淡江大學機構典藏:Item 987654321/65289
English  |  正體中文  |  简体中文  |  全文笔数/总笔数 : 62805/95882 (66%)
造访人次 : 3940222      在线人数 : 1006
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: https://tkuir.lib.tku.edu.tw/dspace/handle/987654321/65289


    题名: Comparison of Magnetic and Aerodynamics Stabilization for a Microsatellite
    作者: Zuu-Chang Hong;Wen-Hu Hu;Yen-Hsun Chen;Da-Ban Lee;Jeng-Shing Chem
    贡献者: 淡江大學機械與機電工程學系
    关键词: TUU-SAT1;attitude control;fuzzy control
    日期: 1997-12-01
    上传时间: 2011-10-20 21:37:29 (UTC+8)
    摘要: When the orbital altitude of a satellite is relatively low, the methods of magnetic and aerodynamic stabilization can be considered. Both methods are very effective when the satellite is small. In particular, magnetic and aerodynamic stabilization systems have been installed in some satellites. Examples are UO-sat and Cosmos-320 with magnetic and aerodynamic methods respectively.

    Magnetic torques acting on a spacecraft result from the interaction of the spacecraft's residual magnetic field and the geomagnetic field. Because a magnetic torque is always orthogonal to geomagnetic field vector, it is not favorable in all regions of the orbit. 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. The gravity gradient stabilization method also 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 purpose of this paper is to compare the methods of magnetic and aerodynamic stabilization both based on the aid of a gravity gradient boom for attitude control. We shall consider the attitude motion of a 50 kg microsatellite and 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: COSPAR Colloquia Series 10, pp.210–221
    DOI: 10.1016/S0964-2749(99)80028-6
    显示于类别:[機械與機電工程學系暨研究所] 期刊論文

    文件中的档案:

    档案 描述 大小格式浏览次数
    Comparison of Magnetic and Aerodynamics Stabilization for a Microsatellite.pdf484KbAdobe PDF1检视/开启
    index.html0KbHTML16检视/开启

    在機構典藏中所有的数据项都受到原著作权保护.

    TAIR相关文章

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