CEMP星HE1005-1439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.     

贫金属星重元素丰度分布的参数化研究

基于大量贫金属星元素丰度的观测资料,以太阳系重元素丰度分布为标准,选取Sr、Ba、Eu分别作为贫金属星弱s-过程、主要s-过程、r-过程3种核合成的典型元素,采用参数化方法,分析了不同核合成过程对贫金属星重元素丰度的贡献比例.研究表明:金属丰度越高,弱s-过程、主要s-过程对较轻的中子俘获元素丰度的贡献就越大,较重的中子俘获元素主要由r-过程和主要s-过程产生;金属丰度较低,重中子俘获元素丰度主要由r-过程产生,星系早期弱s-过程对元素丰度几乎没有贡献.     

两颗CEMP-s视单星化学元素的天体物理来源研究

CS30301–015和HE1045+0226是两颗C元素和s-过程元素均超丰的贫金属(CEMP-s)星.视向速度观测发现这两颗星可能为单星.采用叠加与分解的方法探究这两颗星化学元素的天体物理来源能够为更好地理解银河系早期化学演化提供线索.计算结果表明:这两颗星的轻元素和Fe族元素主要产生于大质量星的primary过程.对于CS 30301–015,中子俘获元素主要来自AGB (Asymptotic Giant Branch)星中的主要s-过程. Pb的显著超丰主要归因于主要s-过程的贡献(约占Pb观测丰度的99.8%).需要更多的视向速度观测来确定这两颗星的轨道特征.对于HE 1045+0226, 56Z (质子数)62的重中子俘获元素主要来源于主要s-过程; Eu主要来源于主要r-过程.而轻中子俘获元素Y和Zr主要来自快速自转大质量星的primary弱s-过程,这一核合成过程对HE 1045+0226的Y和Zr丰度的贡献分别约为69.8%和67.6%.这从观测的角度证明弱s-过程能够在贫金属环境下发生.     

平均中子辐照量计算公式对CEMP-s和CEMP-r/s星的应用

最近的研究结果表明,目前流行的~(13)C壳层(~(13)C pocket)在热脉冲间隔期间辐射燃烧的低质量AGB(Asymptotic Giant Branch)星s-过程核合成模型,其核合成区域的中子辐照量分布可视为指数形式,平均中子辐照量τ0和模型参量之间的关系为τ0=-?τ/ln[q/(1-r+q)],式中?τ为每次照射的中子辐照量,r为重叠因子,q为~(13)C壳层占氦中间壳层的质量比例.利用文献中参数化AGB星s-过程核合成模型对20颗CEMP(Carbon-Enhanced Metal-Poor)-s和CEMP-s/r星观测丰度的拟合结果,对该平均中子辐照量计算公式的可靠性进行了检验,并初步探讨其在重元素s-过程核合成理论研究中的作用.研究结果表明:在辐射s-过程核合成机制下,对于经历连续多次中子照射的CEMP星,公式是适用的;和参数化AGB星s-过程核合成模型结合,公式可以作为单辐照或特殊CEMP星的一个有效筛选工具.考虑到~(13)C壳层的不确定性,公式在理解CEMP星中子俘获元素观测丰度产生的物理条件方面的作用值得做进一步的探讨.     

贫金属星中子俘获元素的丰度分布

在提出的贫金属星中子俘获元素丰度的计算模型基础上研究1999年新发表的21颗贫金属星的中子俘获元素丰度分布。结果表明，对较重的中子俘获元素理论预测曲线与观测值符合得很好，而对较轻的中子俘获元素二者有所偏离。这表明在贫金属环境下，对较重的中子俘获元素各核合成过程产生的丰度分布与太阳系中相应过程的丰度分布相似，但贡献比例与太阳系不同；而对较轻的中子俘获元素丰度分布与太阳系的丰度分布有所偏离；这也说明较轻的和较重的中子俘获元素的核合成场所不同，即具有不同的核合成机制。同时还特别讨论了丰度观测误差对表征各核合成过程的分量系数的影响。     

AGB星辐射s-过程核合成模型中子辐照量分布的计算方法和特点

考虑到模型参量随脉冲数的变化,推导出13C辐射燃烧的低质量AGB星s-过程核合成模型中子辐照量分布的计算方法,该方法具有普适性和简洁性.利用该方法,计算了3 M☉、太阳金属丰度恒星模型的中子辐照量分布.结果表明,若合理假设13C薄层内中子数密度均匀分布,则辐射核合成模型最终的中子辐照量分布趋近于指数分布.对于初始质量一定、金属丰度一定的恒星模型,平均中子辐照量τ0与每个脉冲的中子辐照量△τ存在确定的关系:τ0=0.434λ(q1,q2…qmmax+1,r1,r2…rmmax+1)△τ,式中mmax是带挖掘的脉冲总数,比例系数λ(q1,q2…qmmax+1,r1,r2…rmmax+1)可通过对最终中子辐照量分布的指数拟合得到.该式从中子辐照量分布角度定量地将经典模型和辐射s-过程核合成模型统一起来,使经典模型能为恒星模型核合成数值计算提供指导和约束.     

Mg超丰恒星的性质及其起源的研究

Mg超丰恒星([Mg/Fe]1.0)的特殊丰度模式无法用普通恒星的Mg元素起源和银河系化学演化机制解释。对这类特殊天体的起源和演化及化学丰度性质的研究,有助于深化理解恒星核合成及星系演化中一些特殊过程。首先介绍了目前文献中由高分辨率光谱证认的Mg超丰恒星,并对这些恒星的大气参数、运动学参数和化学丰度特征等性质及其起源机制进行了分析。其次统计了在斯隆巡天数据中系统搜寻的Mg超丰恒星候选体的大气参数和运动学分布特征,并且筛选了其中C超丰的候选体。研究发现绝大部分Mg超丰恒星表现了C超丰;在Mg超丰恒星中,存在中子俘获元素超丰的那些恒星都存在于双星系统中,其演化过程受到了AGB伴星的影响;而没有表现中子俘获元素超丰的那些恒星极有可能起源于第一代低能量超新星,部分恒星具有很高的空间速度,这类空间速度大于300 km/s的Mg超丰恒星可能是搜寻第一代恒星([Fe/H]-5.0)的最好样本。     

贫金属星中子俘获元素丰度

贫金属星的中子俘获元素丰度与恒星的形成和演化密切相关,它为研究星系形成早期的历史背景和化学演化提供了重要信息。贫金属星中子俘获元素丰度的研究已成为近年来核天体物理研究的前沿和热点。介绍了恒星内部重元素的核合图像,ｓ过程和ｒ过程核合成的概念及其核合成场所。着重介绍了近年来有关贫金属星中子俘获元素丰度的观测结果,综述了近年来贫金属星子俘获元素分布的理论研究进展情况和中子俘获元素的星系化学演化的研究进展     

HD 140283元素丰度分析及弱r-过程元素天体物理来源

HD 140283是一颗近邻极贫金属亚巨星,形成于宇宙大爆炸初期,被认为是迄今为止最古老的恒星之一,同时它也是一颗典型的弱r-过程星,对它的研究有助于深入理解宇宙早期演化、丰富元素核合成理论.将HD 140283从C到Zn的观测丰度与单个超新星(SN)事件元素理论产量进行拟合,得出HD 140283可能诞生于前身星质量为22.5 M⊙(下标"⊙"代表太阳)的超新星爆发污染的星云.基于同样的方法,研究了另外5颗典型弱r-过程星,分别得出了污染产生这些恒星的气体云的超新星前身星质量,进一步推测了弱r-过程可能发生的天体物理环境.     

贫金属星重元素平均丰度的金属丰度分区研究

将[Fe／H]从-3．0到0．0等分成10个区间,利用三种中子俘获过程的典型元素的观测丰度平均值,研究各核合成过程在各区间对重元素丰度的平均贡献,以及其它重元素的平均丰度,并与观测平均丰度进行比较．结果表明,在[Fe／H]＞－2．2范围内,各重元素核合成过程产生的重元素平均丰度分布与太阳系相似,但不同核合成过程的平均贡献比例与太阳系不相同．     

The 3-D lattice theory of Flower Constellations

Flower Constellations (FCs) have been extensively studied for use in optimal constellation design. The Harmonic FCs (HFCs) subset, representing the symmetric configurations, have recently been reformulated into 2-D Lattice Flower Constellations (2D-LFCs), encompassing the complete set of HFCs. Elliptic orbits are generally avoided due to the deleterious effects of Earth’s oblateness on the constellation, but here we present a novel concept for avoiding this problem and enabling more effective global coverage utilizing elliptic orbits. This new 3D Lattice Flower Constellations (3D-LFCs) framework generalizes the 2D-LFCs, Walker constellations, elliptical Walker constellations, and many of Draim’s global coverage constellations. Previous studies have shown FCs can provide improved performance in global navigation over existing Global Navigation Satellite Systems (GNSS). We found a 3D-LFC design that improved the average positioning accuracy by 3.5 % while reducing launch $\varDelta v$ Δ v requirements when compared to the existing Galileo GNSS constellation.     

The effect of secular resonances on the long-term orbital evolution of uncontrollable objects on satellite radio navigation systems in the MEO region

We present the results of the study of long-term orbital evolution of space debris objects, formed from end-of-life space vehicles (SV) of satellite radio navigation systems in the medium Earth orbit (MEO) region. Dynamical features of the evolution of objects in this region have been studied on the basis of 20-year laser surveillance with the Etalon-1 and Etalon-2 satellites and the results of numerical simulation of the long-term evolution of operating and disposal orbits of uncontrolled GLONASS and GPS SVs. It is shown that perturbations from secular lunisolar resonances produce an eccentricity growth for orbits with inclinations chosen for navigation constellations; this significantly changes the positions of these orbits in space and results in the ingress of end-of-life objects into the area of operating SVs.     

Regional positioning using a low Earth orbit satellite constellation

Global and regional satellite navigation systems are constellations orbiting the Earth and transmitting radio signals for determining position and velocity of users around the globe. The state-of-the-art navigation satellite systems are located in medium Earth orbits and geosynchronous Earth orbits and are characterized by high launching, building and maintenance costs. For applications that require only regional coverage, the continuous and global coverage that existing systems provide may be unnecessary. Thus, a nano-satellites-based regional navigation satellite system in Low Earth Orbit (LEO), with significantly reduced launching, building and maintenance costs, can be considered. Thus, this paper is aimed at developing a LEO constellation optimization and design method, using genetic algorithms and gradient-based optimization. The preliminary results of this study include 268 LEO constellations, aimed at regional navigation in an approximately 1000 km \(\times \) 1000 km area centered at the geographic coordinates [30, 30] degrees. The constellations performance is examined using simulations, and the figures of merit include total coverage time, revisit time, and geometric dilution of precision (GDOP) percentiles. The GDOP is a quantity that determines the positioning solution accuracy and solely depends on the spatial geometry of the satellites. Whereas the optimization method takes into account only the Earth’s second zonal harmonic coefficient, the simulations include the Earth’s gravitational field with zonal and tesseral harmonics up to degree 10 and order 10, Solar radiation pressure, drag, and the lunisolar gravitational perturbation.     

基于iHCO通信卫星的CAPS星座优化研究

中国区域定位系统(Chinese Area Positioning System,CAPS)把寿命末期的地球静止轨道(Geostationary Earth Orbit,GEO)通信卫星推到比GEO轨道高约200 km的倾斜高圆轨道(inclined Highly Circular Orbit,iHCO),卫星相对地球向西漂移。利用该类卫星组建CAPS导航星座,可以实现全球范围内的导航通信覆盖。重点开展基于iHCO通信卫星的CAPS星座优化研究,结果表明:利用GEO通信卫星和iHCO通信卫星组成的星座可以实现较好的空间星座布局,可以满足一般导航用户的需要。     

Evolution of Planetesimal Velocities Based on Three-Body Orbital Integrations and Growth of Protoplanets

We obtain the viscous stirring and dynamical friction rates of planetesimals with a Rayleigh distribution of eccentricities and inclinations, using three-body orbital integration and the procedure described by Ohtsuki (1999, Icarus137, 152), who evaluated these rates for ring particles. We find that these rates based on orbital integrations agree quite well with the analytic results of Stewart and Ida (2000, Icarus 143, 28) in high-velocity cases. In low-velocity cases where Kepler shear dominates the relative velocity, however, the three-body calculations show significant deviation from the formulas of Stewart and Ida, who did not investigate the rates for low velocities in detail but just presented a simple interpolation formula between their high-velocity formula and the numerical results for circular orbits. We calculate evolution of root mean square eccentricities and inclinations using the above stirring rates based on orbital integrations, and find excellent agreement with N-body simulations for both one- and two-component systems, even in the low-velocity cases. We derive semi-analytic formulas for the stirring and dynamical friction rates based on our numerical results, and confirm that they reproduce the results of N-body simulations with sufficient accuracy. Using these formulas, we calculate equilibrium velocities of planetesimals with given size distributions. At a stage before the onset of runaway growth of large bodies, the velocity distribution calculated by our new formulas are found to agree quite well with those obtained by using the formulas of Stewart and Ida or Wetherill and Stewart (1993, Icarus106, 190). However, at later stages, we find that the inclinations of small collisional fragments calculated by our new formulas can be much smaller than those calculated by the previously obtained formulas, so that they are more easily accreted by larger bodies in our case. The results essentially support the previous results such as runaway growth of protoplanets, but they could enhance their growth rate by 10-30% after early runaway growth, where those fragments with low random velocities can significantly contribute to rapid growth of runaway bodies.     

卫星跟踪卫星模式中轨道参数需求分析

首次基于半解析法利用GRACE(Gravity Recovery and Climate Experiment)双星K波段星间速度误差、GPS接收机轨道误差和加速度计非保守力误差影响累计大地水准面精度的联合模型开展了卫星跟踪卫星模式中轨道参数的需求分析.建议我国将来首颗重力卫星的平均轨道高度设计为400 km和平均星间距离设计为220 km较优.此研究不仅为我国将来卫星重力测量计划中轨道参数的优化选取以及全球重力场精度的有效和快速估计提供了理论基础和计算保证,同时对将来国际GRACE Follow-On地球重力测量计划和GRAIL(Gravity Recovery and Interior Laboratory)月球重力探测计划的发展方向具有一定的指导意义.     

卫星星座与编队飞行问题综述

卫星应用的日益发展需要由多颗卫星组成的卫星系统(形成各种类型的星座)来替代单颗卫星，这就给卫星轨道力学的应用增加了一些新内容。重点阐述了卫星星座整体结构的演化、卫星星座编队飞行中的星-星相对几何构形及其保持问题，以及星座卫星定轨所涉及的测控方式和天地基网联合定轨问题。这些内容都是卫星星座轨道力学中的重要组成部分。     

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．     

Lissajous trajectories for lunar global positioning and communication systems

This work proposes a Lunar Global Positioning System (LGPS) and a Lunar Global Communication System (LGCS) using two constellations of satellites on Lissajous trajectories around the collinear L ₁ and L ₂ libration points in the Earth–Moon system. This solution is compared against a Walker constellation around the Moon similar to the one used for the Global Positioning System (GPS) on the Earth to evaluate the main differences between the two cases and the advantages of adopting the Lissajous constellations. The problem is first studied using the Circular Restricted Three Body Problem to find out its main features. The study is then repeated with higher fidelity using a four-body model and higher-order reference trajectories to simulate the Earth-Moon-spacecraft dynamics more accurately. The LGPS performance is evaluated for both on-ground and in-flight users, and a visibility study for the LGCS is used to check that communication between opposite sides of the Moon is possible. The total ΔV required for the transfer trajectories from the Earth to the constellations and the trajectory control is calculated. Finally, the estimated propellant consumption and the total number of satellites for the Walker constellation and the Lissajous constellations is used as a performance index to compare the two proposed solutions.     

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.