Fuzzy singular perturbation modeling and attitude control method for complex flexible spacecraft

Abstract

The invention belongs to the field of spacecraft control and relates to a fuzzy singular perturbation modeling and robust attitude control method for complex flexible spacecraft, namely a robust combined control method for fusing static output feedback control and output integration. The method comprises the following steps of: establishing an uncertain continuous fuzzy singular perturbation model and a standard discrete fuzzy singular perturbation model according to a dynamic model and a kinematic model of the spacecraft in combination with fuzzy logic and singular perturbation technology; and designing a robust controller combined by a static output feedback controller and an output integrator by a spectral norm and linear matrix inequality (LMI) method and resolving a group of LMIs which are unrelated to a perturbation parameter so as to obtain a controller parameter and solve an ill-conditioned problem caused by the perturbation parameter and the problem of difficulty in selection of an initial value in an LMI resolving static output feedback controller gain method. Through the method, flexible vibration and external interference can be overcome effectively, and control effects such as high response speed, high attitude control accuracy, high anti-jamming capability and high robust performance are achieved.

Description

technical field [0001] The invention relates to a complex flexible spacecraft fuzzy singular perturbation modeling and attitude control method, which belongs to the technical field of spacecraft control. It is especially suitable for very high-precision control of complex spacecraft with flexible accessories, and can also be used for modeling and high-precision control of other nonlinear flexible systems or multi-time scale systems such as robots, power systems, and drilling platforms. Background technique [0002] A complex flexible spacecraft refers to a large spacecraft with multiple retractable flexible appendages, large parts that can be increased, decreased, and moved (solar wings, communication antennas, or remote sensing antennas, etc.). The spacecraft accessories not only rotate rigidly relative to its main body, but also produce flexible vibrations, which affect the attitude of the spacecraft and even make it unstable. In addition, the consumption of spacecraft fu...

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Problems solved by technology

[0005] The purpose of the present invention is to solve the problem that the existing control method cannot eliminate the flexible vibration caused by the flexible accessories and the steady-state error caused by the external interference when the complex flexible spacecraft is running in the outer space, and proposes a complex flexible space vehicle. Fuzzy and Singular Perturbation Modeling and Attitude Stabilization Control Method for Sexual Spacecraft

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