1997-2003年太阳质子事件源区的卡林顿经度分布

分析了1997-2003年期间的59个太阳质子事件,太阳质子事件源区的卡林顿经度带.分析结果表明,质子事件源区主要集中在10°-45°,135°-155°,180°-215°,230°-260°,265°-310°,345°-360°,还有4个质子耀斑分散在72°,74°,93°和107°上.其中最强的活动卡林顿经度带的经度范围是265°-310°,次之为卡林顿经度带135°-155°,最弱的是卡林顿经度带180°-215°最强的活动经度是卡林顿经度272°.1997-2003年期间峰值通量大于100 pfu,质子耀斑南半球发生次数为18,北半球发生次数为10;同一活动经度上的质子事件具有重现的规律,重复出现的时间间隔短的为27天,长的超过4年.     

China’s Space Astronomy and Solar Physics in 2011-2012

In the first part of this paper, we describe briefly the mid and long-term plan of Chinese space astronomy, its preliminary study program, the current status of satellite missions undertaken, and the current status of astronomy experiments in China’s manned space flight program. In the second part, the recent research progress made in the fields of solar physics is summarized briefly, including solar vector magnetic field, solar flares, CME and filaments, solar radio and nonthermal processes, EUV waves, MHD waves and coronal waves, solar model and helioseismology, solar wind and behavior of solar cycle.     

F2 layer characteristics and electrojet strength over an equatorial station

The data presented in this work describes the diurnal and seasonal variation in hmF2, NmF2, and the electrojet current strength over an African equatorial station during a period of low solar activity. The F2 region horizontal magnetic element H revealed that the Solar quiet Sq(H) daily variation rises from early morning period to maximum around local noon and falls to lower values towards evening. The F2 ionospheric current responsible for the magnetic field variations is inferred to build up at the early morning hours, attaining maximum strength around 1200 LT. The Sq variation across the entire months was higher during the daytime than nighttime. This is ascribed to the variability of the ionospheric parameters like conductivity and winds structure in this region. Seasonal daytime electrojet (EEJ) current strength for June solstice, March and September equinoxes, respectively had peak values ranging within 27–35 nT (at 1400 LT) , 30–40 nT (at 1200 LT) and 35–45 nT (at 1500 LT). The different peak periods of the EEJ strength were attributed to the combined effects of the peak electron density and electric field. Lastly, the EEJ strength was observed to be higher during the equinoxes than the solstice period.     

Improving DORIS geocenter time series using an empirical rescaling of solar radiation pressure models

Even if Satellite Laser Ranging (SLR) remains the fundamental technique for geocenter monitoring, DORIS can also determine this geophysical parameter. Gobinddass et al. (2009) found that part of the systematic errors at 118 days and 1 year can be significantly reduced by rescaling the current solar radiation pressure models using satellite-dependent empirical models. Here we extend this study to all DORIS satellites and propose a complete set of empirical solar radiation parameter coefficients. A specific problem related to SPOT-5 solar panel realignment is also detected and explained. New DORIS geocenter solutions now show a much better agreement in amplitude with independent SLR solutions and with recent geophysical models. Finally, the impact of this refined DORIS data strategy is discussed in terms of Z-geocenter monitoring as well as for other geodetic products (altitude of high latitude station such as Thule in Greenland) and Precise Orbit Determination. After reprocessing the full 1993.0-2008.0 DORIS data set, we confirm that the proposed strategy allows a significant reduction of systematic errors at periods of 118 days and 1 year (up to 20 mm), especially for the most recent data after 2002.5, when more DORIS satellites are available for geodetic purposes.     

太阳系边际探测飞行任务规划

针对太阳系边际探测任务,开展了星际多目标飞越的任务规划,采用小推力混合优化设计方法完成了基于借力飞行及电推进技术的行星际转移轨道联合优化设计,对比研究了面向日球层鼻尖和尾部探测的星际多目标探测飞行方案。研究表明,探测器在2024-2025年发射,可飞抵日球层鼻尖区域,在2027-2030年发射可飞抵日球层尾部区域,并可在2049年1月1日前飞离日心100 AU,实现太阳系边际空间的科学探测。其中日球层鼻尖探测任务探测器飞抵100 AU的位置位于鼻尖中心区域,可与旅行者1号、2号探测器形成有效互补。文章所用任务规划方法,可为太阳系边际探测的自主任务规划技术提供基础,相关研究成果能够为未来中国首次太阳系边际探测任务的实施提供有价值的参考。     

光压摄动对卫星姿态轨道耦合的影响分析

随着卫星对地测量精度要求的不断提高, 对卫星轨道的精度要求也随之提高. 目前Topex, Jason-1, Jason-2等一系列海洋测地卫星的轨道计算精度已经达到厘米量级, 相应对卫星动力学模型的要求也越来越精细. 以Topex海洋测地卫星为背景, 考虑卫星帆板有规律的运动, 将其几何形状简化为高精度轨道计算中比较通用的Boxing-Wing模型, 计算了Topex卫星的Boxing-Wing模型在轨运行中受到的太阳光压力及光压力矩. 考虑卫星姿态和轨道耦合的情况下, 计算了太阳光压力及光压力矩对Topex卫星轨道半长轴和卫星姿态的影响. 通过一个轨道周期的计算可知, 光压对卫星轨道半长轴的影响大约为9cm, 对卫星滚动角和俯仰角的影响在6°左右, 因此, 在高精度的轨道计算和姿态控制中这个影响是应该考虑的.     

FT300水陆两用型三座轻型飞机双浮筒配置的探讨

简要介绍了ＦＴ３００水陆两用三座轻型飞机型号设计过程中水动方面的研究与分析，重点对三座轻型飞机筒线性选择、双浮筒相对鸭式飞机安装位置的配置以及轻型水上飞机的主要水动力特性的理论分析作了研究，建立了鸭式布局飞机重心相对浮筒断阶位置的新值。