An LMI-based nonlinear attitude control approach

Long Life Show, Jyh Ching Juang, Ying Wen Jan

研究成果: Article同行評審

82 引文 斯高帕斯(Scopus)

摘要

This paper presents a nonlinear control law for large-angle attitude control of spacecraft. For the ROCSAT-3 spacecraft, a highly accurate and robust attitude control is desired during the orbit-raising phase. The three-axis attitude control is achieved using four body-fixed canted thrusters. In the paper, the nonlinear dynamic equations of the satellite are derived and the control requirements are stated. A novel nonlinear attitude control structure is then proposed for spacecraft control problems. The nonlinear controller contains linear feedback terms for stabilization and nonlinear terms for performance enhancement. One salient feature of the proposed approach is that the nonlinear controller parameters are designed using a linear matrix inequality (LMI) method. It turns out the controller design of stabilization and H-type performance problems for spacecraft dynamics become rather transparent when the proposed controller structure and LMI method are employed. The design is shown to generalize many existing results. Simulation results based on the ROCSAT-3 system are then presented to demonstrate the proposed design method.

原文English
頁(從 - 到)73-83
頁數11
期刊IEEE Transactions on Control Systems Technology
11
發行號1
DOIs
出版狀態Published - 2003 一月

All Science Journal Classification (ASJC) codes

  • 控制與系統工程
  • 電氣與電子工程

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