English  |  正體中文  |  简体中文  |  全文笔数/总笔数 : 51772/86996 (60%)
造访人次 : 8374959      在线人数 : 122
RC Version 7.0 © Powered By DSPACE, MIT. Enhanced by NTU Library & TKU Library IR team.
搜寻范围 查询小技巧:
  • 您可在西文检索词汇前后加上"双引号",以获取较精准的检索结果
  • 若欲以作者姓名搜寻,建议至进阶搜寻限定作者字段,可获得较完整数据
  • 进阶搜寻

    jsp.display-item.identifier=請使用永久網址來引用或連結此文件: http://tkuir.lib.tku.edu.tw:8080/dspace/handle/987654321/65275

    题名: Aerodynamic and gravity gradient stabilization for microsatellites
    作者: Chen, Yen-hsun;Hong, Zuu-chang;Lin, Chung-hsien;Chern, Jeng-shing
    贡献者: 淡江大學機械與機電工程學系
    日期: 2000-04
    上传时间: 2013-05-30 15:26:15 (UTC+8)
    出版者: Kidlington: Pergamon
    摘要: When the orbital altitude of a satellite is relatively low, for example, less than 500 km, the method of aerodynamic stabilization can be considered. In particular, this method is very effective when the satellite is small. The aerodynamic restoring torque can be provided by a very light tail stabilizer which is several meters downstream from the main body of the small satellite. An aerodynamic stabilization system has been installed in the Cosmos-149 and another one in the Cosmos-320. One of the disadvantages in using the aerodynamic stabilization is that no rolling stabilization can be achieved. The gravity gradient stabilization method has been used in many satellites. One of the examples is the Eole satellite. In the recent years, many small satellites have adopted this method owing to its long life and continuous Earth pointing characteristics. The main disadvantage is the poor pointing accuracy with respect to the orbiting reference coordinates. This disadvantage can be overcome with the aid of a small reaction wheel. Both pitch and roll orientations can be stabilized. However, no yawing motion stabilization can be achieved by using the pure passive gravity gradient method.

    The purpose of this paper is to combine the aerodynamic and gravity gradient stabilization methods together so that all the three axes stabilizations can be obtained. We shall consider the attitude motion of a microsatellite under the action of both gravity gradient torque and aerodynamic torque. The set of nonlinear equations of motion will be solved numerically with specified initial condition. The satellite operates in a circular orbit with 500 km altitude. The history of the attitude stabilization will be investigated and discussed in detail.
    關聯: Acta Astronautica 46(7), pp.491-499
    DOI: 10.1016/S0094-5765(99)00191-5
    显示于类别:[機械與機電工程學系暨研究所] 期刊論文


    档案 大小格式浏览次数



    DSpace Software Copyright © 2002-2004  MIT &  Hewlett-Packard  /   Enhanced by   NTU Library & TKU Library IR teams. Copyright ©   - 回馈