ESA开展GEO上小碎片的调查

文章主要介绍了欧空局开展地球同步轨道(GEO)小碎片的调查情况及相应技术.     

电子干扰对低可观测飞行器飞行路径规划的影响

为了提高巡航导弹的低空突防能力,在分析电子干扰对雷达网威胁区域的影响后认为:在多重干扰条件下,雷达探测空间会顺着干扰方向产生内凹和偏移,因此,建立了新的雷达探测空间模型.采用空间对象间拓扑关系推理方法建立了飞行器飞行路径规划目标函数中雷达威胁指数模型,然后改进了飞行器飞行路径规划模型,并在此基础上进行了巡航导弹飞行路径规划的软件仿真.仿真结果表明:考虑电子干扰对雷达威胁区域的影响情况下规划的飞行路径能够回避雷达威胁,有效提高飞行器低空突防能力.     

小推力航天器的地月低能转移轨道

 在限制性四体模型下研究基于小推力方式的地月低能转移问题,通过借助于平动点轨道的相空间结构来揭示小推力转移的机理。重点研究了小推力转移自由飞行段的构造：经由LL₁点穿越获得最小能量的低能转移;而经由LL₁点Halo轨道穿越,得到(M,N)圈穿越轨道;由于Halo轨道相对于平动点增加了一维度的选择,根据(2,2)圈穿越轨道构造该转移的自由飞行段。在地球势阱逃逸和月球势阱捕获段,分别设计了合适的小推力的控制律及发动机开/关机时间,成功实施近地球段的小推力加速和近月球段的减速。尽管未对所得到的结果进行优化,所得转移轨道的燃料消耗也与类似边界条件的SMART-1轨道基本一致。     

基于GNSS的高轨卫星定位技术研究

利用全球卫星导航系统(GNSS)进行导航定位具有全球、全天候、实时和高精度的优点,应用于高地球轨道(HEO)卫星的定位,能够提供精确的轨道和姿态确定,并且可以克服目前主要利用地面测控系统对HEO卫星进行定位的设备复杂、投资高等缺点,使得自主导航成为可能.本文对利用GNSS的高轨卫星定位相关技术进行了研究,分析了单一GNSS系统和多个GNSS组合系统的卫星可见性、动态性和几何精度因子(GDOP).通过仿真分析表明,利用组合GNSS系统并通过提高GNSS接收机灵敏度的方法,可以解决GNSS进行HEO卫星定位的相关问题,并能保证HEO卫星定位精度的要求.      

Application of CCD drift-scan photoelectric technique on monitoring GEO satellites

Geosynchronous Earth Orbit (GEO) satellites are widely used because of their unique characteristics of high-orbit and remaining permanently in the same area of the sky. Precise monitoring of GEO satellites can provide a key reference for the judgment of satellite operation status, the capture and identification of targets, and the analysis of collision warning. The observation using ground-based optical telescopes plays an important role in the field of monitoring GEO targets. Different from distant celestial bodies, there is a relative movement between the GEO target and the background reference stars, which makes the conventional observation method limited for long focal length telescopes. CCD drift-scan photoelectric technique is applied on monitoring GEO targets. In the case of parking the telescope, the good round images of the background reference stars and the GEO target at the same sky region can be obtained through the alternating observation of CCD drift-scan mode and CCD stare mode, so as to improve the precision of celestial positioning for the GEO target. Observation experiments of GEO targets were carried out with 1.56-meter telescope of Shanghai Astronomical Observatory. The results show that the application of CCD drift-scan photoelectric technique makes the precision of observing the GEO target reach the level of 0.2″, which gives full play to the advantage of the long focal length of the telescope. The effect of orbit improvement based on multi-pass of observations is obvious and the prediction precision of extrapolating to 72-h is in the order of several arc seconds in azimuth and elevation.     

天文观测卫星动中探测机动测试系统设计

天文观测卫星普遍采用动中探测模式开展空间探测任务。为了实现动中探测姿态机动模式的地面有效验证，设计了整星机动集成测试方案。设计惯性空间基准的地面动力学仿真，满足惯性空间扫描仿真；设计整星各分系统间高精度时间统一系统，为整星机动测试提供统一基准；基于STK与Matlab接口模块，设计基于实时遥测数据的可视化判读系统，可提高测试判读实时性与准确度。整星测试结果表明，该方案有效验证了动中探测任务中姿态机动功能的正确性和指标符合情况，为开展整星地面测试和在轨应用提供了参考。     

Air-LUSI: A robotic telescope design for lunar spectral measurements

This paper presents the mechanical design of a new robotic telescope that was designed and built to acquire lunar spectral measurements from the science pod of NASA's ER-2 aircraft while flying at an altitude of 70,000 feet (21.34 km). The robotic telescope used a double gimbal design that allowed for target tracking in azimuth and elevation. In addition to the challenging and restrictive geometry of the science pod, each component needed to be carefully selected to ensure that they could withstand the operating conditions at high altitude such as harsh temperatures extending as low as −54 °C and atmospheric pressure less than 1.05 psi (7.23 kPa). Due to the cold temperatures, low atmospheric pressure and the likely exposure to moisture, high strength industrial linear actuators were used to create an adjustable linkage system that controlled the pointing and tracking of the telescope. Although unconventional, this allowed for a robust design that outperformed the team's expectations by tracking the Moon for 40 min with an average tracking error under 0.05°. The results presented within this paper were acquired during a first set of engineering test flights, with further scientific missions to follow.     

Simulation study of motion of charged particles trapped in Earth’s magnetosphere

This article aims to understand the motion of the charged particles trapped in the Earth’s inner magnetosphere. The emphasis is on identifying the numerical scheme, which is appropriate to characterize the trajectories of the charged particles of different energies that enter the Earth’s magnetosphere and get trap along the magnetic field lines. These particles perform three different periodic motions, namely: gyration, bounce, and azimuthal drift. However, often, the gyration of the particle is ignored, and only the guiding center of the particle is traced to reduce the computational time. It is because the simulation of all three motions (gyro, bounce, and drift) together needed a robust numerical scheme, which has less numerical dissipation. We have developed a three-dimensional test particle simulation model in which the relativistic equation of motion is solved numerically using the fourth and sixth-order Runge-Kutta methods. The stability of the simulation model is verified by checking the conservation of total kinetic energy and adiabatic invariants linked with each type of motion. We found that the sixth-order Runge-Kutta method is suitable to trace the complete trajectories of both proton and electron of a wide energy range, 5 keV to 250 MeV for L = 2 – 6. We have estimated the bounce and drift periods from the simulations, and they are found to be in good agreement with the theory. The study implies that a simulation model with sixth-order Runge-Kutta method can be applied to the time-vary, non-analytical form of magnetic configuration in future studies to understand the dynamics of charged particles trapped in Earth’s magnetosphere.     

微重力条件下两相流动沸腾换热地面等效模拟试验研究的必要性

介绍了航天器的热控制模式、对在微重力下的单相流与两相流的换热系统、微重力下与重力场下的两相流沸腾换热进行了比较。最后论述了在微重力条件下进行两相流沸腾换热地面等效试验研究的必要性。     

GPS／SINS姿态组合系统空间一致性研究

在基于卡尔曼滤波器并引入了姿态观测量的GPS/SINS组合导航系统中,GPS天线体坐标系与IMU所在的载体坐标系由于安装误差或其他原因不能完全重合,两个坐标系间存在失准角,导致多天线GPS与SINS输出的姿态信息在空间不能同步,这将影响卡尔曼滤波的效果。本文针对这一问题进行了深入的研究,分析了两个坐标系空间不一致的机理,给出了静态和动基座情况下标定两个坐标系位置关系的方法并进行仿真分析验证了其可行性。