State transition control of satellite attitude
TAN Tian-le
Abstract：For the application requirements of satellite, the kinematics and dynamics of satellite attitude are analyzed and modeled. By using feedback linearization, the high-order nonlinear terms of attitude motion are included in attitude control, by local dynamic linearization, the satellite dynamical system is approximated as a time-invariant system. Method of power series is used to carry out approximate solution of the system state transition. The expected deviation of attitude angle and attitude angular velocity is obtained by using model prediction. By generalized inverse transform, a kind of full state feedback controller is designed based on the minimum norm and least squares of deviation. A high precision control method based on state transition for satellite attitude maneuver, tracking and stabilization is proposed. The parameters of the controller have the characteristics of time-varying adaptive according to the sampling period and the current state of the system. Considering the influence of solar panels flexible vibration and various noise and error, the feasibility and effectiveness of the method are verified by simulation.
Keywords：satellitefeedback linearizationpower seriesmodel predictiongeneralized inverse transformstate tran-sitionattitude control
Publication Date：2017-01-01
Online Publishing Date：2025-08-15(First online date of this platform, not the publication date of the document)
Pages：8( 655-662 )