卫星运动方程

卫星运动方程的摄动解法

The perturbation solution to the equations of satellite motion

卫星运动方程中的摄动力模型

The Perturbation Force Model of Satellite Movement Eguation

推导了协议地球坐标系下的卫星运动方程。

The equation of satellite orbital motion was derived in the conventional terrestrial coordinate system .

本文应用数值积分法构造了卫星运动方程中各摄动力模型，分别给出了轨道计算中所需的实用公式及各相关的偏微分。

This article , through numerical integral method , Constructs the perturbation force model of satellite move-ment eguation , and gives the practical formulas and every relative partial differential needed in orbit Calculating .

主要的研究工作如下：1、系统研究了导航星座自主定轨的基础理论，包括时间系统、坐标系统、动力学模型及卫星运动方程的数值解法。

Followings are the main study in this paper . 1 . The theory and methods of autonomous orbit determination are systematically expounded , including time system , coordinate system , dynamic model and numerical mothod of satellite motion equation .

通过对卫星轨道运动方程积分30min，可知由摄动力模型的简化、积分器和忽略极移影响等因素引起的拟合误差分别为0.827m，0.224m和0.025m。

Min , it can be found that the orbit fitting error due to the simplified force model , the numerical integration method and the neglect of the polar motion are respectively 0.827 ? m , 0.224 ? m and 0.025 ?

用四元数法建立卫星返回运动方程组

Establishing recovery motion equations of satellite with quaternion rule

给出了卫星姿态运动方程，并证明采用两种方法控制卫星姿态的稳定性。

The attitude motion equation of satellite was given , and the attitude of magnetic control for gravity gradient satellite would go to stable .

基于相对轨道根数法，根据卫星相对运动方程，提出了自然队形的概念及队形设计的一般方法，并给出了具体的例子。

A concept of natural formation and a general RT design method are proposed based on the Relative Orbital Element Method and the relative motion equation in this paper . An example is given .

最后对零倾角卫星编队相对运动方程的线性化误差进行了理论分析，并利用数值仿真对两种运动学方法的相对运动方程线性化误差进行了比较分析。

Finally , the linearization error ( LE ) of satellite formation relative motion equation is researched .

第二章给出了编队卫星的相对运动方程和对地观测常用的编队卫星轨道设计。

With earth observing application , chapter 2 describes the inter-satellite relative movement functions and orbital design for ordinary earth observing satellite formation .

描述人造卫星运动的微分方程非常复杂，不可能给出解的解析表达式。

The differential equations that describe the artificial satellite motion are very complicated , and it is impossible to get the analytic express of solution .

分别对分布式卫星相对运动的动力学方程和运动学方程进行了推导和简要的分析。

The dynamic equations and the kinematic equations of relative motion were derived and analyzed separately .

根据星群分离控制的一般要求，本文研究了卫星群的相对运动方程，分析了其相对运动特性。

In the paper the relative motion equation of satellites ' group is studied , and the motion characteristic is analyzed .

基于卫星相对运动状态转移方程，推导出了星座双脉冲式变轨的理论解，即所要施加的脉冲控制量的解析式；

Based on relative motion equation of satellite state transferring , analytic solution of two impulse orbit transfer of constellation is derived , which is analytic equation of impulse control variable .

首先，在合理的假设条件下，基于运动学关系推导了环绕卫星相对参考卫星的相对运动方程；

At first , based on kinematic relationship , motion equations of surrounding satel lite with respect to reference satellite is deduced under proper assumption .

首先，目前在卫星动力学中常用的所有人造卫星运动方程的数值解法有待改进的最重要的问题就是稳定性问题。

First , now in all common numerical methods for the satellite dynamics equations the most important problem that needs to be improved is stability problem . Exercise .

根据GALILEO卫星系统的设计参数，建立了卫星运动方程，编制了GALILEO系统的星座仿真软件；

Satellite motion equation is established based on design parameters of Galileo system and software are compiled to simulate Galileo constellation .