Image Smearing Modeling and Verification for Strapdown Star Sensor

To further extend study on celestial attitude determination with strapdown star sensor from static into dynamic field, one prerequisite is to generate precise dynamic simulating star maps. First a neat analytical solution of the smearing trajectory caused by spacecraft attitude maneuver is deduced successfully, whose parameters cover the geometric size of optics, three-axis angular velocities and CCD integral time. Then for the first time the mathematical law and method are discovered about how to synthesize the two formulae of smearing trajectory and the static Gaussian distribution function (GDF) model, the key of which is a line integral with regard to the static GDF attenuated by a factor 1/ L s (L s is the arc length of the smearing trajectory) along the smearing trajectory. The dynamic smearing model is then obtained, also in an analytical form. After that, three sets of typical simulating maps and data are simulated from this dynamic model manifesting the expected smearing effects, also compatible with the linear model as its special case of no boresight rotation. Finally, model validity tests on a rate turntable are carried out, which results in a mean correlation coefficient 0.920 0 between the camera images and the corresponding model simulated ones with the same parameters. The sufficient similarity verifies the validity of the dynamic smearing model. This model, after parameter calibration, can serve as a front-end loop of the ground semi-physical simulation system for celestial attitude determination with strapdown star sensor.     

Asymptotic Performance of Sparse Signal Detection Using Convex Programming Method

The detection of sparse signals against background noise is considered. Detecting signals of such kind is difficult since only a small portion of the signal carries information. Prior knowledge is usually assumed to ease detection. In this paper, we consider the general unknown and arbitrary sparse signal detection problem when no prior knowledge is available. Under a Neyman-Pearson hypothesis-testing framework, a new detection scheme is proposed by combining a generalized likelihood ratio test (GLRT)-like test statistic and convex programming methods which directly exploit sparsity in an underdetermined system of linear equations. We characterize large sample behavior of the proposed method by analyzing its asymptotic performance. Specifically, we give the condition for the Chernoff-consistent detection which shows that the proposed method is very sensitive to the 2 norm energy of the sparse signals. Both the false alarm rate and the miss rate tend to zero at vanishing signal-to-noise ratio (SNR), as long as the signal energy grows at least logarithmically with the problem dimension. Next we give a large deviation analysis to characterize the error exponent for the Neyman-Pearson detection. We derive the oracle error exponent assuming signal knowledge. Then we explicitly derive the error exponent of the proposed scheme and compare it with the oracle exponent. We complement our study with numerical experiments, showing that the proposed method performs in the vicinity of the likelihood ratio test (LRT) method in the finite sample scenario and the error probability degrades exponentially with the number of observations.     

复杂截面高层建筑角对角布置的气动干扰机理研究

基于两栋角对角布置、横截面复杂的实际超高层建筑的刚性模型测压风洞试验数据,分析了综合体型系数以及风压系数分布特性,详细讨论了建筑间的气动干扰机理。研究结果表明,两栋塔楼在气流方向上串列布置时,其间可能产生恒定的旋涡,使得上游建筑背风面和下游建筑迎风面的平均风压都表现为较高的负压,上游建筑的平均风荷载会大大超过单体建筑的情况;两栋塔楼在气流方向上大致并列布置时,建筑两侧可能产生周期性的旋涡脱落,导致横风向响应的均方根值较大。此外,建筑的等效静力风荷载以平均风荷载为主,且建筑的自由振动频率远远大于气动力的卓越频率,脉动风荷载以背景分量为主而共振分量较小,这使得结构刚度的增加无法显著降低建筑的等效静力风荷载。     

Defect Recognition in Thermosonic Imaging

This work is aimed at developing an effective method for defect recognition in thermosonic imaging.The heat mechanism of thermosonic imaging is introduced,and the problem for defect recognition is discussed.For this purpose,defect existing in the inner wall of a metal pipeline specimen and defects embedded in a carbon fiber reinforced plastic(CFRP) laminate are tested.The experimental data are processed by pulse phase thermography(PPT) method to show the phase images at different frequencies,and the characteristic of phase angle vs frequency curve of thermal anomalies and sound area is analyzed.A binary image,which is based on the characteristic value of defects,is obtained by a new recognition algorithm to show the defects.Results demonstrate good defect recognition performance for thermosonic imaging,and the reliability of this technique can be improved by the method.     

The STEREO/IMPACT Magnetic Field Experiment

The magnetometer on the STEREO mission is one of the sensors in the IMPACT instrument suite. A single, triaxial, wide-range, low-power and noise fluxgate magnetometer of traditional design—and reduced volume configuration—has been implemented in each spacecraft. The sensors are mounted on the IMPACT telescoping booms at a distance of ～3 m from the spacecraft body to reduce magnetic contamination. The electronics have been designed as an integral part of the IMPACT Data Processing Unit, sharing a common power converter and data/command interfaces. The instruments cover the range ±65,536 nT in two intervals controlled by the IDPU (±512 nT; ±65,536 nT). This very wide range allows operation of the instruments during all phases of the mission, including Earth flybys as well as during spacecraft test and integration in the geomagnetic field. The primary STEREO/IMPACT science objectives addressed by the magnetometer are the study of the interplanetary magnetic field (IMF), its response to solar activity, and its relationship to solar wind structure. The instruments were powered on and the booms deployed on November 1, 2006, seven days after the spacecraft were launched, and are operating nominally. A magnetic cleanliness program was implemented to minimize variable spacecraft fields and to ensure that the static spacecraft-generated magnetic field does not interfere with the measurements.     

全机地面共振试验的飞机支持方式综述

飞机的支持方式对于全机地面共振试验十分重要。在分析飞机支持要求的基础上，论述了3种基本的飞机支持方式：起落架支持、空气弹簧支持、弹簧绳吊挂支持，并给出了每种支持方式的刚度系数。     

层板冷却特性的实验与数值模拟研究

在大尺寸低速回流式风洞内对一种应用于涡轮叶片的典型的层板结构进行了流阻特性和冷却特性的实验研究,获取了该层板综合冷却效果与层板两侧压比的关系,结果表明层板具有很高的冷却效果。运用商用软件Fluent6 0对其进行了流固耦合传热计算,分析了层板内部复杂的流动和换热情况,得到了在不同的进出口条件下该层板的综合冷却效果。计算结果和实验值进行了比较,两者符合较好,表明通过数值计算获取层板冷却效果的方法是可行的。     

The Magnetic Field Pile-up and Density Depletion in the Martian Magnetosheath: A Comparison with the Plasma Depletion Layer Upstream of the Earth's Magnetopause

Using magnetometer and electron observations from the Mars Global Surveyor (MGS) and the Wind spacecraft we show that the region of magnetic field pile-up and density decrease located between the Martian ionosphere and bow shock exhibit strong similarities with the plasma depletion layer (PDL) observed upstream of the Earth's magnetopause in the absence of magnetic reconnection when the magnetopause is a solid obstacle in the solar wind. A PDL is formed upstream of the terrestrial magnetopause when the magnetic field piles up against the obstacle and particles in the pile-up region are squeezed away from the high magnetic pressure region along the field lines as the flux tubes convect toward the magnetopause. We here discuss the possibility that at least part of the region of magnetic field pile-up and density depletion upstream of Mars may be formed by the same physical processes which generate the PDL upstream of the Earth's magnetopause. More complete ion, electron, and neutral measurements are needed to conclusively determine the relative importance of the plasma depletion process versus exospheric processes.     

层板冷却结构强化换热机理

应用简化的换热模型分析了影响层板冷却效果的因素,得出了燃气侧气膜冷却效率η_f,层板内部换热效率η_i和参数f是影响冷效的决定因素。为了研究层板强化换热机理,提高其内部换热效率η_i以优化层板传热设计,本文在相同的两侧换热条件和冷气密流下,对5种相同孔径、通道高度和开孔率,不同内部绕流形式的层板结构和1种双层壁结构进行了流固耦合传热计算,得到了其综合冷却效率。结果表明层板结构的综合冷却效率明显高于双层壁;冷气沿程吸热焓增带走了大部分从燃气侧进入层板的热,并且冷气与层板内表面的换热主要发生在出气板上,扰流柱的存在增加了换热面积,一定程度上增强了换热;合理设计绕流结构有利于改善层板的热均匀性。      

角加速度计在飞行器/水下航行器制导控制系统中的应用

介绍了角加速度计在飞行器/水下航行器制导控制的三个领域:制导控制一体化设计、抗未知瞬发干扰稳定控制、动力学系数辨识中的应用机理。角加速度计作为一种测量用传感器,能够在飞行器/水下航行器运动过程中直接采集俯仰、航向和滚动三个通道的飞行器/航行器本体的角加速度信息。通过对角加速度信息的获取及处理,分析飞行器/水下航行器质心运动与姿态运动的内在联系,同时将角加速度信息与惯性导航转置所采集的信息相互结合,便可以使得系统的动力学系数辨识和制导控制一体化设计成为可能;同时,由于角加速度信息在相位上超前于角速度反馈,因此引入角加速度信息的反馈可以提升飞行器/水下航行器抗未知瞬发干扰的能力。