共查询到19条相似文献，搜索用时 156 毫秒
1.
为了对卫星轨道径向位置误差进行分析，本文将给出由地球北球形引力位引起的卫星径向摄动表达式。它将同时包含完整的卫星轨道道偏心率的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
2.
本文提出一种近地卫星联合摄动的计算方法,给出近地卫星轨道在地球形状摄动和大气阻力摄动同量级时的计算公式。它适用于近地点地面高度在160公里≤z_0≤250公里,轨道偏心率在0≤e≤0.01的近地卫星。 相似文献
3.
本文提出一种有效的半分析方法,给出近地卫星轨道在地球形状摄动和大气阻力摄动同样显著情况下的一阶解,相应的计算公式并不复杂,而计算速度要比数值方法快。 相似文献
4.
《大气一号》气球卫星轨道倾角变化分析 总被引：1，自引：0，他引：1
引起《大气一号》两颗气球卫星（ＤＱ－１Ａ和ＤＱ－１Ｂ）轨道倾角变化的摄动因素主要是太阳光压摄动、大气旋转和日月引力摄动。太阳光压摄动引起气球卫星轨道倾角增大，平均每天变化约０．００１７，大气旋转引起轨道倾角减小，平均每天变化不到０．０００１，但随着高度下降，变化量亦增大，陨落前达０．００２。本文根据卫星轨道摄动理论，给出气球卫星轨道倾角变化的一种定量分析方法，得到的分析结果为：（１）由太阳光压摄动 相似文献
5.
即使静止、同步卫星有着标称位置，但由于各种摄动的存在会使卫星轨道发生漂移．而在许多应用中，例如高精度时间同步，必须精确知道卫星的轨道．另外，由于很少为时间传递、时间同步发射专用卫星，所以它通常使用以其他目的为基本任务的卫星，如气象卫星、通信广播卫星等．以往，这些卫星的轨道信息总是由卫星主管部门给出，在这种情况下，卫星的轨道确定不可能专门考虑第二目的．为此，应用部门为了满足自己的需要，在不影响卫星基本功能条件下，采用闭路动态技术来精确确定卫星的轨道．本文在简要叙述闭路动态卫星定轨原理的基础上，探讨了利用卫星彩色电视副载波信号测速进行同步卫星定轨的可能性．并给出单台站的某些试验测量结果． 相似文献
6.
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
7.
8.
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
9.
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
10.
中高轨卫星广播星历精度分析 总被引：17，自引：0，他引：17
GPS广播星历参数具有物理意义明确、参数少、精度高等优点,可以考虑将它应用于其他卫星导航系统。但是GPS系统的卫星构成比较单一,而其他卫星导航系统可能包含中地球轨道 (MEO)、倾斜地球同步轨道(IGSO)和地球静止轨道(GEO)等多种不同类型的中高轨卫星。分析了采用GPS广播星历参数时,MEO、IGSO和GEO卫星的广播星历拟合精度,特别讨论了轨道倾角接近于0的GEO卫星的广播星历拟合精度,并给出了相应的改进措施。计算表明,对于 MEO卫星,2 h的广播星历拟合精度(三维位置)可达厘米级;对于IGSO卫星和轨道倾角较大的GEO卫星,4 h的广播星历拟合精度约为0．1 m,径向位置误差在厘米量级;而对于轨道倾角接近于0的GEO卫星,若不采取特殊措施,由于轨道倾角和升交点经度统计相关,其广播星历拟合精度很差,为此提出了一种坐标转换方法。采用此方法后的广播星历拟合精度可达0．1 m,径向位置误差为厘米量级。 相似文献
11.
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
12.
In view of the scheduled satellite mission EXOSAT (European X-Ray Observatory Satellite) of ESA (European Space Agency) the lunar occultation technique to determine the position of point-like X-ray sources is investigated. An error analysis for the source coordinates resulting from this technique is presented and an occultation strategy is proposed to achieve optimum lunar occultations. The analysis takes into account the errors of the space coordinates of the satellite and the Moon, the unevenness of the lunar surface, the intensities of source and background, the apparent angular velocity of the Moon as seen from the satellite, the finite sizes of the preoccultation position error boxes of the X-ray sources and the inaccuracies in the satellite orbit correction manoeuvres necessary to achieve the occultations. 相似文献
13.
Some aspects for efficient computation of the tidal perturbation due to the ellipticity effects of the Earth, the luni-solar potential on an Earth-orbiting satellite and the perturbations of the satellite's radial, transverse and normal position components due to the effects of the Earth's gravitational and ocean tide fields are presented. A straightforward method for computing the spectrum of the geopotential and the tidal-induced perturbations of the orbit elements and the radial, transverse and normal components is described. 相似文献
14.
This paper argues that the Milky Way galaxy is probably the largest member of the Local Group. The evidence comes from estimates of the total mass of the Andromeda galaxy (M31) derived from the three-dimensional positions and radial velocities of its satellite galaxies, as well as the projected positions and radial velocities of its distant globular clusters and planetary nebulae. The available data set comprises 10 satellite galaxies, 17 distant globular clusters and nine halo planetary nebulae with radial velocities. We find that the halo of Andromeda has a mass of together with a scalelength of 90 kpc and a predominantly isotropic velocity distribution. For comparison, our earlier estimate for the Milky Way halo is Although the error bars are admittedly large, this suggests that the total mass of M31 is probably less than that of the Milky Way . We verify the robustness of our results to changes in the modelling assumptions and to errors caused by the small size and incompleteness of the data set.
Our surprising claim can be checked in several ways in the near future. The numbers of satellite galaxies, planetary nebulae and globular clusters with radial velocities can be increased by ground-based spectroscopy, while the proper motions of the companion galaxies and the unresolved cores of the globular clusters can be measured using the astrometric satellites Space Interferometry Mission ( SIM ) and Global Astrometric Interferometer for Astrophysics ( GAIA ). Using 100 globular clusters at projected radii 20 R 50 kpc with both radial velocities and proper motions, it will be possible to estimate the mass within 50 kpc to an accuracy of 20 per cent. Measuring the proper motions of the companion galaxies with SIM and GAIA will reduce the uncertainty in the total mass caused by the small size of the data set to 22 per cent. 相似文献
Our surprising claim can be checked in several ways in the near future. The numbers of satellite galaxies, planetary nebulae and globular clusters with radial velocities can be increased by ground-based spectroscopy, while the proper motions of the companion galaxies and the unresolved cores of the globular clusters can be measured using the astrometric satellites Space Interferometry Mission ( SIM ) and Global Astrometric Interferometer for Astrophysics ( GAIA ). Using 100 globular clusters at projected radii 20 R 50 kpc with both radial velocities and proper motions, it will be possible to estimate the mass within 50 kpc to an accuracy of 20 per cent. Measuring the proper motions of the companion galaxies with SIM and GAIA will reduce the uncertainty in the total mass caused by the small size of the data set to 22 per cent. 相似文献
15.
Stefano Casotto 《Celestial Mechanics and Dynamical Astronomy》1993,55(3):223-241
Kaula's celebrated solution to the problem of satellite motion in the gravitational field of a rigid body is transformed to give the perturbation spectra in both position and velocity in the radial, transverse and normal directions of the orbital reference frame. This work is an extension and a refinement of the theory of orbital perturbations due to the geopotential previously published by Rosborough and Tapley (1987). 相似文献
16.
We define combinations of dual‐ and single‐satellite crossover differences to isolate both stationary orbit‐geopotential and
non‐geopotential errors in altimetry data. Specifically two types of combinations are found useful. While no combination of
differences can resolve the full radial error of single or paired satellites, an approximation of the mean or geographically
correlated error of the generally dominant lower orbit of a pair can be found from one kind (substitutions). (The variable
part of the error is always available from the single‐satellite crossover differences.) A second useful combination type is
found to yield no geopotential orbit error (zeros): uniquely, these can reveal errors in altimetry from imperfect media corrections
as well as oceanographic changes in sealevel. The later circumstance is particularly important when the missions for a pair
of satellites are disparate in time.
This revised version was published online in July 2006 with corrections to the Cover Date. 相似文献
17.
In this paper the extended H
filtering algorithms for the design of the GPS-based on-board autonomous navigation system for a low earth orbit (LEO) satellite are introduced. The dynamic process models for the estimation of position, velocity and acceleration from the GPS measurements are established. The nominal orbit of the small LEO satellite is determined by using the 7th–8th order Runge—Kutta algorithms. Three filtering approaches are applied to smooth the orbit solutions, respectively, based upon the simulated GPS pseudo range observables using the Satellite Navigation Tool Box. The simulation shows that the observed orbit errors obtained by using the extended H
filtering algorithms can be reduced to a lower level than the observed orbit errors in the sense of RMS within 12 h of tracking time by using the H
filtering algorithms and the extended Kalman filtering algorithms under the appropriately designed parameters. Based upon the position errors predicted by the three filtering algorithms after the last observation, we find that the extended H
filtering algorithm provides the least position errors of the user satellite.This revised version was published online in October 2005 with corrections to the Cover Date. 相似文献
18.
Radial,transverse and normal satellite position perturbations due to the geopotential 总被引：1，自引：0，他引：1
Perturbations in the position of a satellite due to the Earth's gravitational effects are presented. The perturbations are given in the radial, transverse (or alongtrack) and normal (or cross-track) components. The solution is obtained by projecting the Kepler element perturbations obtained by Kaula [Kaula, 1966] into each of the three components. The resulting perturbations are presented in a form analogous to the form of Kaula's solution which facilitates implementation and interpretation. 相似文献
19.
《天文和天体物理学研究(英文版)》2016,(2)
An optical survey is the main technique for detecting space debris. Due to the specific characteristics of observation, the pointing errors and tracking errors of the telescope as well as image degradation may be significant, which make it difficult for astrometric calibration. Here we present an improved method that corrects the pointing and tracking errors, and measures the image position precisely. The pipeline is tested on a number of CCD images obtained from a 1-m telescope administered by Xinjiang Astronomical Observatory while observing a GPS satellite. The results show that the position measurement error of the background stars is around 0.1 pixel, while the time cost for a single frame is about 7.5 s; hence the reliability and accuracy of our method are demonstrated. In addition, our method shows a versatile and feasible way to perform space debris observation utilizing non-dedicated telescopes, which means more sensors could be involved and the ability to perform surveys could be improved. 相似文献