【作者】 韦娟；

【导师】 袁建平；

【作者基本信息】 西北工业大学 ， 飞行器设计， 2002， 博士

【摘要】 本论文所研究的双基站卫星群是指以地面基站和天基基站(空间站)同时作为基地的一组小卫星。这种形式的小卫星群将空间站直接作为天基信息网中的一个节点，同时考虑了空间站对小卫星群的支持，从而形成一个新型的天地一体化信息网络，将在对地观测、遥感、军事航天等任务中发挥重要的作用。 本文主要探讨了两种双基站小卫星群的布设方法，并研究了小卫星群位置保持和姿态控制。主要内容如下： 在对空间站和小卫星网的相互需求和支持以及空间站与小卫星网的综合应用进行综述之后，重点研究了基于运动学方法的相对运动方程。首先将相对运动参数与轨道要素直接联系起来，详细推导了利用相对轨道要素来描述的相对运动方程，据此可直接得出环绕卫星的轨道根数；然后，从实际出发建立了一套有利于相对轨道分析和设计的相对运动方程。接着考虑安全性和编队飞行相对距离的限制，研究了绕飞轨道的相对轨道要素取值范围，详细推导了大气阻力摄动与地球扁率摄动的相对摄动表达式。 在第3章，首先分析了卫星相对地基的运动特性，在地基的运动特性研究中，重点研究了以升交点地理经度来描述所有能覆盖到目标点的轨道，利用球面三角形方法推导了在考虑地球形状J2项摄动影响时，各种情况下能覆盖目标点的轨道升交点经度范围，得到了完整的解析表达式。并且利用升交点经度特性，得到了在过顶时间限制条件下的升交点取值范围。探讨了卫星相对于天基的运动特性，并利用地基运动特性的结果，得到了卫星相对于空间站在过顶时间限制条件下的升交点取值范围。 利用前一章的分析结果，第4章为空间站设计专用的数据中继星座。主要包括星座轨道高度的选择；偏心率和倾角的选择；升交点赤经的选择；轨道面数目及其卫星的布置；在设计中，同时考虑了轨道漂移和卫星之间的星际链路建立。 接下来作者研究了编队飞行卫星群构型和策略以及位置和姿态的保持，首先分别利用动力学和运动学方法进行编队卫星群布局设计研究，以空间站为参考卫星，研究了星下点为圆形的对地观测任务的编队构型设计，研究了在地球扁率摄动影响下，编队卫星群的运行情况。然后推导了编队卫星的相对位置保持控制律，对于以参考卫星(空间站)为中心的编队飞行和对于由若干个相同卫星组成的虚 摘 要拟大卫星两种情况分别进行了姿态控制研究。 最后一章探讨了同时进行平移运动和旋转运动的编队重构问题。研究重点是平移运动，由于系统是时变的，所以引入了鲁棒控制理论，利用H。对系统进行平移控制。更多还原

【Abstract】 Small satellites based Two-Station-System refers to a cluster of small satellites which will be governed by both ground station and space station in this paper. Space station will be a main node of space-based information network to small satellite groups. Considering support of space station to small satellite groups, this will be form a new information network of space and ground, which will be important to such applications as earth observation, remote sensing and military affairs etc.Two kinds of configuration and design of small satellites groups based on Two-Station-System are discussed emphatically in the dissertation. The position keeping and attitude control about small satellites is also studied. The main contents are as follows:After the summary of the requirements and applications of space station and small satellites groups, a direct equation of relative motion based on kinematics method is elected. Firstly, the equation of relative motion based on kinematics is presented in detail, so relative motion parameters may relate directly with orbit elements. Secondly, relative motion is simplified from practice, so it is convenient for orbit analyzing and design. Then, considering safety and limit of relative distance of formation flying, the select area of relative orbit elements are studied. Finally, perturbation of relative motion on air drag and J2 term are induced in detail.In chapter 3, the characteristics of relative motion of small satellite based on ground station are firstly analyzed, in which using spherical trigometry, the analytic formulas evaluating the longitude ranges of ascending node which can cover the target are deduced with J2 precession. With the solution, the longitude ranges of ascending node limited by the cross-time can be gained. Secondly, a serious of characteristics of small satellite to space station is studied. According to the results of small satellite to ground station, the longitude ranges of ascending node limited by the cross-time can be gained relative space station.Using the analytic results above, in chapter 4, a special data relay constellation is designed for space station, which include mainly the selection of orbit altitude, eccentricity, inclination, longitude of ascending node, the number of orbit and distribution of satellite. Orbit drift and inter-satellite link is also considered.In the following content, configuration and strategy, position keeping and attitude control of formation flying are researched. With kinematics and dynamicsmethod separately, configuration and design of formation flying are studied. An example about earth observation is given, in which space station is reference satellite, and configuration of formation flying is circle in track of sub-satellite point. The impact of J2 precession to formation flying is studied too. Then relative position keeping of formation flying is presented. Finally, two kinds of method of relative attitude control are investigated. The first case is that reference satellite (space station) is the center in formation flying. All satellites, which form a large virtual satellite, are both reference and adjoint satellites in the second case.In the last chapter, rotation and translational motion is studied to formation reconfiguration. The emphasis is translational motion. Due to system of control is time-variant system, robust control theory ( H, ) is used to translational control.更多还原