固定模糊度的GRACE-FO卫星简化动力学定轨精度分析

对GRACE-FO卫星进行精密定轨研究,利用简化动力学方法处理其14 d的星载GPS数据并进行精度分析。通过载波相位残差分析、重叠弧段比较、参考轨道比较以及KBR检核,对比通过UPD方法固定模糊度参数的简化动力学轨道与浮点解轨道。结果表明,GRACE-FO卫星固定解轨道的载波相位残差约为1 cm,比浮点解大1～2 mm。3 d固定解重叠弧段差异的RMS值在R、T、N方向上均小于等于9.4 mm,优于浮点解的12.4 mm。与GFZ提供的精密科学轨道相比,GRACE-C卫星简化动力学固定解轨道在各方向上差异的RMS均值均小于1 cm,表明解算得到的轨道与PSO具有较高的一致性。固定模糊度后K波段测距(K-band ranging)检核残差的RMS均值从9.6 mm下降到6.7 mm,说明固定解能够进一步提升GRACE-FO卫星间的相对位置精度。因此,模糊度固定能够改善GRACE-FO卫星的定轨精度,提供更可靠的轨道服务。     

NCEP/NCAR再分析气温在南极中山站-Dome A考察断面的适用性研究

以东南极冰盖边缘地带LGB69、冰盖内陆Eagle、冰盖顶点Dome A自动气象站2005—2006年记录的日平均气温为基础,辅以南极大陆边缘中山站2005年的连续气温资料,根据4个站点的海拔、气温、气压和地形,选择最接近气象站观测点的气压层,通过改进的9格点反距离加权内插法,分析NCEP/NCAR再分析气温在该断面的适用性.结果表明:NCEP/NCAR再分析气温与中山站、LGB69站、Eagle站和Dome A站实际观测值之间的相关系数分别高达0.624、0.648、0.744和0.705(p0.001,n≥365),能够反映本地区气温的年变化和季节变化.但与实测值相比,再分析资料具有气温普遍偏高、年温差和标准偏差偏小、春夏季适用性强而秋冬季适用性差等特点.此外,从南极冰盖边缘至内陆,再分析气温误差有增大的趋势.     

无准确初轨信息时星载GPS低轨卫星定轨方法研究

本文提出了适用于星载GPS低轨卫星定轨的一种精密自主定轨方法。该方法利用星载GPS观测资料直接解算GPS方程求得卫星初轨,避免了早期使用短弧资料定初轨时法方程的病态性的影响,为精密定轨提供了较准确的近似值,并以此展开观测方程进行精密定轨,保证了迭代过程的收敛,减少了迭代次数,节约了时间,适用于低轨卫星的自主定轨和实时定轨。     

GPS卫星定轨中的摄动力影响分析

分析了地球重力场、海洋潮汐、行星摄动、地极潮汐、相对论加速度等对GPS轨道拟合及轨道外推造成的影响,认为在GPS定轨中除了顾及地球重力场及海洋潮汐对卫星轨道影响之外,还应注意地球重力场模型及海洋潮汐模型的选用问题;此外,在短弧定轨可以不考虑行星摄动、地极潮汐以及相对论加速度的影响,但长弧定轨中需考虑它们的影响。     

Solar Sail Halo Orbits at the Sun–Earth Artificial L 1 Point

Halo orbits for solar sails at artificial Sun–Earth L₁ points are investigated by a third order approximate solution. Two families of halo orbits are explored as defined by the sail attitude. Case I: the sail normal is directed along the Sun-sail line. Case II: the sail normal is directed along the Sun–Earth line. In both cases the minimum amplitude of a halo orbit increases as the lightness number of the solar sail increases. The effect of the z-direction amplitude on x- or y-direction amplitude is also investigated and the results show that the effect is relatively small. In case I, the orbit period increases as the sail lightness number increases, while in case II, as the lightness number increases, the orbit period increases first and then decreases after the lightness number exceeds ~0.01.     

Laplacian Orbit Determination and Differential Corrections

Laplace’s method is a standard for the calculation of a preliminary orbit. Certain modifications, briefly summarized, enhance its efficacy. At least one differential correction is recommended, and sometimes becomes essential, to increase the accuracy of the computed orbital elements. Difficult problems, lack of convergence of the differential corrections, for example, can be handled by total least squares or ridge regression. The differential corrections represent more than just getting better agreement with the observations, but a means by which a satisfactory orbit can be calculated. The method is applied to three examples of differing difficulty: to calculate a preliminary orbit of Comet 122/P de Vico from 59 observations made during five days in 1995; a more difficult calculation of a possible new object with a poor distribution of observations; Herget’s method fails for this example; and finally a really difficult object, the Amor type minor planet 1982 DV (3288 Seleucus). For this last object use of L₁ regression becomes essential to calculate a preliminary orbit. For this orbit Laplace’s method compares favorably with Gauss’s.     

SINGLE AND MULTI-STATION RADAR OBSERVATIONS OF THE GEMINID/SEXTANTID METEOR STREAM SYSTEM

The Canadian Meteor Orbit Radar (CMOR) is used to look at the distribution of meteoroids which encounter the Earth. As a single-station operation, it is capable of determining radiant distributions on a statistical basis and the position and speed of individual meteors. The addition of two outlying receiving stations allows the determination of the orientation in space of the meteor leading to an estimate of the orbital parameters of the individual meteor and an independent additional estimate of its speed. Comparison is made of the effectiveness of the two modes of operation using observations on the Geminid and Sextantid meteor streams.     

抗差方差分量估计在卫星定轨中的应用

针对卫星精密定轨过程中观测资料存在粗差以及观测资料的合理定权问题，将抗差方差分量估计引入到卫星精密定轨中。采用Lageos 2卫星1996年1月至2000年12月的全球SLR实测数据进行了卫星精密定轨计算，结果表明，抗差方差分量估计既可以有效地减弱观测资料中粗差的影响，又可以较好地解决观测资料的合理加权问题，从而可以提高卫星的定轨精度。     

双重网格井间地震层析成像技术

提出了一种不同于常规的井间地震层析成像技术，即在较细的网格上进行射线追踪，以提高射线路径和旅行时的计算精度，在较粗的网格上进行层析反演成像，使网格像素上射线覆盖的最低次数达到一定要求，以提高成像质量。分析了采用这种双重网格地震层析成像技术的必要性，模型实验证实了此技术实用性和有效性。     

Spacecraft Orbit Determination with The B-spline Approximation Method

It is known that the dynamical orbit determination is the most common way to get the precise orbits of spacecraft. However, it is hard to build up the precise dynamical model of spacecraft sometimes. In order to solve this problem, the technique of the orbit determination with the B-spline approximation method based on the theory of function approximation is presented in this article. In order to verify the effectiveness of this method, simulative orbit determinations in the cases of LEO (Low Earth Orbit), MEO (Medium Earth Orbit), and HEO (Highly Eccentric Orbit) satellites are performed, and it is shown that this method has a reliable accuracy and stable solution. The approach can be performed in both the conventional celestial coordinate system and the conventional terrestrial coordinate system. The spacecraft's position and velocity can be calculated directly with the B-spline approximation method, it needs not to integrate the dynamical equations, nor to calculate the state transfer matrix, thus the burden of calculations in the orbit determination is reduced substantially relative to the dynamical orbit determination method. The technique not only has a certain theoretical significance, but also can serve as a conventional algorithm in the spacecraft orbit determination.