地球自转变化的重力效应

极移对重力测量的影响在前人的研究和工作中已得到了充分的考虑并有不同形式的改正公式。但是由于地轴转动速率变化的重力效应的量级很小,且限于以前的测量精度以及资料处理方法, 因而常常被忽略。随着重力测量精度的提高以及资料处理方法的改进, 有必要重新讨论该项影响。本文从推导地球瞬时自转极运动对地面台站重力测量值影响的公式入手, 将地球自转角速率变化的重力效应和极移的重力效应分离开来, 并对它们的量级分别作了估计。本文着重讨论自转角速率变化对重力测量的影响。用 Ｉ Ｅ Ｒ Ｓ 的日长变化序列和极移序列分别具体地计算了１９８２ ～１９９６ 年期间对武汉的重力测量值的影响, 结果表明, 自转角速率变化对武汉地区重力值的影响最大可达０ ．２５ ｍｉｃｒｏｇａｌ（ｐｅａｋ －ｔｏ － ｐｅａｋ） , 这在高精度的绝对重力测量和相对重力测量中不应再被忽略     

地球自转变化的重力效应

极移对重力测量的影响在前人的研究和工作中已得到了充分的考虑并有不同形式的改正公式。但是由于地轴转动速率变化的重力效应的量级很小,且限于以前的测量精度以及资料处理方法,因而常常被忽略。随着着重力测量精度的提高以及资料处理方法的改进,有必要重新讨论该影响。本文从推导地球瞬时自转极运动对地面台站重力测量值影响的公式入手,将地球自转角速率变化的重力效应和极移的重力效应分离来来,并对它们的量级分别作了估计。     

一种计算垂线偏差的抗差最小二乘严密解法

针对当前利用大地水准面模型求解垂线偏差精度不高、稳健性差的问题,设计了一种严密的垂线偏差抗差最小二乘解法.首先,基于大地水准面与垂线偏差的关系,采用EGM2008 (Earth Gravity Model 2008)重力场模型计算参数初始解;然后,引入中位数抗差法,并选用Huber权函数计算等价权,迭代计算出稳健的垂线偏差最小二乘解;最后,结合两个实测算例对设计方法进行验证.试验结果表明,该方法计算的垂线偏差分量与约定真值最大偏差在0.5′′左右,相较于对比方法精度更高;同时,该方法能有效抵抗粗差值的影响,具有较强的稳健性.     

德令哈13.7m望远镜重力变形研究

借助于数字摄影测量结果调整天线面板,使德令哈13.7 m望远镜在仰角52°时获得最佳反射面面形,从而使天线效率在观测仰角范围内得到整体优化.与之前基于经纬仪测量的面板调整结果相比,天线口径效率提高约1倍.依据不同俯仰姿态下的测量结果,得到了天线的重力变形模型,包括副面偏移和倾斜、主面焦距和面形偏差随仰角变化的规律.根据不同仰角的面形偏差测量数据反演反射面重力变形模型时,采用了数据拟合方法,这样可以减小测量误差对模型精度的影响.     

PSD法测量大型射电望远镜副面位姿

指向精度是大型射电望远镜天线具有挑战性的关键技术指标.在望远镜运行中,方位俯仰角的变化、重力以及日照等对副面撑杆的综合影响会引起望远镜的副面位姿改变从而引起指向误差的增加和天线效率的降低.基于天马65 m射电望远镜,使用位置传感器装置(PSD)法构建了副面位置偏移量测定系统,可以实时采集副面的3维位移数据,构建重力模型,将测试结果与射电法构建的现有副面模型进行对比,有较好的一致性.此外,该系统可以分析日照(引起撑腿局部温度效应)引起的副面位移情况,也可以监视风载和瞬时启停对副面位姿的影响.     

一种测定并置站垂线偏差的小网参数转换法

推导了传统全球卫星导航定位系统(GNSS)测定垂线偏差(Deflection of the Vertical, DOV)形式误差的表达式;提出一种可用以解算并置站DOV的小网参数转换法.利用乌鲁木齐南山多技术并置站控制网观测信息,开展了算法验证,并对该站内多个地点DOV开展了实测.结果表明,高精度的小网DOV仅由点位观测精度最高、覆盖面积最广的3个站点决定.个别精度较差的点会为DOV的测定值带来较大的不确定性;采用小网转换法所解算的DOV与实测值间的一致性分别为-2.3′′±4.3′′(子午分量)和0.2′′±4.6′′(卯酉分量);小网转换求取DOV的方法在精度上与经典的GNSS水准方法相当,但步骤更加简便.鉴于多技术并置站会不定期地开展本地测量,可利用该方法实现多技术并置站DOV的零成本长期监测.     

重力卫星检测到的全球陆地水储量变化

利用GRACE时变重力位模型反演了2004年至2008年共60个月的全球陆地水存储量变化,并采用滑动年平均,对全球陆地水储量的长期性变化情况进行了分析,同时也推求了全球陆地水储量的季节性变化。研究表明,使用滑动年平均对GRACE重力位模型数据进行处理,可以较好地揭示全球陆地水储量的长期和季节性变化情况,其监测能力足以揭示几cm的等效水高变化。     

用球函数方法计算东亚测站的综合海潮负荷参数(英)

用球谐函数方法（SHM）计算了由Schwiderski海潮图和日本海海潮图引起的M2,S2,K1和O1各分潮波的综合海潮负荷参数.计算中采用了Pagiatakis（1990）地球模型的负荷Love数.结果表明SHM具有更高的计算效率和计算精度．为了真正实现±毫米的VLBI地壳运动测定精度和±0.1微伽的绝对重力测量精度,对未来海潮图模型,特别是日本海的海潮图模型的精度要求作了讨论．计算结果还表明不同地球模型的负荷Love数对计算的测站位移之差为0.7毫米,在目前测量精度下尚可以不作考虑.中国近海的海潮M2波对台北,上海,Daejeon,Okinawa,和Kagosima站的径向和水平分量位移影响可分别达±22．4～±1．0毫米和±05-±5.5毫米,表明中国近海高精度的海潮图模型对东亚测站的地壳运动高精度测量是十分重要的．     

利用GNSS测量射电望远镜参考点的仿真分析

高精度测量射电望远镜参考点和轴线偏差等参数,对建立天线指向模型和本地连接参数、提高测站坐标精度等具有重要意义。为完成新建射电望远镜参考点初始参考值的快速测定,根据望远镜的旋转模型,结合常规静态归心测量方法和随机动态测量方法,提出了一种利用GNSS天线代替测量靶标实现望远镜参考点测量的方法。通过仿真分析验证了该方法的合理性和有效性,并分析了数据点个数和数据点测量精度对天线参考点和轴线偏差解算精度的影响。     

模拟研究卫-卫跟踪中星间隔的选择问题

从两要从两个方面讨论了低轨卫星在做卫-卫跟踪(SST)观测时,星间隔的选择问题．1)用地球重力位系数作为扰动量,比较该扰动引起的不同间隔的SST星间距离和速度变化大小．2)用随机误差为1μm／s的星间速度变化作为模拟观测量,恢复不同间隔的地球重力位系数,并做精度评估．两种结果表明,适当增大SST间隔对求解重力场有利,但无限制增大无实际意义,对于选定高度为420km卫星,在作SST观测时,星间隔不宜超过690km,此模拟方法及结果对我国确定重力卫星指标有着重要意义．     

The 2nd-order Post-Newtonian Orbit Equation of Light

Based on the 2nd-order post-Newtonian approximation under the DSX frame of the general relativity theory, the 2nd-order post-Newtonian orbital equation of light in the axis-symmetrical stationary spacetime is derived, and from this, the angle of deflection of light propagating in the equatorial plane is derived. The obtained results are consistent with those of the Schwarzchild and Kerr metrics within the limits of measuring precision.     

基于EfficientNet的星系形态分类研究

星系的结构和形态能够反映星系自身的物理性质,其形态的分类是后续分析研究的一个重要环节.EfficientNet模型使用复合系数对深度网络模型的深度、宽度、输入图像分辨率进行更加结构化的统一缩放,是一种新的深度网络优化扩展方法.将该模型应用于星系数据形态的分类研究中,结果表明基于EfficientNetB5模型的平均准确率、精确率、召回率以及F1分数(精确率与召回率的调和平均数)都在96.6%以上,与残差网络(Residual network, ResNet)中ResNet-26模型的分类结果相比有较大的提升.实验结果证明EfficientNet的深度网络优化扩展方法可行且有效,可应用于星系的形态分类.     

Distribution and time-variation of spire streaks at Pavonis Mons on Mars

We documented the distribution and the time-variation of the specific dark wind streaks at Pavonis Mons. We focused on the streaks we named “Spire Streaks”, which are overlapping spindle shaped dark streaks at the upper boundary of the coalesced dark streaks on Tharsis volcanoes. We investigated both visible and infrared images obtained by Viking orbiter camera, Mars Orbiter Camera (MOC), THEMIS, CTX and HiRISE of the spire streaks at Pavonis Mons. We also used topographic data obtained by Mars Orbiter Laser Altimeter (MOLA) to see the relationship between the topography and the distribution of the spire streaks. The spire streaks at Pavonis Mons provide us high-resolution information about the direction of the nighttime slope wind, and could be indirect clues for the time-variation of the nighttime environment. We conclude that the spire streaks are erosional features. However, some features of the spire streaks reported in this paper are outside the scope of previous modeling for erosional process, and we need a new category of model for the formation.     

Formation flying solar-sail gravity tractors in displaced orbit for towing near-Earth asteroids

Several methods of asteroid deflection have been proposed in literature and the gravitational tractor is a new method using gravitational coupling for near-Earth object orbit modification. One weak point of gravitational tractor is that the deflection capability is limited by the mass and propellant of the spacecraft. To enhance the deflection capability, formation flying solar sail gravitational tractor is proposed and its deflection capability is compared with that of a single solar sail gravitational tractor. The results show that the orbital deflection can be greatly increased by increasing the number of the sails. The formation flying solar sail gravitational tractor requires several sails to evolve on a small displaced orbit above the asteroid. Therefore, a proper control should be applied to guarantee that the gravitational tractor is stable and free of collisions. Two control strategies are investigated in this paper: a loose formation flying realized by a simple controller with only thrust modulation and a tight formation realized by the sliding-mode controller and equilibrium shaping method. The merits of the loose and tight formations are the simplicity and robustness of their controllers, respectively.     

A new lunar absolute control point: established by images from the landing camera on Chang'e-3

The establishment of a lunar control network is one of the core tasks in selenodesy, in which defining an absolute control point on the Moon is the most important step. However, up to now, the number of absolute control points has been very sparse. These absolute control points have mainly been lunar laser ranging retroreflectors, whose geographical location can be observed by observations on Earth and also identified in high resolution lunar satellite images. The Chang'e-3(CE-3) probe successfully landed on the Moon, and its geographical location has been monitored by an observing station on Earth. Since its positional accuracy is expected to reach the meter level, the CE-3 landing site can become a new high precision absolute control point. We use a sequence of images taken from the landing camera, as well as satellite images taken by CE-1 and CE-2, to identify the location of the CE-3 lander. With its geographical location known, the CE-3 landing site can be established as a new absolute control point, which will effectively expand the current area of the lunar absolute control network by 22%, and can greatly facilitate future research in the field of lunar surveying and mapping, as well as selenodesy.     

三星星座对地定位的最佳构形研究

用数值方法对三星星座几何构形与定位精度的关系进行了仿真计算，结果表明对满足较高定位精度的区域进行定位，三星的几何构形呈等边三角形时，定位精度最高。     

Effect of the finite size of an asteroid on its deflection using a tether–ballast system

Potentially hazardous near-Earth objects which can impose a significant threat on life on the planet have generated a lot of interest in the study of various asteroid deflection strategies. There are numerous asteroid deflection techniques suggested and discussed in the literature. This paper is focused on one of the non-destructive asteroid deflection strategies by attaching a long tether–ballast system to the asteroid. In the existing literature on this technique, very simplified models of the asteroid-tether–ballast system including a point mass model of the asteroid have been used. In this paper, the dynamical effect of using a finite size asteroid model on the asteroid deflection achieved is analyzed in detail. It has been shown that considering the finite size of the asteroid, instead of the point mass approximation, can have significant influence on the deflection predicted. Furthermore the effect of the tether-deployment stage, which is an essential part of any realistic asteroid deflection mission, on the predicted deflection is studied in this paper. Finally the effect of cutting the tether on the deflection achieved is analyzed and it has been shown that depending on the orbital properties of the asteroid as well as its size and rotational rate, cutting the tether at an appropriate time can increase the deflection achieved. Several numerical examples have been used in this paper to elaborate on the proposed technique and to quantitatively analyze the effect of different parameters on the asteroid deflection.     

Accurate analytical approximation of asteroid deflection with constant tangential thrust

We present analytical formulas to estimate the variation of achieved deflection for an Earth-impacting asteroid following a continuous tangential low-thrust deflection strategy. Relatively simple analytical expressions are obtained with the aid of asymptotic theory and the use of Peláez orbital elements set, an approach that is particularly suitable to the asteroid deflection problem and is not limited to small eccentricities. The accuracy of the proposed formulas is evaluated numerically showing negligible error for both early and late deflection campaigns. The results will be of aid in planning future low-thrust asteroid deflection missions.     

A more exact expression for the gravitational deflection of light,derived using material medium approach

The deflection of a ray of light passing close to a gravitational mass is generally calculated from the null geodesic which the light ray (photon) follows. However, there is an alternate approach, where the effect of gravitation on the ray of light is estimated by considering the ray to be passing through a material medium. Calculations have been done in this paper, following the latter approach, to estimate the amount of deflection due to a static non-rotating mass. The refractive index of such a material medium, has been calculated in a more rigorous manner in the present work, and the final expression for the amount of deflection calculated here is claimed to be more exact than all other expressions derived so far, using material medium approach. Based on this expression, the amount of deflection for a sun grazing ray has also been calculated. The exact amount of deflection can be performed in a number of ways, without the material medium approach. However, the method presented here using the material medium approach and without any weak field approximation is believed to be original.