共查询到19条相似文献，搜索用时 0 毫秒
1.
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
2.
研究了地球磁场对带电的非赤道卫星的轨道根数的摄动影响。理论结果表明，地球磁场对带电卫星的轨道半长轴没有摄动影响，既无周期摄动，也无长期摄动，但对轨道偏心率、轨道倾角、升交点赤经、近地点经度和历元平近点角均有周期摄动，且对升交点和近地点经度还有长期摄动效应。通过算例表明，当卫星带有大量电荷时，地球磁场对卫星轨道的摄动影响必须加以考虑。 相似文献
3.
地球磁场对带电人造卫星轨道根数的摄动影响 总被引：2，自引：0，他引：2
研究了地球磁场对带电的非赤道卫星的轨道根数的摄动影响，理论结果表明，地球磁场对带电卫星的轨道半长轴没有摄动影响，既无周期摄动，也无长期摄动，但对轨道偏心率、轨道倾角、升交点赤经、近地点经度和历元平近点角均有周期摄动，且对升交点和近地点经度还有长期摄动效应，通过算例表明，当卫星带有大量电菏时，地球磁场对卫星轨道的摄动影响必须加以考虑。 相似文献
4.
用功能转换原理和摄动理论的两种方法重点研究了导体卫星在地球磁场和有电导率介质空间飞行时磁感应阻力对圆形轨道半径的摄动影响。理论研究表明：导体卫星在圆形轨道上受磁感应阻力后轨道半径有随时间变化的长期摄动效应外还有周期性变化。此外，文中还讨论了磁感应阻力对圆形轨道的其它要素的摄动影响概况。 相似文献
5.
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
6.
韩韬 《紫金山天文台台刊》1994,13(1):18-22
根据后牛顿方法,得到了自转因素产生的轨道根数的参数化后牛顿效应。这种效应对轨道根数a、e、i、M没有长期摄动,只对ωΩ产生长期摄动,并且对所有轨道根数不产生长周期摄动,只产生短周期摄动。 相似文献
7.
研究了双星多方模型的形状对同步子星轨道要素的摄动影响，假定两子星在同一轨道面上运动，推出了主星对伴星的轨道要素的摄动量，理论结果表明，双星多方模型对轨道半长轴和偏心率只有周期项摄动，无长期摄动，但对近星点和历元平近点角除有周期摄动外还有长期摄动效应。文中将理论结果应用于同步双星βＰｅｒ（大陵五双星）的计算上，除计算了两个子星的形状（椭率）外对同步子星的轨道要素变化的周期项振幅和长期项的效应做了数值 相似文献
8.
从计及J2项的地球重力场度规出发，我们导出在这样的度规场中人造卫星的摄动加速度及在径向、横向和轨道面法向等方面的摄动函数，进而计算了轨道一阶导数的平均值，讨论了在这种重力场中卫星的轨道特性。其主要结论是：1、球形地球的广义相对论摄动仅对近地点角距ω和平近点角τ产生长期项，而地球J2项的广义相对论效应不仅对这两个根数有长期摄动，而且对升效点角距Ω出有长期摄动。值得注意的是这两种广义相对论效应对半长轴a，偏心率e及倾角i都没有长期摄动；2、球形地球的广义相对论效应对倾角i和升交点角距Ω仅有短周期摄动，但地球J2项的广义相对论效应除了对它们有短周期摄动外，还有长周期摄动，对Ω甚至还有长期摄动。 相似文献
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10.
研究了双星多方模型的形状对同步子星轨道要素的摄动影响。假定两子星在同一轨道面上运动，推出了主星对伴星的轨道要素的摄动量。理论结果表明：双星多方模型对轨道半长轴和偏心率只有周期项摄动，无长期摄动，但对近星点和历元平近点角除有周期摄动外还有长期摄动效应。文中将理论结果应用于同步双星βＰｅｒ（大陵五双星）的计算上。除计算了两个子星的形状（椭率）外对同步子星的轨道要素变化的周期项振幅和长期项的效应做了数值计算 相似文献
11.
Lin-Sen Li 《Journal of Astrophysics and Astronomy》2014,35(2):189-200
The influence of the gravitational radiation damping on the evolution of the orbital elements of compact binary stars is examined by using the method of perturbation. The perturbation equations with the true anomaly as an independent variable are given. This effect results in both the secular and periodic variation of the semi-major axis, the eccentricity, the mean longitude at the epoch and the mean longitude. However, the longitude of periastron exhibits no secular variation, but only periodic variation. The effect of secular variation of the orbit would lead to collapse of the system of binary stars. The deduced formulae are applied to the calculation of secular variation of the orbital elements for three compact binary stars: PSR19 13 + 16, PSR J0737-3039 and M33X-7. The results obtained are discussed. 相似文献
12.
Lin-Sen Li 《Astrophysics and Space Science》2012,340(2):323-330
Perturbative post-Newtonian variations of the standard osculating orbital elements are obtained by using the two-body equations of motion in the parameterized post-Newtonian theoretical framework. The results obtained are applied to the Einstein and Brans–Dicke theories. As a results, the semi-major axis and eccentricity exhibit periodic variation, but no secular changes. The longitude of periastron and mean longitude at epoch experience both secular and periodic shifts. The post-Newtonian effects are calculated and discussed for six extrasolar planets. 相似文献
13.
将作者在变质量天体力学所得理论结果应用于太阳质量损失对流星群轨道根数变化的长期效应上。太阳质量损失包括光子辐射和太阳风造成的质量损失。利用G—M型变质量天体轨道根数变化方程的一阶和二阶解对15个流星群轨道半长轴、近日点距离、轨道周期和近日点经度因太阳质量损失造成的每世纪的长期改变效应做了数值计算,并得出计算结果。其计算结果表明,太阳质量损失使流星群轨道半长轴每世纪的改变效应较明显,它们同太阳距离的扩大影响值得关注,但对轨道周期的拉长每世纪的影响甚小,对近日点经度只有量级变化小到可以略而不计。 相似文献
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给出了以偏近点角为自变量的变引力常数的摄动方程组的解.解包括轨道半长轴的长期和周期变化项,其他轨道根数在一阶解中无长期项,只有周期项.近星点经度和平经度在二阶解中显示长期项变化.给出了由于引力常数变化对双星轨道演变情况的数值估计,对结果做了讨论并给出结论. 相似文献
16.
S. Šegan 《Celestial Mechanics and Dynamical Astronomy》1987,41(1-4):381-388
An analytical interpretation of the satellite orbital element perturbations under influence of a drag has been developed. Some useful formulae for the perturbations of the semi-major axis are given. The agreement with observed values is very good. 相似文献
17.
A second order atmospheric drag theory based on the usage of TD88 model is constructed. It is developed to the second order
in terms of TD88 small parameters K
n,j
. The short periodic perturbations, of all orbital elements, are evaluated. The secular perturbations of the semi-major axis
and of the eccentricity are obtained. The theory is applied to determine the lifetime of the satellites ROHINI (1980 62A),
and to predict the lifetime of the microsatellite MIMOSA. The secular perturbations of the nodal longitude and of the argument
of perigee due to the Earth’s gravity are taken into account up to the second order in Earth’s oblateness. 相似文献
18.
Xavier James Raj 《Planetary and Space Science》2009,57(11):1312-1320
A new non-singular analytical theory for the motion of near-Earth satellite orbits with the air drag effect is developed in terms of uniformly regular KS canonical elements. Diurnally varying oblate atmosphere is considered with variation in density scale height dependent on altitude. The series expansion method is utilized to generate the analytical solutions and terms up to fourth-order terms in eccentricity and c (a small parameter dependent on the flattening of the atmosphere) are retained. Only two of the nine equations are solved analytically to compute the state vector and change in energy at the end of each revolution, due to symmetry in the equations of motion. The important drag perturbed orbital parameters: semi-major axis and eccentricity are obtained up to 500 revolutions, with the present analytical theory and by numerical integration over a wide range of perigee height, eccentricity and inclination. The differences between the two are found to be very less. A comparison between the theories generated with terms up to third- and fourth-order terms in c and e shows an improvement in the computation of the orbital parameters semi-major axis and eccentricity, up to 9%. The theory can be effectively used for the re-entry of the near-Earth objects, which mainly decay due to atmospheric drag. 相似文献
19.
The theory of velocity dependent inertial induction, based upon extended Mach’s principle, has been able to generate many interesting results related to celestial mechanics and cosmological problems. Because of the extremely minute magnitude of the effect its presence can be detected through the motion of accurately observed bodies like Earth satellites. LAGEOS I and II are medium altitude satellites with nearly circular orbits. The motions of these satellites are accurately recorded and the past data of a few decades help to test many theories including the general theory of relativity. Therefore, it is hoped that the effect of the Earth’s inertial induction can have any detectable effect on the motion of these satellites. It is established that the semi-major axis of LAGEOS I is decreasing at the rate of 1.3 mm/d. As the atmospheric drag is negligible at that altitude, a proper explanation of the secular change has been wanting, and, therefore, this paper examines the effect of the Earth’s inertial induction effect on LAGEOS I. Past researches have established that Yarkovsky thermal drag, charged and neutral particle drag might be the possible mechanisms for this orbital decay. Inertial induction is found to generate a perturbing force that results in 0.33 mm/d decay of the semi major axis. Some other changes are also predicted and the phenomenon also helps to explain the observed changes in the orbits of a few other satellites. The results indicate the feasibility of the theory of inertial induction i.e. the dynamic gravitation phenomenon of the Earth on its satellites as a possible partial cause for orbital decay. 相似文献