Anomalous enhancement of electric field derived from ionosonde data before the great Wenchuan earthquake

The seismo-ionospheric coupling is a hot topic of modern scientific research. One of the most reasonable mechanisms is the hypothesis of quasistatic electric field. With a preliminary analytical method, electric field in F2-region before Wenchuan earthquake was derived from the five lower latitude ground-based ionosondes: Lhasa (29.63°N, 91.17°E), Chongqing (29.50°N, 106.40°E), Kunming (25.00°N, 102.70°E), Guangzhou (23.15°N, 113.35°E) and Haikou (23.15°N, 110.35°E). The results show that there was an anomalous enhancement of electric field in F2-region close to the epicenter with maximal amplitude ∼2 mV/m (about 10 times of the background) at 15:00 LT on 9 May, which is in line with the amplitudes of anomalous electric field related to some previous earthquakes observed by satellites.     

NOVEL HIGH-SPEED FPGA-BASED FFT PROCESSOR

A novel architecture for computing the fast Fourier transform ( FFT ) on programmable devices is presented.To improve the system operation speed , a hybrid parallel FFT algorithm is used.Results indicate that the use of an 8×8parallel structure for realizing the 64-point FFT leads to a 8times higher processing speed compared with its counterparts employing other series of techniques.     

Effects of sector structure of the interplanetary magnetic field on the upper mesosphere–lower thermosphere dynamics

In this paper we study the influence of the interplanetary magnetic field (IMF) polarity changes caused by the Earth passing through the IMF sector boundary on the dynamic processes taking place in neutral atmosphere within the altitude interval of the upper mesosphere–lower thermosphere (83–101 km). The analysis has revealed the influence of the IMF sector structure on dynamics of the upper mesosphere–lower thermosphere. There has been a significant seasonal variation of the wind reaction to the IMF polarity changes observed. The influence of the IMF polarity changes on neutral atmosphere dynamics within the altitude range of 83–101 km is most pronounced in the zonal component of neural wind when the IMF polarity changes from negative to positive in all the seasons except for spring and when IMF polarity changes from positive to negative – in spring only.     

（20～400）MeV准单能中子参考辐射场的建立方法CSCD

为了满足对高能中子辐射场测量仪器进行校准的需要,必需建立20MeV以上的准单能中子参考辐射场.对国际上（20～400） MeV准单能中子参考辐射场的建立情况及建立方法进行了调研,可通过7Li（p,n）7Be反应获得该能区准单能中子场,中子束流轮廓可通过转换体和影像板进行测量,辐射场中子能谱可利用液体闪烁探测器或者238U裂变电离室通过飞行时间法进行测量,可建立高效率的反冲质子望远镜作为该能区的中子注量测量初级标准.     

液冷模块的热仿真分析

运用基于CFD的热仿真软件Flotherm对液冷模块进行了热仿真分析,分别研究了在不同环境温度,不同冷却液流量以及不同冷却液温度条件下,液冷模块内部温度场的变化规律。仿真分析结果表明,环境温度对液冷模块的温度场影响非常小;液冷模块冷却液流量的增幅与元器件温度的降幅并非正比关系;元器件温度的升幅与冷却液温度的增幅相同。     

AIUB-CHAMP02S: The influence of GNSS model changes on gravity field recovery using spaceborne GPS

The gravity field model AIUB-CHAMP02S, which is based on six years of CHAMP GPS data, is presented here. The gravity field parameters were derived using a two step procedure: In a first step a kinematic trajectory of a low Earth orbiting (LEO) satellite is computed using the GPS data from the on-board receiver. In this step the orbits and clock corrections of the GPS satellites as well as the Earth rotation parameters (ERPs) are introduced as known. In the second step this kinematic orbit is represented by a gravitational force model and orbit parameters.     

航电系统外场保障实习台的设计与研究

根据航电系统在外场通电时对操作人员的技能要求和相关设备需求,提出了研制航电系统外场保障实习台的思路和方案;构建了实习台的半实物仿真模型,设计了基于模拟操作功能的硬件电路,编制了基于虚拟仪器技术的软件流程,完成了实习台的系统集成与调试,实现了航电系统外场通电保障的模拟训练;应用结果表明,实习台功能强,可扩展性好,使用广泛,军事经济效益显著。     

Dependence of the 27-day variation of cosmic rays on the global magnetic field of the Sun

We show that the higher range of the heliolongitudinal asymmetry of the solar wind speed in the positive polarity period (A > 0) than in the negative polarity period (A < 0) is one of the important reasons of the larger amplitudes of the 27-day variation of the galactic cosmic ray (GCR) intensity in the period of 1995–1997 (A > 0) than in 1985–1987 (A < 0). Subsequently, different ranges of the heliolongitudinal asymmetry of the solar wind speed jointly with equally important corresponding drift effect are general causes of the polarity dependence of the amplitudes of the 27-day variation of the GCR intensity. At the same time, we show that the polarity dependence is feeble for the last unusual minimum epoch of solar activity 2007–2009 (A < 0); the amplitude of the 27-day variation of the GCR intensity shows only a tendency of the polarity dependence. We present a three dimensional (3-D) model of the 27-day variation of GCR based on the Parker’s transport equation. In the 3-D model is implemented a longitudinal variation of the solar wind speed reproducing in situ measurements and corresponding divergence-free interplanetary magnetic field (IMF) derived from the Maxwell’s equations. We show that results of the proposed 3-D modeling of the 27-day variation of GCR intensity for different polarities of the solar magnetic cycle are in good agreement with the neutron monitors experimental data. To reach a compatibility of the theoretical modeling with observations for the last minimum epoch of solar activity 2007–2009 (A < 0) a parallel diffusion coefficient was increased by ∼40%.     

Solving a plane problem of elasticity theory with the use of a hybrid FEM formulation

In the framework of a plane problem of elasticity theory in strength analysis based on the finite element method in the hybrid formulation, we suggest that the approximation of displacements and stresses be used as magnitudes of vector and tensor fields, respectively. The quadrilateral finite element, the displacements and stresses of which are accepted as nodal unknowns is proposed. The mixed Reissner functional is applied to form a finite element deformation matrix.     

Spin-stabilized satellite magnetic attitude control scheme without initial detumbling

The angular motion of an axisymmetrical satellite equipped with an active magnetic attitude control system is considered. The dynamics of the satellite are analytically studied on the whole control loop. The control loop is as follows: preliminary reorientation along with nutation damping, spinning about the axis of symmetry, then precise reorientation of the axis of symmetry in inertial space. Reorientation starts right after separation from the launch vehicle. Active magnetic attitude control system time-response with respect to its parameters is analyzed. It is proven that low-inclined orbit forces low control system time-response. Comparison with the common control scheme shows the time-response gain. Numerical analysis of the disturbances effect is carried out and good pointing accuracy is proved.