Method for controlling flexible satellite based on feature model

Abstract

The invention relates to a method for controlling a flexible satellite based on a feature model, which is characterized in that the time dimension, the sampling time and the parameters M and m are determined according to the kinetic equation of the flexible satellite; the coefficient range of the feature model is determined according to each obtained variable; the parameters of the feature model are identified by utilizing a gradient method; and a control law is designed according to the coefficients of the feature model obtained through the identification, and the attitude angle of the flexible satellite is controlled through the kinetic equation that the control law is fed back to the flexible satellite. The method has the advantages that the time dimension and the sampling period of the flexible satellite are introduced; the change rate of the flexible satellite is depicted; the bottleneck problem of the feature modeling of the flexible satellite is solved; the expression of the parameter range of the feature model of the flexible satellite is provided; the parameter property of the feature model is qualitatively researched; the boundary of the parameters of the feature model is relative to the sampling period, the modeling error, the system order and the change rate of the system from the given parameter range; and the theoretical foundation of the self-adaptive control based on the feature model is laid for the flexible satellite. The method is suitable for the feature model of the attitude kinetics of an aircraft so as to lay the foundation for the aircraft based on the attitude control of the feature model.

Description

technical field [0001] The invention relates to a satellite control method, in particular to a characteristic model-based flexible satellite control method, which belongs to the technical field of satellite control. Background technique [0002] The full-coefficient adaptive control method based on the characteristic model was proposed by Academician Wu Hongxin. After more than 20 years of research, important progress has been made in theory and application, and a set of highly practical adaptive control theory and method has been formed. This method requires fewer identification parameters, can guarantee the transient performance and steady-state performance of the closed-loop system, and has strong robustness and adaptability. In particular, the theoretical ideas and engineering points of this method have been creatively applied to the control of spacecraft return and reentry, and its parachute opening accuracy has reached the world's advanced level. [0003] The basic id...

AI Technical Summary

Problems solved by technology

The problem of determining the parameter range of the characteristic model of the linear steady system has been solved, but for the nonlinear system, this problem has always been the bottleneck restricting the design of the full coefficient adaptive control

[0004] Nonlinear Golden Section Adaptive Control, Wu Hongxin, Wang Ying, Xie Yongchun, Acta Astronautics Publishing (2002, 23(6): 1-8.2) and the characteristic model and adaptive fuzzy control method of multivariable linear time-varying systems, Sun Duo Qing, Wu Hongxin, Acta Astronautica Sinica Publishing (2005, 26(6): 677-681.) discloses the method of transforming several types of nonlinear systems of special forms into second-order time-varying difference equations. The method given is only valid for the particular form of nonlinear system considered and does not take into account modeling errors

For the determination method of the parameter boundary of the flexible satellite characteristic model under the arbitrary modeling error given by the present invention, there is no disclosed method with complete practical significance

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