T-S fuzzy model-based flexible spacecraft multi-objective integrated control method

Abstract

The invention provides a T-S fuzzy model-based flexible spacecraft multi-objective integrated control method. According to the method, a T-S fuzzy dynamic model of a flexible spacecraft is established, and the universal approximation of the T-S fuzzy model of the spacecraft is proved; the uncertainty of the inertia of the spacecraft which is caused by relative movement of flexible parts, and various kinds of space disturbance torques are considered; a control-performance LMI description and multi-objective integrated LMI method is adopted; and a robust H-infinity state feedback controller which can make a closed-loop system meet pole constraints and control input constraints is designed based on the T-S fuzzy model of the spacecraft. As indicated by numerical value simulation results, the designed state feedback control system has the advantages of short dynamic adjustment time, fast response, small overshoot and high steady-state accuracy, and can effectively inhibit the vibration of the flexible parts caused by attitude variation, and has high robustness and adaptability for the uncertainty of the model of the spacecraft.

Description

technical field [0001] The invention relates to a multi-objective comprehensive control method for a flexible spacecraft based on a T-S fuzzy model, and belongs to the technical field of spacecraft dynamics and control. Background technique [0002] With the development of modern science and technology, the large-scale, flexible and multi-functional spacecraft is an important development direction. As a result, a representative spacecraft structure is produced, that is, a spacecraft with a central rigid body and extended flexible accessories. Such extended flexible accessories include various solar panels, flexible antennas and their supporting arms, mechanical arms, cranes, etc. This type of spacecraft is being widely used in the aerospace field. For this multibody system with flexible appendages, the maneuvering of the body will inevitably cause the vibration of the appendages, and the vibrations of the appendages will in turn affect the attitude of the body. This kind o...

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Problems solved by technology

However, on the one hand, these studies did not fully consider the vibration of flexible components, and directly used the structural dynamics model obtained from the structural dynamics analysis; on the other hand, although the control method of modern control theory was combined int...

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