Flexible spacecraft attitude control method for flywheel saturation and friction characteristics

Abstract

The invention relates to a flexible spacecraft attitude control method for flywheel saturation and friction characteristics and aims to solve a problem of influence of flywheel saturation and friction characteristics on spacecraft control precision. According to the method, a spacecraft coupling kinetic equation containing flywheel saturation and friction characteristics is firstly constructed; secondly, a friction interference estimator according to flywheel friction characteristics is established; thirdly, a flexible vibration observer is designed according to interference caused by flexible accessory vibration; fourthly, an anti-saturation controller is designed for inhibition according to friction interference estimation errors and flexible vibration interference observation errors; and lastly, through solving control gain of the anti-saturation controller, the friction interference estimator and the flexible vibration observer, a composite layered anti-interference controller is designed, and spacecraft anti-interference attitude control under the action of multi-source interference influence is accomplished. The method is advantaged in that attitude control precision of spacecrafts employing a flywheel execution mechanism can be remarkably improved, and the method can be applied to high precision attitude control on spacecrafts such as high precision earth observation satellites in the aerospace field and space telescopes.

Description

technical field [0001] The invention relates to a flexible spacecraft attitude control method aimed at flywheel saturation and friction characteristics, which is suitable for a flexible spacecraft attitude control system that needs to carry limited execution capabilities and needs to achieve high-precision control, and belongs to the field of spacecraft attitude control. Background technique [0002] In recent years, with the continuous enrichment of human space exploration activities, the complexity of tasks has increased, and the demand has also increased. It is required that spacecraft be equipped with larger solar panels to provide more energy. In addition, as spacecraft missions become more and more remote, higher requirements are placed on spacecraft communication antennas, which require antennas with larger structures and stronger power to receive weak signals at long distances; The spacecraft needs to carry larger and larger accessories. In terms of launch cost and t...

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Problems solved by technology

[0004] Patent application No. 201510294341.9 proposes an anti-jamming attitude control method based on the friction characteristics of the reaction wheel, but there are two problems: (1) This article does not consider the vibration interference caused by the flexible accessories attached to the flexible spacecraft , will affect the accuracy of the spacecraft; (2) does not consider the saturation characteristics of the flywheel, and will be limited in actual use

The patent application number is 201510303102.5, which proposes a flexible spacecraft attitude control system and method for flywheel low-speed friction. The proposed method also has similar problems: (1) does not consider the saturation characteristics of the flywheel; (2) the method The flywheel friction observer involved in this patent is completely different from the form of this patent, and it cannot guarantee fast tracking of friction disturbances in a limited time, so it will be inferior to the method in this paper in terms of accuracy and speed

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