关于星座小卫星的编队飞行问题

从轨道力学角度来看星座小卫星编队飞行和星星跟踪中的伴飞，遵循着如下动力学机制：(1)在各小卫星绕地球运动过程中轨道摄动变化的主要特征决定了星-星之间的空间构形，(2)当星星之间相互距离较近时，在退化的限制性三体问题(实为限制性二体问题)中，共线秤动点附近的条件周期运动亦可在一定时间内制约星-星之间的空间构形．将具体阐明这两种动力学机制的原理和相应的星星之间的相对构形，并用仿真计算来证实这两种动力学机制的适用范围，为星座小卫星编队飞行和在伴飞运动过程中进行轨控提供理论依据和具体的轨控条件．     

天体力学的几个热点问题

阐述当今天体力学前沿课题中的几个热点问题，近地小行星与地球的交会及其动力演化，航天器定轨新手段中的得一星跟踪自主定轨方法以及星际探测中的轨道力学问题。     

针对低轨星座的空间信号测距误差投影系数确定

随着低轨星座建设的不断推进,计算卫星空间信号测距误差(signal in space range error,SISRE)的面向对象不再局限于全球卫星导航系统(Global Navigation Satellite System, GNSS)的地面用户,还包括GNSS的低轨星载用户和低轨导航系统地面用户。为更好地支持基于低轨星座SISRE的解算,根据SISRE的计算原理,分别研究了低轨星载用户和低轨卫星地面用户的SISRE误差投影系数的特征。计算结果显示,GNSS卫星对地面用户的误差投影系数并不适用于低轨星载用户及低轨导航星座地面用户。当低轨卫星轨道高度由2 000 km降低至300 km时,GNSS卫星对低轨星载接收机的轨道径向误差投影系数由0.96增加到0.98,轨道切法平面误差投影系数由0.20降低至0.15;低轨卫星对地面用户的轨道径向误差投影系数从0.72降至0.37,轨道切法平面误差投影系数从0.49增加至0.66。上述结果可为未来低轨卫星相关的空间信号测距误差分析以及低轨完好性研究提供重要参考。     

关于星—星跟踪与地面跟踪的联合定轨问题

关于航天器测轨问题,由天基网部分地代替地基网是目前航天测控的一个发展趋势,现已实现的利用全球导航系统（ＧＰＳ）和跟踪与数据中继卫星系统（ＴＤＲＳＳ）对低轨用户星的测轨手段就是如此。本文将阐述另一种类型的测轨模型和具体定轨方法,即一个中低轨卫星星座中的卫星与地面站的组合对星座中其它卫星进行定轨。     

同步卫星短弧定轨

同步卫星受到摄动力的影响,它的实际轨道有一点漂移．卫星需要不断的调轨调姿,以保证其正常运行．为了研究卫星在几小时,甚至更短的时间内的轨迹情况,采用短弧段定轨法．用动力学方法进行短弧定轨,分别研究1小时和15分钟定轨并进行比较,目的是为了在同步轨道卫星变轨后,能尽快地为卫星提供精密的预报轨道．此外,在系列短弧定轨后,得到精密轨道系列,为研究轨道变化的力学因素及研究短弧中卫星转发器时延变化规律等提供依据．     

土星卫星的精密定轨方案

由于星际探测事业的发展,对土星卫星的定位精度要求愈来愈高,经典的分析法定轨方法已难以适应,在当今计算技术条件高度发展的背景下,本文给出了土星卫星的数值法定轨方案,采用了土星卫星运动的高精度力学模型,并运用１８７４－１９８９这１００多年间的观测资料,引用现代最小二乘估计,对土星卫生进行精密定轨。该方案可以在引用同样的力学模型的前提下,对土星各颗卫星进行定轨,亦可同时进行多颗卫星的定轨。相应的软件比较     

月球卫星轨道力学综述

月球探测器的运动通常可分为3个阶段，这3个阶段分别对应3种不同类型的轨道：近地停泊轨道、向月飞行的过渡轨道与环月飞行的月球卫星轨道。近地停泊轨道实为一种地球卫星轨道；过渡轨道则涉及不同的过渡方式(大推力或小推力等)；环月飞行的月球卫星轨道则与地球卫星轨道有很多不同之处，它决不是地球卫星轨道的简单克隆。针对这一点，全面阐述月球卫星的轨道力学问题，特别是环月飞行中的一些热点问题，如轨道摄动解的构造、近月点高度的下降及其涉及的卫星轨道寿命、各种特殊卫星(如太阳同步卫星和冻结轨道卫星等)的轨道特征、月球卫星定轨等。     

区域导航卫星精密定轨研究

区域卫星导航系统采用混合星座设计,GEO(地球同步轨道)卫星是系统的重要组成部分,其精密定轨技术也是导航系统的关键技术之一。GEO卫星的高轨特性致使地面跟踪基线长度有限,定轨几何条件不佳;其静地特性致使卫星轨道与钟差存在强相关特性,对于基于伪距的GEO卫星定轨模式,需要星地与站间时间同步技术的支持。因此,如何利用区域卫星导航系统的多种测量技术实现多模式、多层次的导航卫星精密定轨,是一项值得深入研究的课题。     

星载单频GPS接收机低轨卫星几何法定轨研究

讨论星载ＧＰＳ接收机为单频情形的低轨卫星几何法定轨,包括绝对定轨法,相对定轨法和动态网定轨法,并利用ＴＯＰＥＸ／ＰＯＳＥＩＤＯＮ卫星星载ＧＰＳ实现Ｌ１观测值进行验证。结果表明,绝对定轨法三维轨道位置精度可达２０ｍ左右,适用于低轨卫星实时导航;相对定轨和动态网定轨精度均比绝对定轨精度高,伪距相对定轨三维轨道位置精度可达米级,载波相位相对定轨精度可达分米级;动态网定轨相当于在各基准站相对定轨之间加权均     

星载GPS精密测轨研究及应用

星载ＧＰＳ定轨系统由于其全天侯、价格低、不受卫星高度的影响可达到米级、分米级乃至厘米级的测轨精度等特点已成为低轨道卫星精密定轨的要求,概述了星载ＧＰＳ系统的组成和定轨原理,给出了星载ＧＰＳ测轨的几种主要方法和数学模型,同时根据ＴＯＰＥＸ卫星星载ＧＰＳ实测数据分析了各种定轨方法的测轨精度以及影响定轨精度的各种因素。     

CEMP星HE 1005-1439中子俘获元素天体物理来源的研究

HE1005-1439是一颗金属丰度极低([Fe/H]～-3.0)的碳增丰贫金属星(Carbon Enhanced Metal-Poor,CEMP),该星的s-过程元素显著超丰([Ba/Fe]=1.16±0.31,[Pb/Fe]=1.98±0.19),而r-过程元素温和超丰([Eu/Fe]=0.46±0.22),使用单一的s-过程模型和i-过程模型均不能拟合该星中子俘获丰度分布.采用丰度分解的方法探究该星化学元素的天体物理来源可有助于理解CEMP星的形成和化学演化.利用s-过程和r-过程的混合模型对其中子俘获元素的丰度分布进行拟合,发现该星的中子俘获元素主要来源于低质量低金属丰度AGB伴星的s-过程核合成,而r-过程核合成也有贡献.     

卫星星座的结构演化

主要研究星座几何结构的演化问题，分析了在地球扁率摄动和卫星的入轨偏差影响下轨道的演化过程，以卫星的相位和升交点赤经为参数描述了星座结构演化的一般规律，又以星下点轨迹变化和星下点的相互位置关系的变化为参数描述了区域星座结构演化的地域特性．分析表明，地球扁率摄动将导致星座结构的整体漂移，而卫星的入轨偏差则会导致星座几何结构的紊乱，特别是轨道半长轴的偏差，将是影响星座几何结构稳定性的决定因素．     

Ensuring dynamic stability of the orbital structure of the Arktika-M space system

The control of the orbital structure of the satellite constellation (SC) of continuous service with spacecraft in highly elliptical orbits of the Molniya type is considered. For ensuring the SC dynamic stability, it is proposed to use passive, active, and combined approaches to the SC orbital structure control. A statement of the problem to ensur e dynamic stability is given and results of its solution for a particular variant of the orbital construction of the Arktika-M space system are presented for the passive control approach. The proposed orbital structure control is based on minimizing the evolution-induced space-time deformation of the orbital structure by means of differentiated selection of initial parameters of orbits at the stages of the SC deployment and replenishment and by means of control of the spacecraft’s ground track at the SC operation stage. Using this control method is especially important with long active life spans of spacecraft and limitations on propellant margins for orbit correction.     

3-Dimensional Necklace Flower Constellations

A new approach in satellite constellation design is presented in this paper, taking as a base the 3D Lattice Flower Constellation Theory and introducing the necklace problem in its formulation. This creates a further generalization of the Flower Constellation Theory, increasing the possibilities of constellation distribution while maintaining the characteristic symmetries of the original theory in the design.     

Satellite motion in a Manev potential with drag

In this paper, we consider a satellite orbiting in a Manev gravitational potential under the influence of an atmospheric drag force that varies with the square of velocity. Using an exponential atmosphere that varies with the orbital altitude of the satellite, we examine a circular orbit scenario. In particular, we derive expressions for the change in satellite radial distance as a function of the drag force parameters and obtain numerical results. The Manev potential is an alternative to the Newtonian potential that has a wide variety of applications, in astronomy, astrophysics, space dynamics, classical physics, mechanics, and even atomic physics.     

Chaotic Dynamics of Satellite Systems

We consider the problem of calculating the Lyapunov time (the characteristic time of predictable dynamics) of chaotic motion in the vicinity of separatrices of orbital resonances in satellite systems. The primary objects of study are the chaotic regimes that have occurred in the history of the orbital dynamics of the second and fifth Uranian satellites (Umbriel and Miranda) and the first and third Saturnian satellites (Mimas and Tethys). We study the dynamics in the vicinity of separatrices of the resonance multiplets corresponding to the 3 : 1 commensurability of mean motions of Miranda and Umbriel and the multiplets corresponding to the 2 : 1 commensurability of mean motions of Mimas and Tethys. These chaotic regimes have most probably contributed much to the long-term orbital evolution of the two satellite systems. The equations of motion have been numerically integrated to estimate the Lyapunov time in models corresponding to various epochs of the system evolution. Analytical estimates of the Lyapunov time have been obtained by a method (Shevchenko, 2002) based on the separatrix map theory. The analytical estimates have been compared to estimates obtained by direct numerical integration.__________Translated from Astronomicheskii Vestnik, Vol. 39, No. 4, 2005, pp. 364–374.Original Russian Text Copyright © 2005 by Mel’nikov, Shevchenko.     

The Loci of Satellite Positions: A Constellation Design Approach

In special cases in which satellite constellations can be described by a limited set of parameters, a correlation between the latter and the constellation characteristics (i.e. shape and kinematics of the satellite configurations) has been investigated. Such cases may be a useful starting point for designing more complex constellations in order to achieve better the desired performances. Therefore, this proves to be one way to fix an initial set of parameters once the desired behaviour of the constellation has been established on the basis of the operational purposes required. This revised version was published online in August 2006 with corrections to the Cover Date.     

Coriolis forces in numerical integration of satellite orbits,and absolute reference system

The reference system defined by Veis and currently used for computing satellite orbits is not sufficiently accurate for some scientific applications, considering the new accuracy of laser data. We have therefore defined another orbital reference system with associated apparent forces. The reference system chosen is the mean celestial system 1970.0. The motion of a satellite is numerically integrated in the instantaneous celestial system (sideral system), taking into account all the complementary forces due to precession and nutation. The complete set of formulas is given here and has been introduced in a differential orbital improvement program.     

A numerical-analytical method for studying the orbital evolution of distant planetary satellites

We describe an approximate numerical-analytical method for calculating the perturbations of the elements of distant satellite orbits. The model for the motion of a distant satellite includes the solar attraction and the eccentricity and ecliptic inclination of the orbit of the central planet. In addition, we take into account the variations in planetary orbital elements with time due to secular perturbations. Our work is based on Zeipel’s method for constructing the canonical transformations that relate osculating satellite orbital elements to the mean ones. The corresponding transformation of the Hamiltonian is used to construct an evolution system of equations for mean elements. The numerical solution of this system free from rapidly oscillating functions and the inverse transformation from the mean to osculating elements allows the evolution of distant satellite orbits to be studied on long time scales on the order of several hundred or thousand satellite orbital periods.