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空间目标探测和编目是航天器安全的重要课题, 空间目标数量巨大, 造成轨道计算的工作量十分繁重. 分析方法虽然计算速度快, 却不能适应高精度观测资料的处理工作, 因而数值方法将成为目标轨道计算的重要方法. 空间目标编目工作普遍涉及密集星历的产生和计算问题, 针对这一问题的大偏心率轨道数值计算目前尚未形成兼具计算精度和计算效率的有效技术手段, 难以满足编目工作的处理要求. 在此背景下, 提出一种适用于大偏心率轨道密集星历精密计算的快速处理方法, 并通过数值实验对模型参数进行优选, 最后通过计算实例证实了该计算方案的优越性. 相似文献
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已知e或a的先验值的初轨迭代算法 总被引：1，自引：0，他引：1
本文讨论由短弧测角资料,已知偏心率ｅ 或半长轴ａ 的先验值时,初轨的迭代算法。某根数的先验值可看作是对该根数的具有一定精度的观测量,在加权残差平方和达到极小意义下,本文导出了最小二乘估计的迭代算法。仿真结果显示,周期的估计精度主要取决于偏心率先验值的精度;当ｅ 足够小时,可用园轨道计算的ａ′作为ａ 的先验值,定出的初轨有较高精度。 相似文献
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RKNF方法和大偏心率轨道数值积分 总被引：1，自引：0，他引：1
本文比较在建立中等和大偏心率轨道的精密数值历表时几种数值方法的计算效率,特别推荐国内轨道工作中尚未见使用的直接积分２ 阶微分方程的ＲＫＮＦ 方法。数值实算表明,在方程右函数显含速度和中等或大偏心率轨道情况下,嵌套的７ 阶方法ＲＫＮＦ７８ 是一个普适性好、效率高、程序设计简单的方法。 相似文献
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在小天体深空探测任务中,经常需要调用力模型较完备的精确小天体数值历表,然而由于部分小天体可能有较大的轨道偏心率以及存在近距离飞越大行星的可能,导致传统的等区间分段切比雪夫多项式插值方法不适用于构建这些小天体的数值历表.在传统方法基础上采用结合误差自适应的二分法对原始轨道进行分段,并采用二叉树结构来组织所有的分段区间,能解决历表读取中的系数反查问题.以大偏心率近地小行星4179 Toutatis和3200 Phaethon、大偏心率彗星2P/Encke以及将近距离飞越地球的99942 Apophis小行星为例,通过数值仿真证实了该算法的有效性.由于该方法没有对小天体的轨道性质做任何要求,因此能够作为构建太阳系小天体数值历表的通用方法,可应用于大量目标小天体的精确轨道设计中. 相似文献
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Lin Liu 《Chinese Astronomy and Astrophysics》1997,21(4):488-500
With the aim of analyzing the errors in the radial position of satellites, we give in this paper the expressions for the radial perturbation which include the complete zeroth- and first-order terms in the orbital eccentricity. A simpler and faster method of calculating the perturbation is given. 相似文献
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By linear perturbation theory, a sensitivity study is presented to calculate the contribution of the Mars gravity field to the orbital perturbations in velocity for spacecrafts in both low eccentricity Mars orbits and high eccentricity orbits(HEOs). In order to improve the solution of some low degree/order gravity coefficients, a method of choosing an appropriate semimajor axis is often used to calculate an expected orbital resonance, which will significantly amplify the magnitude of the position and velocity perturbations produced by certain gravity coefficients. We can then assess to what degree/order gravity coefficients can be recovered from the tracking data of the spacecraft. However, this existing method can only be applied to a low eccentricity orbit, and is not valid for an HEO. A new approach to choosing an appropriate semimajor axis is proposed here to analyze an orbital resonance. This approach can be applied to both low eccentricity orbits and HEOs. This small adjustment in the semimajor axis can improve the precision of gravity field coefficients and does not affect other scientific objectives. 相似文献
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卫星径向位置摄动计算中的几个问题 总被引：1，自引：0，他引：1
为了对卫星轨道径向位置误差进行分析，本文将给出由地球非球形引力位（包括潮汐形变）引起的卫星径向位置摄动表达式，它将同时包含完整的卫星轨道偏心率的0阶和1阶项，并给出径向位置摄动空间分布的一种简单计算方法，它可明显地节省计算机时． 相似文献
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偏心率是描述天体运动轨道的重要参数之一, 能够为揭示天体的动力学演化提供重要线索, 进而帮助理解天体形成与演化的过程及背后的物理机制. 随着天文观测技术的不断发展, 人们对于天体运动轨道的研究已经走出太阳系, 包含的系统也从大质量端的恒星系统延伸到了低质量端的行星系统. 聚焦天体轨道偏心率研究, 回顾了目前在恒星系统(包括主序恒星、褐矮星以及致密星)和行星系统(包括太阳系外巨行星以及``超级地球''、``亚海王星''等小质量系外行星)方面取得的进展, 总结了不同尺度结构下偏心率研究的一些共同之处和待解决的问题. 并结合当下和未来的相关天文观测设备和项目, 对未来天体轨道偏心率方面的研究工作进行了展望. 相似文献
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The method applied since 1996 for the analysis of the orbital residuals of the LAGEOS satellites in order to measure the Lense-Thirring effect has been the subject of the present work. This method, based on the difference between the orbital elements of consecutive arcs, is explained and analysed also from the analytical point of view. It is proved that this “difference method” works well for the determination of the secular effects, as in the case of the relativistic precession induced by the Earth's angular momentum, but also very useful for the determination and study of the long-term periodic effects. Indeed, the only limitation in the determination of the periodic effects is the possibility of the reduction of their amplitude by a factor which depends from the periodicity of the given perturbation and from the orbital arc length chosen for the satellite during the data analysis. In the case of the Yarkovsky-Schach effect, the main non-gravitational perturbation seen in the LAGEOS satellites orbital residuals, in particular in its perigee rate and eccentricity vector excitation residuals, we show that the “difference method” is quite good also for the determination of the long-period perturbations induced by this subtle non-conservative force. 相似文献
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Hugh R. A. Jones R. Paul Butler C. G. Tinney Geoffrey W. Marcy Brad D. Carter Alan J. Penny Chris McCarthy Jeremy Bailey 《Monthly notices of the Royal Astronomical Society》2006,369(1):249-256
We report Doppler measurements of the stars HD 187085 and HD 20782 which indicate two high eccentricity low-mass companions to the stars. We find HD 187085 has a Jupiter-mass companion with a ∼1000-d orbit. Our formal 'best-fitting' solution suggests an eccentricity of 0.47, however, it does not sample the periastron passage of the companion and we find that orbital solutions with eccentricities between 0.1 and 0.8 give only slightly poorer fits (based on rms and χ2 ν ) and are thus plausible. Observations made during periastron passage in 2007 June should allow for the reliable determination of the orbital eccentricity for the companion to HD 187085. Our data set for HD 20782 does sample periastron and so the orbit for its companion can be more reliably determined. We find the companion to HD 20782 has M sin i = 1.77 ± 0.22 M Jup , an orbital period of 595.86 ± 0.03 d and an orbit with an eccentricity of 0.92 ± 0.03. The detection of such high-eccentricity (and relatively low-velocity amplitude) exoplanets appears to be facilitated by the long-term precision of the Anglo-Australian Planet Search. Looking at exoplanet detections as a whole, we find that those with higher eccentricity seem to have relatively higher velocity amplitudes indicating higher mass planets and/or an observational bias against the detection of high-eccentricity systems. 相似文献
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研究了在高空电离层中运动的带电荷的卫星受电感应阻力后对轨道根数产生的摄动影响。研究结果表明 ,电感应阻力对带电卫星的轨道半长轴、轨道偏心率、近地点赤经、历元平赤经均有周期摄动影响 ,但除对半长轴有长期摄动效应外对其它轨道根数均无长期摄动。轨道倾角和升交点赤经不受摄动影响。文中以飞行在高度 1 50 0km的电离层中的导体卫星作为算例。计算结果显示 :带电导体卫星在高空电离层中带有一定电量时电感应阻力对轨道半长轴的缩短产生显著效应 相似文献
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A method of realtime autonomous orbit determination for earth satellites using the extended Kalman filtering is proposed. The observed quantities are: the satellite-sun direction vector measured by a sun sensor, the satellite-earth and satellite-moon direction vectors measured by an ultraviolet sensor, and the geocentric distance measured by a radar altimeter. At the same time the satellite attitude to the earth is also determined. Results of our simulation of the autonomous orbit determination show that the precision of the orbit determinations is better than 200 m. The effects of the sampling period, orbital inclination, orbital eccentricity and orbital altitude on the precision of orbit determination are analyzed and compared, and certain principles helpful for improving the precision of orbit determination are suggested. 相似文献
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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 相似文献