• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文学位 >Attitude control of small satellites using fuzzy logic.
【24h】

Attitude control of small satellites using fuzzy logic.

机译：使用模糊逻辑控制小型卫星的姿态。

获取原文
获取原文并翻译 | 示例
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

Current interest in small satellites lies in the feasibility of achieving specific but limited objectives. By necessity, small spacecraft technology requires simple control schemes, where small attitude errors can be tolerated inside specified deadbands. The attitude control of a small satellite using fuzzy logic is examined in this thesis.; A realistic satellite is modelled as a central rigid body with a set of flexible appendages. The continuous flexible structures are discretized using the assumed modes method. Equations governing the attitude motion and the bending vibrations of the appendages are obtained from the Lagrangian formulation, while the orbital motion is assumed to be Keplerian.; The cases of thrusting and magneto-torquing are considered for the missions of three-axis and spin stabilization of the satellite, respectively. For each case, a set of control rules based on fuzzy logic is formulated to control the polarity and the switching time of the actuators. Control constraints are imposed on the actuators. Various simulations in the presence of environmental disturbances and uncontrolled vibrations of the appendages illustrate the effectiveness of the attitude fuzzy logic controllers.
机译：当前对小型卫星的兴趣在于实现特定但有限目标的可行性。小型航天器技术必然需要简单的控制方案，在指定的死区内可以容忍较小的姿态误差。本文研究了利用模糊逻辑对小卫星的姿态控制。现实卫星被建模为具有一组柔性附件的中央刚体。连续柔性结构使用假定模式方法离散化。从拉格朗日公式中可以得出控制肢体姿态运动和弯曲振动的方程式，而轨道运动则假定为开普勒。在卫星的三轴和自旋稳定任务中分别考虑了推力和磁转矩情况。对于每种情况，制定了一套基于模糊逻辑的控制规则，以控制执行器的极性和切换时间。对执行器施加控制约束。在存在环境干扰和附件的不受控制的振动的情况下的各种模拟说明了姿态模糊逻辑控制器的有效性。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号