The shape and perigee of artificial satellite orbits shall continually variate due to caused by the atmospherical drag and the earth gravity.
人造地球卫星的轨道由于大气阻力和地球引力场等因素的摄动，其形状和近地点位置将不断改变。
This paper deals with the characteristic, the USES and the calculation of orbits of earth synchronous satellite.
本文阐述了地球同步卫星的特征、用途及其轨道计算。
The automated detection software stores video clips of each detected satellite, debris, and meteor and provides estimates of the, altitude and inclination of the orbits.
自动化的检测软件检测到存储每个卫星，碎片和流星视频剪辑，并提供估计的，高度和轨道倾角。
This paper presents a new method to classify satellite orbits and the basic Characterization of stay orbit.
本文给出卫星轨道分类的一个新方法和逗留轨道的基本特性，这一特性可用于卫星轨道的初步设计。
According to the limitation of the satellite orbits and spectrum resources, this paper puts forward some methods for making effective use of the satellite orbits and spectrum resources.
根据卫星轨道和频谱资源的有限性，提出了有效利用卫星轨道和频谱资源的几种方法。
GEOSAT, a US altimetry satellite, is introduced in this paper. Its characteristics of the orbits, both theoretic and observational, are analyzed.
本文介绍了美国的海洋测高卫星GEOSAT，分析讨论了GEOSAT的理论设计轨道及实测轨道特征。
According to this difficulty, a kind of fast calculation method of satellite orbit-extract the orbits control points is put forward, and perspective frustum is combined to judge the orbits visibility.
针对这一难点，提出了一种卫星轨道快速计算的方法-提取轨道的控制点，结合透视裁剪体来判断轨道的可见性。
Taking the SILEX as an example, the characteristic and the upgrading scenarios of the satellite optical terminals in different orbits are also analyzed in brief.
以SILEX研究计划为例，简要分析了各种轨道之间光通信系统的特性及未来光学终端的升级方案。
The GPS ephemeris and GLONASS ephemeris adapt to some kind of the satellite orbits while they have some shortcoming.
GPS和GLONASS广播星历形式适合于某一类卫星轨道，但存在一定局限性。
A method of standardization GPS satellite orbits using trigonometric polynomial function is put forward in this paper.
本文提出了一种基于三角函数多项式的GPS轨道标准化方法。
The paper analyzes the capability of satellite-board interceptor on low orbits to intercept the satellites on high orbits by orbit maneuvering.
本文分析了低轨星载拦截器进行轨道机动拦截高轨卫星的能力。
Based on the two-body assumption, two methods are used to investigate the relative motion of satellite formation flying on circular or near-circular orbits.
首先基于二体假设，采用两种方法系统地研究了圆或近圆轨道上卫星编队飞行的相对运动。
Based on the two-body assumption, two methods are used to investigate the relative motion of satellite formation flying on circular or near-circular orbits.
首先基于二体假设，采用两种方法系统地研究了圆或近圆轨道上卫星编队飞行的相对运动。
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