indicate that BATH show a consistent 0.8–1.2 km positive bias over the tropics and high latitude regions compared with LRTH, however, over 25° to 40° latitude in both hemisphere, BATH results are less stable. Furthermore, the mean bias between BATH and LRTH displayed a different symmetrical characteristic from 2017.12 to 2018.2 (DJF) compared to 2018.6–2018.8 (JJA). However, except for some bias over Antarctica, the mean value of both LRTH and BATH show a similar tropopause variation, indicating the consistency of both methods.     

嫦娥五号探测器多舱段间接力式校时及误差控制方法

为优化嫦娥五号探测器操控,达到通过给任意具备测控链路的舱段校时即可实现多舱段组合体时间同步的目标,提出了一种接力式校时及误差控制方法。该方法通过相邻舱段间接力式时间传递实现舱段间时间自流动。设计了基于飞行模式的时间基准设备检索方法,通过统一的检索配置表使各设备能够根据飞行模式识别上级时间基准设备,实现了各舱段的自主校时。设计了总线控制器(Bus controller,BC)与远置单元(Remote terminal,RT)间的分布式时间传递误差控制方法,BC端修正时间信息发送时产生的误差,RT端控制时间信息接收时引入的误差,保证了整器时统精度。研究方法实现了多舱段复杂航天器的器内自组织时统,已在嫦娥五号探测器上得到应用并取得预期效果,可为后续航天器软件设计提供参考。     

Use of land＇s cooperative object to estimate UAV＇s pose for autonomous landing

The research of unmanned aerial vehicles＇（UAVs＇）autonomy navigation and landing guidance with computer vision has important signifcance.However,because of the image blurring,the position of the cooperative points cannot be obtained accurately,and the pose estimation algorithms based on the feature points have low precision.In this research,the pose estimation algorithm of UAV is proposed based on feature lines of the cooperative object for autonomous landing.This method uses the actual shape of the cooperative-target on ground and the principle of vanishing line.Roll angle is calculated from the vanishing line.Yaw angle is calculated from the location of the target in the image.Finally,the remaining extrinsic parameters are calculated by the coordinates transformation.Experimental results show that the pose estimation algorithm based on line feature has a higher precision and is more reliable than the pose estimation algorithm based on points feature.Moreover,the error of the algorithm we proposed is small enough when the UAV is near to the landing strip,and it can meet the basic requirements of UAV＇s autonomous landing.