Approximate Feedback Linearization of Spacecraft with Momentum Exchange Devices

• Main Authors: Wu, Tsung-Che, 吳宗哲
• Other Authors: Jyh-Jong Sheen
• Format: Others
• Language: zh-TW
• Published: 1996
• Online Access: http://ndltd.ncl.edu.tw/handle/78632488755136644379

碩士 === 國立海洋大學 === 機械與輪機工程學系 === 84 === Spacecraft attitude control and momentum management is a highly nonlinearcontrol problem. The first objective of this thesis is to extend the result ofthe feedback linearization for spacecraft attitude control and momentum manage-ment problem on principal axes to body axes. Basically, feedback linearizationis an extension of pole placement for linear system to nonlinear systems. Simplified feedback linearizing controllers such as, linearized first ordercontroller and second order nonlinear controller will be obtained. The compari-son of the performance of these controllers will be conducted. The singularityand the stability problem of the control systems will be discussed. Due to the limitations of the application of feedback linearization tech-nique to control systems, the second objective of this research is to investi-gate the application of approximate feedback linearization developed by Krenerto the spacecraft nonlinear control problem. There are two advantages in thisscheme: it can be easily applied to to the controller design of arbitrary order; and it only need to solve a set of linear partial differential equations todetermine nonlinear coordinate change and state feedback. The simulation results indicate the performance of the high order non-linear controller is closer to the performance of the feedback linearizing controller than the linearized one. Moreover, the stability of the control system with the feedback linearizing controller is guaranteed inside the validregion of state transformation. However, the approximate controllers may causethe stability problem of the control systems. This will be demonstrated bysimulations.