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1.
《天文学进展》2018,(4)
针对限制性三体问题,分别选取以中心天体和摄动体质心为坐标原点的惯性系,及以中心天体为坐标原点的非惯性系,讨论了不同坐标系下天体运动轨道描述的异同。利用运动天体轨道能量E的大小,可以确定受摄运动方程采用椭圆轨道根数还是采用双曲线轨道根数进行描述。为此,推导出一个关于轨道半长径和偏心率满足的临界关系判别式。结果表明,在摄动天体质量较大的情况下,非惯性系中存在大量轨道,这些轨道在原惯性坐标系中是稳定的椭圆轨道,转换到非惯性系中后却无法用椭圆轨道根数进行描述。只能引入双曲线轨道根数来描述轨道,由此将产生非惯性系下摄动运动方程轨道根数类型选择问题。最后,指出选择雅可比坐标系可以避免上述问题,并推导出适用于任意运动区域的具有统一形式的摄动函数展开式。 相似文献
2.
报道Ｋｅｒｒ黑洞周围一般轨道中,静质量ｍ≠０的束缚粒子短程线的物理性质,根据粒子运动方程用数值计算方法得到了在轨两类粒子的存在判据和料子的轨迹,给出了不同运动 发常数据条件下,粒子一参数的变化规律。 相似文献
3.
在以前研究的基础上继续研究了双星两子星的自转对轨道变化的后牛顿效应，给出自转对轨道产生的长期摄动效应和周期摄动效应。理论结果表明，两子星的自转对轨道半长轴、轨道偏心率、近星点角和平近点经度均产生周期摄动效应，但对前两个轨道根数不产生长期摄动效,人对后两个轨道根数产生长期摄动效应，并利用理论结果对6颗双星系：EK Cep、GT Cep、NY Cep、V448 Cyg和V451 Oph中两子星的自转对轨道产生周期和长期摄动效应做了数值计算，数值结果显示：对于两个质量较大快速自转的双星系，由此产生的后牛顿铲应是不能忽视的。 相似文献
4.
在电离中电感应阻力对带电卫星轨道根数的摄动影响 总被引：2，自引：0，他引：2
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，但除对半生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1500km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
5.
提出一种直接推导摄动运动方程的方法,也就是以矢量的微分运算为工具直接推导二体问题意义下的瞬时椭圆如何在摄动力三分力的作用下轨道根数发生的变化,推导过程几何图像清晰,力学意义明确．特别是对ω、M两根数的推导,比传统的方法更简洁、直观． 相似文献
6.
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
7.
根据Ｋｅｒｒ度规下粒子运动的一般方程,计算黑洞周围一般轨道单色发光环的谱线轮廓,获得了坐标系曳（ＦＤ）的特征。结果表明,原谱线发生分裂,呈现具有伴峰的双主峰轮廓,且随参数变化峰型差异明显;谱线全部发生谱移,计算参数下谱移量为负０．５到１．５;并且应用上述ＦＤ的证据,结合ＭＣＧ－６－３０－１５实际观测结果,讨论了利用发射谱线获得黑洞相关信息的可行性。 相似文献
8.
9.
本文所提出的分离摄动项求解法,是利用小行星在整个轨道上分布的不少于9次的位置测定值,与用该小行星的轨道根数初值计算出的列表位置进行比较,将由太阳系其它天体摄动力对小行星位置、速度的影响进行分离,求解出分点及赤道改正,小行星轨道根数改正,地球轨道根数改正和由摄动力引起的小行星位置和速度改正。这种方法的优点在于:(1)列表位置仅需根据小行星的轨道根数初值计算出,不考虑摄动力的作用,这样可避免小行星运动理论不完善对确定分点和赤道改正的影响;(2)在解算中,可以单独地求出摄动力对小行星运动速度和位置的影响,通过对摄动函数的数值积分,可求得任一时刻的小行星的真位置。 相似文献
10.
卫星轨道预报的一种分析方法 总被引：5，自引：0，他引：5
人造地球卫星的轨道预报是空间环境监测和实时跟踪测量中一个重要环节，由于监测对象众多，要求精度也不太高，通常采用分析法预报．在已有分析法得到t时刻平均根数的基础上给出一种轨道预报方法，由t时刻的平均根数给出该时刻卫星的位置和速度，在此基础上将地球非球形引力摄动的周期项直接用卫星直角坐标的位置和速度分量表示，这样可以避免在计算轨道根数变化的周期项时出现的奇点问题，从而对根数的选择无特殊要求，可适用于各种轨道，简化预报程序和相应的软件，提高预报效率。 相似文献
11.
We study the effects of a non-singular gravitational potential on satellite orbits by deriving the corresponding time rates
of change of its orbital elements. This is achieved by expanding the non-singular potential into power series up to second
order. This series contains three terms, the first been the Newtonian potential and the other two, here R
1 (first order term) and R
2 (second order term), express deviations of the singular potential from the Newtonian. These deviations from the Newtonian
potential are taken as disturbing potential terms in the Lagrange planetary equations that provide the time rates of change
of the orbital elements of a satellite in a non-singular gravitational field. We split these effects into secular, low and
high frequency components and we evaluate them numerically using the low Earth orbiting mission Gravity Recovery and Climate
Experiment (GRACE). We show that the secular effect of the second-order disturbing term R
2 on the perigee and the mean anomaly are 4″.307×10−9/a, and −2″.533×10−15/a, respectively. These effects are far too small and most likely cannot easily be observed with today’s technology. Numerical
evaluation of the low and high frequency effects of the disturbing term R
2 on low Earth orbiters like GRACE are very small and undetectable by current observational means. 相似文献
12.
David Parry Rubincam 《Celestial Mechanics and Dynamical Astronomy》1977,15(1):21-33
The motion of a satellite with negligible mass in the Schwarzschild metric is treated as a problem in Newtonian physics. The relativistic equations of motion are formally identical with those of the Newtonian case of a particle moving in the ordinary inverse-square law field acted upon by a disturbing function which varies asr ?3. Accordingly, the relativistic motion is treated with the methods of celestial mechanics. The disturbing function is expressed in terms of the Keplerian elements of the orbit and substituted into Lagrange's planetary equations. Integration of the equations shows that a typical Earth satellite with small orbital eccentricity is displaced by about 17 cm from its unperturbed position after a single orbit, while the periodic displacement over the orbit reaches a maximum of about 3 cm. Application of the equations to the planet Mercury gives the advance of the perihelion and a total displacement of about 85 km after one orbit, with a maximum periodic displacement of about 13 km. 相似文献
13.
Electromagnetic Radiation and Motion of a Particle 总被引：2，自引：2，他引：0
Jozef Klačka 《Celestial Mechanics and Dynamical Astronomy》2004,89(1):1-61
We consider the motion of uncharged dust grains of arbitrary shape including the effects of electromagnetic radiation and
thermal emission. The resulting relativistically covariant equation of motion is expressed in terms of standard optical parameters.
Explicit expressions for secular changes of osculating orbital elements are derived in detail for the special case of the
Poynting-Robertson effect. Two subcases are considered: (i) central acceleration due to gravity and the radial component of
radiation pressure independent of the particle velocity, (ii) central acceleration given by gravity and the radiation force
as the disturbing force. The latter case yields results which may be compared with secular orbital evolution in terms of orbital
elements for an arbitrarily shaped dust particle. The effects of solar wind are also presented.
This revised version was published online in July 2006 with corrections to the Cover Date. 相似文献
14.
S. A. Gasanov 《Astronomy Letters》2001,27(2):124-133
The plane motion of a mass point inside an inhomogeneous rotating ellipsoidal body with a homothetic density distribution is considered. The force function of the problem is expanded in terms of the ellipsoid's second eccentricities up to the fourth order, which are taken as small parameters. We derive an expression for the perturbing function and solve the equations of perturbed motion in orbital elements. 相似文献
15.
L. Sehnal 《Celestial Mechanics and Dynamical Astronomy》1981,25(2):169-179
The changes of the orbital motion of an artificial satellite caused by the terrestrial infrared radiation pressure are studied. The infrared radiation is described as a series of spherical harmonics and only the zero-th and second-order harmonics and taken into account. The expressions for the disturbing components and for the changes of the orbital elements are given together with numerical examples. The comparison of the computed magnitudes of the disturbing force with observed data shows good agreement. 相似文献
16.
In the first part of the paper the Newtonian analogue of force for the Kerr-de Sitter metric has been investigated. To the first-order of approximation, a component of the force vector corresponds to the Newtonian gravitational force and a cosmic force arising due to the cosmological constant A. Int the higher order of approximation, the relativistic correction terms due to rotation and the presence of A are obtained. In the second part of the paper the motion of a freely-falling body has been investigated. It is found that plane orbits are not possible. Also a radial fall is not possible and there is a rotational drag on the particle which has no Newtonian analogue. 相似文献
17.
David R. Cok 《Celestial Mechanics and Dynamical Astronomy》1977,16(4):459-479
The lunar disturbing function for a close-Earth satellite is expressed as a sum of products of harmonics of the satellite's position and harmonics of the Moon's position, and the latter are expanded about a rotating and precessing elliptic orbit inclined to the ecliptic. The deviations of the Moon from this approximate orbit are computed from Brown's lunar theory andthe perturbations in satellite orbital elements due to these inequalities are derived. Numerical calculations indicate that several perturbations in the position of the satellite's node and perigee have magnitudes on the order of one meter.The author is supported in part by a National Science Foundation Graduate Fellowship. 相似文献
18.
主要阐述近年来在近地小行星轨道演化研究工作中所获得的一些基本结果，即合理的力学模型和相应的有效算法，并以实际预报算例（近地小行星与地球的交会状态）与有关权威性的结果作了比较，证实这些研究结果确实是可信的。在给出的力学模型中，考虑了所有可能影响近地小行星运动的力学因素，包括各大天体和较大的主带小行星的引力作用、有关天体的扁率影响以及源于太阳引力的后牛顿效应。而在计算方法中，合理地处理了变步长问题和月球位置量这种相对而言的快变化问题，使得数值求解一个高维方程组时，对各天体而言，可采用同一步长进行 积分，避免了求解过程中的复杂性。 相似文献
19.
In the present paper, we have discussed the propagation of spherical shock waves in a radiating magnetohydrodynamic rotating interplanetary medium. The effects of force of self-gravitation have been taken into account with the assumption that at the equilibrium position the effects of rotation on the force of gravitation are negligible. The combined effects of rotation and gravitation on the variation of flow variables have been shown in tables. The particular cases of the problem have been discussed and compared by considering effects of rotation and gravitation separately. 相似文献
20.
This paper deals with the perturbations which rotation can produce to the orbital elements of a close binary system. The rectangular components,R, S andW of the disturbing accelerations due to rotation have been substituted to the Gauss form of Lagrange's planetary equations to yield the first order approximation. The results obtained are exact for any value of orbital eccentricity between the values 0<e<1 and for arbitrary inclinations of the rotational axes to the orbital plane.First and second order approximations are given for the special case when equators are coplanar to the orbit. 相似文献