What are the physical mechanisms of eruptions and CMEs?

CMEs are due to physical phenomena that drive both, eruptions and flares in active regions. Eruptions/CMEs must be driven from initially force-free current-carrying magnetic field. Twisted flux ropes, sigmoids, current lanes and pattern in photospheric current maps show a clear evidence of currents parallel to the magnetic field. Eruptions occur starting from equilibria which have reached some instability threshold. Revisiting several data sets of CME observations we identified different mechanisms leading to this unstable state from a force free field. Boundary motions related to magnetic flux emergence and shearing favor the increase of coronal currents leading to the large flares of November 2003. On the other hand, we demonstrated by numerical simulations that magnetic flux emergence is not a sufficient condition for eruptions. Filament eruptions are interpreted either by a torus instability for an event occurring during the minimum of solar activity either by the diffusion of the magnetic flux reducing the tension of the restraining arcade. We concluded that CME models (tether cutting, break out, loss of equilibrium models) are based on these basic mechanisms for the onset of CMEs.     

基于Gabor滤波器的航空图像居民区域提取

中低分辨率航空图像中居民区域的自动提取对地理信息系统更新和无人机导航具有重要作用.详细分析了Gabor滤波器参数对纹理提取的影响,提出了一种基于Gabor滤波器的居民区快速提取算法.算法包含4步:运用Gabor滤波器分析图像纹理,采用核密度估计生成居民区域置信图像,进而计算自适应阈值分割置信图得到候选区域,最后根据区域几何形状去除干扰得到居民区.算法平均运算时间为0.42s,实验结果表明了算法的高效性和准确性.     

太阳10.7 cm射电流量中期预报模型研究(Ⅱ)

太阳活动指数中期预报一直是空间环境业务预报的难点之一.本文在自回归方法模型的基础上,利用太阳活动区面积、位置等参数与10.7cm辐射流量之间的定量关系,根据活动区面积衰减规律,建立了一个基于活动区参数及演化规律的改进型太阳活动指数中期预报模型.通过对预报测试实例分析发现,在日面出现较大活动区导致F_(10.7)迅速增长并超过历史数据峰值的情况,在日面活动区消亡导致指数突然出现平静期的情况,新模型的预报准确性相比自回归模型有很大提高,预报的平均相对误差下降约5%～9%.由此可见,新模型在某些特定条件下提高了原有模型的精度.该研究为提高业务型太阳10.7cm射电流量中期预报模型的预报精度奠定了基础.     

Variation of ionospheric electron and ion temperatures during periods of minimum to maximum solar activity by the SROSS-C2 satellite over Indian low and equatorial latitudes

To study the variation of ionospheric electron and ion temperatures with solar activity the data of electron and ion temperatures were recorded with the help of Retarding Potential Analyzer payload aboard Indian SROSS-C2 satellite at an average altitude of ∼500 km. The main focuses of the paper is to see the diurnal, seasonal and latitudinal variations of electron and ion temperatures during periods of minimum to maximum solar activity. The ionospheric temperatures in the topside show strong variations with altitude, latitude, season and solar activity. In present study, the temperature variations with latitude, season and solar activity have been studied at an average altitude ∼500 km. The peak at sunrise has been observed during all seasons, in both electron and ion temperatures. Further, the ionospheric temperatures vary with latitude in day time. The latitudinal variation is more pronounced for low solar activity than for high solar activity.     

轴压载荷作用下全复合材料裙与壳体搭接区的结构分析

对轴压载荷作用下固体火箭发动机复合材料裙与壳体搭接区的受力变形情况及承载能力进行了有限元分析,应用板壳理论对搭接区进行了分析,证明有限元计算结果合理可信;对裙搭接长度在40~60 mm范围内进行了寻优计算。结果说明,搭接区裙外铺层是搭接区最薄弱的环节;影响搭接区承载能力的主要结构因素有裙尖厚度、裙外铺层厚度、直段橡胶长度;随裙搭接长度的增大,搭接区承载能力呈现先增大后减小的趋势,存在搭接区承载能力的极大值。该分析方法和结果可供搭接区分析设计参考。     

基于ICA和BP神经网络相结合的掌纹识别

提出了一种基于独立成分分析(ICA,Independent Comment Analysis)和多层前馈(BP,Back Propagation)神经网络相结合的方法对掌纹进行识别.首先采用一种新的方法检测角点,得到掌纹图像的不变特征点,根据这些点校正掌纹方向并得到掌纹的感兴趣区域.对该区域采用定点快速ICA算法(FastICA),得到掌纹特征子空间,然后构建BP神经网络,并采用训练样本得到的掌纹特征进行训练,得到合适的权值.对香港理工大学掌纹数据库进行测试,与主成分分析(PCA,Principal Components Analysis)提取特征的方法进行比较,取得了较高的识别率.      

体-翼干扰区热环境特性分析及预测

高速飞行器的体—翼干扰区热流精确预测对于飞行器生存能力与战术性能的提高具有重要的 意义,是高性能飞行器设计水平的一个重要标志。由于体—翼干扰区流场的复杂性,目前尚 无满足工程设计要求的热环境预测方法,在分析体—翼流场特性的基础上应用文献［1 ］的压力—热流关系式,提出体—翼干扰区的热流预测方法,即压力由N-S数值解给出,热 流应用压力—热流关系式得到,炮风洞的实验结果验证了本文预测方法的可 靠性 。
     

径向直叶片燃油汽心泵汽心形态数值模拟

为获得燃油汽心泵内气态区域的形成过程及形态的变化规律,基于renormalization group(RNG) k-ε双方程湍流模型与Schnerr-Sauer空化相变模型,对径向直叶片燃油汽心泵进行了整体三维建模与气液两相定常数值模拟,分析转速、进口节流活门开度、出口压力等因素对燃油汽心泵内气态区域的影响.结果表明:一定转速范围内气态区域随转速增加而扩大;转速不变时出口压力增加会使气态区域范围减小;气态区域扩张至极限位置即叶轮直径外,燃油汽心泵进入不稳定工况.RNG k-ε双方程湍流模型和与Schnerr-Sauer空化相变模型适用于燃油汽心泵汽心形态的数值模拟.      

Flight trajectory optimization of sun-tracking solar aircraft under the constraint of mission region

The optimal yawing angle of sun-tracking solar aircraft is tightly related to the solar azimuth angle, which results in a large arc flight path to dynamically track the sun position. However, the limited detection range of payload usually requires solar aircraft to loiter over areas of interest for persistent surveillance missions. The large arc sun-tracking flight may cause the target area on the ground to be outside the maximum coverage area of payload. The present study therefore develops an optimal flight control approach for planning the flight path of sun-tracking solar aircraft within a mission region. The proposed method enables sun-tracking solar aircraft to maintain the optimal yawing angle most of the time during daylight flight, except when the aircraft reverses its direction by turning flight. For a circular region with a mission radius of 50 km, the optimal flight trajectory and controls of an example Λ-shaped sun-tracking solar aircraft are investigated theoretically. Results demonstrate the effectiveness of the proposed approach to optimize the flight path of the sun-tracking aircraft under the given circular region while maximizing the battery input power. Furthermore, the effects of varying the mission radius on energy performance are explored numerically. It has been proved that both net energy and energy balance remain nearly constant as the radius constraint varies, which enables the solar aircraft to achieve perpetual flight at almost the same latitude as the large arc flight. The method and results presented in this paper can provide reference for the persistent operation of sun-tracking solar aircraft within specific mission areas.