Observations of the Martian Subsolar ENA Jet Oscillations

The Neutral Particle Detector (NPD) of the ASPERA-3 experiment (Analyser of Space Plasmas and Energetic Atoms) on board the Mars Express (MEX) spacecraft observed an intense flux of H ENAs (energetic neutral atoms) with average energy of about 1.5 keV emitted anisotropically from the subsolar region of Mars. The NPD detected the ENA jet near the bow shock at radial distances of about 1 R _M from the Martian surface as the spacecraft moved outbound, while the NPD continuously pointed towards the subsolar region. The jet intensity shows oscillative behavior. These intensity variations occur on two clearly distinguishable time scales. The majority of the identified events have an average oscillation period of about 50 sec. The second group consists of events with long-scale variations with a time scale of approximately 300 sec. The fast oscillations of the first group exhibit a periodic structure and are detected in every orbit, while the slow variations of the second group are identified in ∼40% of orbits. The intensity of the fast oscillations have a peak-to-valley ratio about 20 to 30% of the peak intensity. One of the possible mechanisms to explain fast oscillations is the formation of the low frequency ion waves at the subsolar region of Mars. Slow variations may be explained by either temporal variations in the ENA generation source or by a specific structure of the ENA generation source, in which hair-like ENA subjets can be present.     

债转股问题初探

债转股作为经济体制改革的一个重要探索，已经成为当今法学界和经济学界讨论的主题。作为一个新事物的出现，债转股必然会遇到一系列来自不同方向的阻碍，本文就这些困惑进行论述，阐明了债转股面临的主要问题，并提出相应的解决方案和建议。国民经济体制改革需要大胆的探索和创新，债转股就是一个很好的范例，尽管其实施过程中难免遇到一些难题，但必将取得骄人的成果。     

The Solar Wind Interaction With the Martian Ionosphere/Atmosphere

The interaction of the solar wind with the Martian exosphere and ionosphere leads to significant loss of atmosphere from the planet. Spacecraft data confirm that this is the case. However, the issue is how much is actually lost. Given that spacecraft coverage is sparse, simulation is one of the few ways for these estimates to be made. In this paper the evolution of our attempts to place bounds on this loss rate will be addressed. Using a hybrid particle code the loss rate with respect to solar EUV flux is addressed as well as a variety of numerical and chemical issues. The progress made has been of an evolutionary nature, with one approach tried and tested followed by another as the simulations are improved and better estimates are produced. The results to be reported suggest that the ion loss rates are high enough to explain the loss of water from Mars during earlier solar epochs.     

Modelling and design of wing tip devices at various flight conditions using a databased aerodynamic prediction tool

A design study of wing tip devices at high and low speeds is described. The basis of the design study is an equivalent drag approach containing both aerodynamic drag gain and structural weight penalty. A comprehensive parameter study is carried out using a rapid aerodynamic prediction tool named Lift and Drag Component Analysis (LIDCA). Adding to an available lifting-line method a databased module for airfoil data is employed that uses results of two-dimensional flow simulations by multidimensional interpolation. Detailed validation studies of the method at high lift and high speed have demonstrated good accuracy. RANS computations of the selected wing tip designs confirm the predicted benefits at cruise condition. The results of the most effective wing tip designs are analysed at both flight conditions. Finally, options for improving the performance at take-off are suggested.     

Observations of Vertical Reflections from the Topside Martian Ionosphere

The Martian ionosphere has for the first time been probed by a low frequency topside radio wave sounder experiment (MARSIS) (Gurnett et al., 2005). The density profiles in the Martian ionosphere have for the first time been observed for solar zenith angles less than 48 degrees. The sounder spectrograms typically have a single trace of echoes, which are controlled by reflections from the ionosphere in the direction of nadir. With the local density at the spacecraft derived from the sounder measurements and using the lamination technique the spectrograms are inverted to electron density profiles. The measurements yield electron density profiles from the sub-solar region to past the terminator. The maximum density varies in time with the solar rotation period, indicating control of the densities by solar ionizing radiation. Electron density increases associated with solar flares were observed. The maximum electron density varies with solar zenith angle as predicted by theory. The altitude profile of electron densities between the maximum density and about 170m altitude is well approximated by a classic Chapman layer. The neutral scale height is close to 10 to 13 km. At altitudes above 180 km the densities deviate from and are larger than inferred by the Chapman layer. At altitudes above the exobase the density decrease was approximated by an exponential function with scale heights between 24 and 65 km. The densities in the top side ionosphere above the exobase tends to be larger than the densities extrapolated from the Chapman layer fitted to the measurements at lower altitudes, implying more efficient upward diffusion above the collision dominated photo equilibrium region.     

汽车车身曲面激光自动测量技术研究

针对追求整体协调要求的车身曲面宏观形状测量问题，开发了相应的以激光技术，传感技术、伺服控制技术以及工程应用光学等为基础的自动测量，文章对自动测量的原理、测头随动准则，测头扫描规则以及测点坐标数据采集、传输和处理等内容，均作了较为详细的探讨。     

战斗机航迹可飞性过载检验算法

生成满足战斗机过载约束条件的三维航迹以及对航迹进行可飞性过载检验是战斗机航迹规划的重要内容。利用B样条曲线拟合战斗机航迹并计算航迹曲率,给出了航迹可飞性过载判断准则以及相应的保证措施,即降低速度与调整导航点。通过对某型战斗机按拟合航迹飞行的需用过载进行仿真并对航迹可飞性进行过载约束检验,有效地验证了调整导航点位置的两条可用原则:防撞优先与规避优先。该算法对于实现战斗机三维航迹规划生成以及航迹可飞性过载检验具有一定的实用价值。     

Modified gradiometer technique applied to Double Star (TC-1)

On TC-1 (Tan Ce 1), the equatorial spacecraft of the Double Star mission, a strong spin-synchronized magnetic interference from the solar panels was observed. In-flight correction techniques for spinning spacecraft that are based on minimizing spin tones in the spin-aligned component and in the magnitude of the ambient magnetic field are therefore not possible in this case. However, due to the fortunate situation that the spacecraft carries two flux-gate magnetometers on the same boom (at 0.5 m distance from each other), the spacecraft field effects could be removed from the spin-averaged data to achieve 0.2 nT relative accuracy, by using a gradiometer technique. Methodology and results are presented. The obtained accuracy allows the use of the data in multi-spacecraft studies together with the Cluster satellites.     

基于TOPSIS算法的数据中继任务动态优先级设置方法

针对中继卫星系统资源分配中的数据中继任务优先级设置问题开展研究,提出动态优先级评价方法,打破现有基于预设固化时段完成冲突消解的任务规划模式.综合考虑用户、需求,以及任务重要性等因素,建立任务优先级两级评价指标体系.其中,刚性优先级用于度量资源申请的必要性,柔性优先级用于维护资源分配的公平性,同时促进资源使用的合理性.详细列举了各项指标的量化模型,给出了柔性指标综合计算算法.在实验分析中,通过大量数据统计,测试了所提方法的可行性和有效性.     

整体叶盘叶片磨抛工艺参数优化

以整体叶盘作为加工对象,为提高其叶片表面加工质量,降低表面粗糙度,展开整体叶盘磨抛工艺参数(如砂带粒度、砂带线速度、进给速度)的优化.首先,进行整体叶盘数控磨抛试验,其次,应用信噪比优化磨抛工艺参数,最后,选最优工艺参数对整体叶盘进行磨抛试验,加工表面测量结果表明,整体叶盘表面粗糙度显著降低,满足叶盘表面加工质量要求.