Robust Hinf spacecraft pointing control method and system based on feature structure configuration

Abstract

Provided is a robust Hinf spacecraft pointing control method and system based on feature structure configuration. A controller designed by the feature structure configuration method can provide complete parameterization representation of all control laws with desired characteristics or structures for the control system, and then a reasonable constraint condition is designed according to the characteristics of a spacecraft to select free parameters in the control laws. According to the method disclosed by the invention, the satellite robust Hinf high-precision pointing control design is carriedout by mainly taking the feature structure configuration method, according to the designed closed-loop control system result, the feature value of the reasonable closed-loop system is determined andis adjusted according to the normalized structure of an existing satellite controller, the main feature value of the on-satellite closed-loop control system is consistent to that of the invention, sothat the closed-looped system has the similar motion characteristics. The in-orbit verification of the spacecraft with uncertain large-flexible structures shows that the convergence and robust stability are high, and the high-precision pointing task demand in the long-term on-orbit operation can be guaranteed, thus the reliability of the system is improved.

Description

technical field [0001] The invention relates to a robust Hinf spacecraft high-precision pointing control method and system based on characteristic structure configuration, which solves the problem of low bandwidth and long steady-state response time of traditional controllers in the design of spacecraft control systems with large flexible accessories. It belongs to the field of satellite control technology to improve the responsiveness and robustness of the closed-loop system by configuring the eigenvalues ​​and eigenvectors of the system by adopting modern control theory methods. Background technique [0002] For a spacecraft with a large flexible attachment with an arm length and reflector diameter of more than ten meters, the traditional design method is mainly used when designing controller parameters, that is, the frequency of the closed-loop system is lower than that of the flexible attachment by reducing the system bandwidth. Several times the fundamental frequency to...

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Problems solved by technology

However, the problem brought by this method is that the steady-state response time of the closed-loop system is relatively long. When the satellite switches from one working mode to another, a long period of steady-state process is required, or the payload is in the During the orbit test, the satellite attitude needs to cooperate with the maneuver to make the large flexible antenna point to different ground reference points, so the slow response of the control system will inevitably affect the steady-state time of the payload pointing, and then affect the communication and other business work

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