基于解析梯度的近地小天体探测机会搜索问题研究

研究近地小天体的探测机会搜索问题.针对交会型探测任务,通过结合变分理论和状态转移矩阵推导了性能指标关于可调参数的解析偏导数,然后在搜索空间中随机生成初始点,并从这些初始点出发利用解析偏导数寻优,从而得到搜索空间内对应潜在发射机会的全部局部极小值点.此方法既在一定程度上保持了传统搜索方法全局搜索的特点,又克服了传统搜索方法的盲目性,因此计算速度获得很大提高.此外该方法可以对探测机会的搜索精度进行有效地控制.     

用LLR资料解算日月轨道根数

本文推导了激光测月资料归算中测距对地月系轨道根数的偏导数，并对所得偏导数进行了精度估计，利用这些偏导数和１９８８年至１９９２年全球激光测月资料解算了日月轨道根数，得到了比较理想的结果。     

空间碎片光学观测中若干问题研究

<正>地基光学观测是探测空间碎片的重要手段.本文从目标搜索方案的制定、目标质心提取、目标精密定位以及目标关联4方面入手,研究提升设备探测能力、提高目标观测精度的方法.首先,为了满足对GEO(Geosynchronous Orbit,地球同步轨道)空间碎片探测的要求,克服长时间曝光CCD像元饱和溢出的问题,使用多帧连续曝光图像叠加的方法,增加图像的宽容度,同时保证系统的探测能力.实验表明,叠加10帧连续图像,有效消除了像元饱和的情况,提升目标信噪比约3.2倍,提升探测能力约2.5 mag,使用底片常数的均值计算目标位置,精度符合要求.使用星像几何形态检测     

太阳系探索和地外生命搜索

综述了国际上进行太阳系空间探测的现状，着重介绍了探测月球，火星，不星和外行星的意义，目的，手段和成就，择要介绍了美国宇般局，欧洲空间局，俄罗斯和日本近年来和下世纪初的空间计划，论及地外生命搜索，主要介绍了火星上水和生命搜索进展，地外生命搜索的的SETI计划及其发民菜，物理学家与生物学家有关搜索成功的可能性的争论，以及太阳系外行星系统的发现，太阳系外行星系统的发现是当代天文学最时髦的，也将是未来21世纪成果最丰富的研究领域之一，目前，已经发现了大约50个太阳系外行星系统，太阳系外行星系统的发现与地外生命搜索研究是密不可分的，这项研究近20年来发展较快，它的研究也促进了航天学，宇宙化学，天文生物学乃至哲学等其化学科的发展。     

日珥线光谱的降维法分析

本文提出了多搜索变量的目标函数直接优化法。该方法不涉及目标函数的导数计算,通用性强;同时该方法可控制搜索变量在值域内取值,这在一定程度上保证了解的可靠性。用此方法,本文分析了1984年2月18日太阳边缘环珥的一些Hα谱线,结果表明,本文方法具有收敛半径大,精度高的特点。     

今后几年的月球探测和月球科学

近年来月球探测已经进入了一个全新的时代。特别是 1 990年以来 ,多个月球探测计划已经被成功实现 ,而且另外还有多个探测计划也在准备当中 ,并将在未来的几年内发射升空。在这种背景之下 ,中国的航天机构和有关的科学家也开始积极酝酿和开发自己的月球探测计划。这些月球探测计划将利用卫星上搭载的各种仪器探测和测量月球的地质和地理特性、化学成分和矿物组成、月球物理学特征以及包含地球大气在内的地月空间环境和行星际空间环境 ;进一步研究月球的起源和演化 ,探明月面环境 ,研究太阳等离子体物理 ,提供月面天文台和月面长期科研基地的候选地址 ,调查月球上的可利用资源 ,为将来开发月球提供充实的背景资料。参与新一轮的月球探测同样也为中国天文学研究带来了新的机会。     

基于天籁射电阵的空间目标探测与测向方法研究

天籁计划射电望远镜阵列(简称天籁射电阵)具有大视场与高灵敏度的双重优势,既可以在观测时探测到尺寸较小的空间目标,也能在同一时刻探测到多个空间目标,具有较强的空间目标探测能力,因此可作为空间目标监测设备之一。以曲靖非相干散射雷达作为发射源,对天籁射电阵的空间目标探测能力进行计算。随后提出了可用于该系统的基于相位差测量法的空间目标测向方法,并研究了测向误差与测向角度之间的关系。     

今后几年的月球探测和月球科学

近年来月球探测已经进入了一个全新的时代。特别是1990年以来，多个月球探测计划已经被成功实现，而且另外还有多个探测计划也在准备当中，并将在未来的几年内发射升空。在这种背景之下，中国的航天机构和有关的科学家也开始积极酝酿和开发自己的月球探测计划。这些月球探测计划将利用卫星上搭载的各种仪器探测和测量月球的地质和地理特性、化学成分和矿物组成、月球物理学特征以及包含地球大气在内的地月空间环境和行星际空间环境；进一步研究月球的起源和演化，探明月面环境，研究太阳等离子体物理，提供月面天文台和月面长期科研基地的候选地址，调查月球上的可利用资源，为将来开发月球提供充实的背景资料。参与新一轮的月球探测同样也为中国天文学研究带来了新的机会。     

基于调频广播信号的空间碎片探测方法

空间碎片对人造卫星和飞船的威胁日益增长.为了保持一个安全的空间环境,需要寻找成本低而又准确的空间天体探测和追踪方法.前些年,使用射电望远镜作为被动雷达,探测空间碎片反射的调频广播信号的可能性已经被讨论过,并且月球和国际空间站反射的信号已经被默奇森大视场射电阵(MWA)探测到.介绍MWA探测到的卫星反射广播信号事件,论证MWA有能力探测600 km高度处0.1 m量级大小的空间碎片,位置误差在10 km左右.     

空间碎片激光测距探测能力分析

针对利用激光测距技术探测空间碎片这一新的发展趋势,基于国内外现状和未来探测的需求,首先对空间碎片激光测距的探测成功率进行了理论计算;其次计算分析了望远镜口径大小、激光器单脉冲能量及重复频率与可探测空间碎片大小及探测距离之间的关系。研究结果表明,采用大功率激光器与大口径望远镜可有效地提高空间碎片的探测能力。为满足探测微小空间碎片(尺寸在20 cm左右)的需要,建议采用能量在2 J~3 J之间、重复频率为100 Hz的激光器和口径1.2 m以上的望远镜。     

Exploration Opportunity Search of Near-earth Objects Based on Analytical Gradients

The problem of search of opportunity for the exploration of near-earth minor objects is investigated. For rendezvous missions, the analytical gradients of the performance index with respect to the free parameters are derived using the variational calculus and the theory of state-transition matrix. After generating randomly some initial guesses in the search space, the performance index is optimized, guided by the analytical gradients, leading to the local minimum points representing the potential launch opportunities. This method not only keeps the global-search property of the traditional method, but also avoids the blindness in the latter, thereby increasing greatly the computing speed. Furthermore, with this method, the searching precision could be controlled effectively.     

Optimization of Low-Thrust Trajectories Using an Indirect Shooting Method without Guesses of Initial Costates

According to the optimal control theory, the optimal control problem of the low-thrust tra jectory can be converted into a solution of nonlinear two- point boundary-value problem (TPBVP). To solve the TPBVP, the repeated random guesses for the initial costate variables and iterative computations are needed. In order to enhance the convergence of the iterations, we select an appropriate performance index, and then linearize the equations of the TPBVP around a Keplerian orbit. For multi-revolution transfers, instead of the multi- revolution Lambert tra jectory, multiple segmented Keplerian arcs are used to ensure the effectiveness of the linearization. The method is totally automatic with multiple iterations. With this method, we can get the results within 3 ∼ 5 iterations, and the random guess of the initial costates is unnecessary. Finally by the iterative optimization of the performance index, a better control strategy approaching to the bang-bang control is obtained.     

无需初值猜测的间接法小推力轨道设计

在间接法求解小推力轨道计算中,通过先选取合适的性能指标,并对小推力最优控制问题转化为两点边值问题的方程在开普勒轨道附近线性展开,有效增强了协态变量初值收敛性,使得该方法无需对协态变量初值进行反复的随机猜测,迭代过程也不需要人工干预,提高了轨道搜索应用中的计算效率.之后再对性能指标进行迭代优化,可获得逼近于Bang-bang控制的控制方案.     

Fast Earth–Moon transfers with ballistic capture

This contribution deals with fast Earth–Moon transfers with ballistic capture in the patched three-body model. We compute ensembles of preliminary solutions using a model that takes into account the relative inclination of the orbital planes of the primaries. The ballistic capture orbits around the Moon are obtained relying on the hyperbolic invariant structures associated to the collinear Lagrangian points of the Earth–Moon system, and the Sun–Earth system portion of the transfers are quasi-periodic orbits obtained by a genetic algorithm. The trajectories are designed to be good initial guesses to search optimal cost-efficient short-time Earth–Moon transfers with ballistic capture in more realistic models.     

The solution of Kepler's equation,III

Recently proposed methods of iteration and initial guesses are discussed, including the method of Laguerre-Conway. Tactics for a more refined initial guess for use with universal variables over a small time interval are described.     

Analytical design methods for transfer trajectories between the Earth and the Lunar Orbital Station

Lunar Orbital Station (LOS) is proposed as support of manned lunar exploration missions. A fast-converging iteration method for determining the initial conditions of two-impulse transfer trajectories between the Earth and the LOS is proposed based on the patched conic approach. In the Earth phase, near Earth state is connected with the state at the lunar sphere of influence (LSOI) based on the relationship between the initial and terminal orbital state. Then, an analytical algorithm is proposed to find the state vector at LSOI, such to satisfy the LOS orbital constraint. An iterative process is finally adopted to generate favorable initial solutions that satisfy the constraint near the Earth and at the perilune. The algorithm convergence is investigated, and two types of transfer trajectories are found for both Earth-LOS and LOS-Earth transfer. Based on the algorithm, orbital transfer windows, velocity impulse and time of flight are analyzed in the typical years 2025 and 2034. At last, the initial solution is corrected with a high fidelity model based on the active-set method, which shows the precision of this algorithm. The novel procedure for the transfer trajectories design and the analytic result can be used as a basis for rapid mission evaluation and design for future manned lunar missions based on the LOS.     

The low-frequency radio spectrum of the continuum emission from the undisturbed sun

The low-frequency radio spectrum of the continuum emission from the undisturbed Sun is determined for 24 days during the period 1985 May-September. It is found that the spectral index varied from + 1.6 to +3.6 during this period. It is suggested that the large positive spectral indices are due to the existence of temperature gradients in the outer corona.     

An efficient computational algorithm for the initial value problem associated with the universal Y functions

In the present paper, an efficient iterative method of arbitrary integer order of convergent ≥2 based on the homotopy continuation techniques for the solution of the initial value problem of space dynamics using the universal Y functions is presented. The method is of dynamic nature in the sense that, ongoing from one iterative scheme to the subsequent one, only additional instruction is needed. Most importantly, the method does not need any prior knowledge of the initial guess. This is a property which avoids the critical situations between divergent to very slow convergent solutions that may exist in other numerical methods which depend on initial guesses. A computational package for digital implementation of the method is given, together with numerical applications for elliptic, hyperbolic, and parabolic orbits. The accuracy of the results for all orbits is O(10^–16). (© 2016 WILEY‐VCH Verlag GmbH & Co. KGaA, Weinheim)     

基于粒子群优化的LAMOST初始波长定标方法

大天区面积多目标光纤光谱天文望远镜(Large Sky Area Multi-Object Fiber Spectroscopic Telescope,LAMOST)初始波长定标操作,对于在先验定标系数附近搜索解空间内的每一点,通过插值法生成对应定标系数下的虚拟定标灯谱,再将生成的虚拟定标灯谱与实测定标灯谱作互相关运算,使得相关系数最大时对应的定标系数即为初始定标结果,其实质是一个多参数寻优问题.粒子群优化是一种基于群体智能的随机全局优化算法,具有实现简单、精度高、收敛快的特点.鉴于粒子群优化的优异性能,提出一种基于粒子群优化的LAMOST初始波长定标方法,并设计相应算法和测试实验.实验结果表明,基于粒子群优化的LAMOST初始波长定标在收敛性、解的质量、运行时间等方面都优于基于改进遗传算法参数寻优方法.     

The analytical solution of the Stellar Interior Equations for approximating stellar and protostellar structure

This work presents an analytical solution of the Stellar Interior Equations (SIE) in order to approximate the structure of a star. Herein we model the gradients of mass, pressure, temperature, and luminosity for a Main-Sequence star, such as the Sun. Also presented is an analytical method for approximating the hydrostatic core of a protostellar structure. The methods derive, dimensionless variables from the SIE which are then used to solve linearly approximate equation, which are expanded about an initial point. The results are in good agreement with standard computer studies in existence (at least for the present Main-Sequence Sun).Paper presented at the Second International Conference on Industrial and Applied Mathematics, July 8–12, 1991, Washington, D.C., U.S.A.