水下PNT体系之声学导航定位技术应用展望CSCD

声学导航技术是水下PNT体系的重要组成部分,也是水下PNT建设的一种有效增量手段,应充分利用中高频声学导航技术的隐蔽性和精确性,以及低频声学导航技术的广域性,满足水下用户对水下导航定位能力的隐蔽性、广域性以及精确性需求,有效促进水下导航定位服务能力的持续提升。从水下应用需求出发,研究了声学导航的任务剖面、边界条件和融合方式等,明确其在水下应用的优越性与局限性,最后对我国未来声学导航技术水下应用提出了建议。     

极区夏季中间层半日潮汐的VHF雷达观测

采用德国SOUSYVHF雷达观测数据,研究了极区夏季中间层半日潮汐的结构和变化特征.纬向和经向风的动态Lomb-Scargle谱表明,半日潮是中间层高度上占支配地位的波动,其谱峰对应的频率一般与1/12c·h-1有偏离,说明它们经常处在被扰动状态.稳定的半日潮振幅随高度增加而迅速增长,在87.9km高度附近达到饱和;经向分量的相位一般比纬向分量的相位超前π/4-π/2,从而水平扰动速度矢量端点随时间变化的轨迹显示出顺时针方向旋转的特征.半日潮汐特征参量在纬向和经向风中随时间的变化在基本趋势一致的基础上显示出一定程度的各向异性.      

自动倒码式力标准机技术及其应用

静重式力标准机是最重要的力值计量、传递仪器之一。采用倒换砝码的加载方法,只需少量的砝码,可以实现大范围测量应用,并减小设备体积。理论上,一台较大规格的自动倒码式力标准机可以替代其容量以下所有规格的设备。分析了加载过程中砝码倒换的力学原理,论述了所研制的自动倒码式力标准机的工作原理及其自动监控问题,并进行了应用实验。结果表明,关于砝码倒换的力学原理的理论分析和力标准机的监控方法是正确和有效的。自动倒码式力标准机非常适合于包括宇航推力计量器具在内的各种测力仪的标定和校准。     

Integrated supersonic wind tunnel nozzle

In supersonic wind tunnels, the airflow at the exit of a convergent-divergent nozzle is affected by the connection between the nozzle and test section, because the connection is a source of disturbance for supersonic flow and the source of disturbance generated by this disturbance propagates downstream. In order to avoid the disturbance, the test can only be carried out in the rhombus area. However, for the supersonic nozzle, the rhombus region is small, limiting the size and attitude angle of the test model. An integrated supersonic nozzle is a nozzle and a test section as a whole, which is designed to weaken or eliminate the disturbance. The inviscid contour of the supersonic nozzle is based on the method of characteristics. A new curve is formed by the smooth connection between the inviscid contour and test section, and the boundary layer is corrected for the overall curve. Integrated supersonic nozzles with Mach number 1.5 and 2 are designed, which are based on this method. The flow field is validated by numerical and experimental results. The results of the study highlight the importance of the connection about the nozzle outlet and test section. They clearly show that the wave system does not exist at the exit of the supersonic nozzle, and the flow field is uniform throughout the test section.     

冲压发动机控制路径研究

冲压发动机的性能高低很大程度上取决于它的控制品质.控制系统通过设置各种极限函数确保冲压发动机在外部干扰和内部扰动下可靠稳定工作,并结合任务特点采用不同的控制策略进行合理的调节,充分发挥出冲压发动机的性能.本文研究了3种不同控制参数下冲压发动机的稳定工作范围.针对不同的飞行任务的要求,研究了常用的控制策略下冲压发动机的控制路径.     

Ionospheric disturbance associated with radiation accidents of Fukushima I nuclear power plant damaged by the M9.0 2011 Tohoku Earthquake

Transient ionospheric disturbances in the total electron content (TEC) are examined before and after the M9.0 2011 off the Pacific coast of Tohoku Earthquake to find ionospheric responses to the radiation caused by Fukushima I nuclear power plant accident, which was damaged by the earthquake and tsunamis. The TEC is derived from records of a ground-based receiving network of GPS Earth Observation Network (GEONET) in Japan. Both small enhancement and disturbance of TEC were detected over the nuclear power plant after the radiation was suddenly enhanced on March 14 of 2011, while similar signatures were not detected in the other sudden radiation enhancements. Further, no continuous enhancement and disturbance lasting for more than an hour were observed over the nuclear power plant. Therefore, the results indicate that radioactive materials may not cause the ionospheric disturbance or disturb the ionosphere in highly specific circumstance even if such effects exist.     

《儒林外史》及其英译本人称照应衔接手段对比

人称照应衔接手段存在于英汉两种语言中。基于韩礼德的衔接理论,以《儒林外史》及其英译本为例,对比英汉语中人称照应衔接手段的异同,并从意合与形合,螺旋型与直线型及语法化程度对差异进行解释。     

论市场比较法－－《房地产估价规范》系列研究之一

市场比较法是房地产估价的主要方法，本文综述了市场比较法的因素指标体系，提出因素指标修正必须考虑权重的论点，简述了权重的测定方法，总结估价教学实务，对市场比较法的理论与实务进行了探讨。     

径向全跳动误差的理论研究

叙述了直角坐标采样时 ,径向全跳动误差的最小二乘评定法数学模型 ,并用计算机进行仿真研究。结果表明 ,所建立的数学模型具有编程简单 ,计算准确度较高等特点。所建立的数学模型为研制形位误差虚拟测量系统提供了理论基础     

High-temperature gas effects on aerodynamic characteristics of waverider

This paper focuses on the analysis of high-temperature effect on a conical waverider and it is a typical configuration of near space vehicles. Two different gas models are used in the numerical simulations, namely the thermochemical non-equilibrium and perfect gas models. The non-equilibrium flow simulations are conducted with the usage of the parallel non-equilibrium program developed by the authors while the perfect gas flow simulations are carried out with the commercial software Fluent. The non-equilibrium code is validated with experimental results and grid sensitivity analysis is performed as well. Then, numerical simulations of the flow around the conical waverider with the two gas models are conducted. In the results, differences in the flow structures as well as aerodynamic performances of the conical waverider are compared. It is found that the thermochemical non-equilibrium effect is significant mainly near the windward boundary layer at the tail of the waverider, and the non-equilibrium influence makes the pressure center move forward to about 0.57% of the whole craft’s length at the altitude of 60 km.