No angular velocity measurement earth-oriented space station angular momentum management method

Abstract

The invention discloses a no angular velocity measurement earth-oriented space station angular momentum management method, and designs a control scheme based on an auto-disturbances-rejection concept, which can work normally when the angular rate gyroscope of a space station measuring system loses efficacy. The method comprises: first, offline designing a system basic controller based on a linear quadratic adjuster configured according to poles; second, separately designing a three-stage linear extension state observer in three axes of the system to observe angular velocity and external disturbance, and meanwhile offline performing presetting to obtain related parameters of each observer; third, uploading parameters of the designed basic controller and observer onto a spaceborne computer, and allowing the attitude control unit of the spaceborne computer to estimate online in real time the attitude angular velocity and aerodynamic moment which can not be provided by a measurement system according to the designed basic observer, meanwhile online identifying aerodynamic moment parameters; and finally, according to designed control laws and compensation algorithms, performing reasonable compensation on aerodynamic moment, and realizing earth-oriented space station attitude control and angular momentum management without angular velocity measurement.

Description

technical field [0001] The invention belongs to the field of attitude control of spacecraft, and relates to an attitude control and angular momentum management method of a space station. Background technique [0002] As a large and complex spacecraft, the space station has a large mass and receives an aerodynamic moment as strong as 10Nm. As a result, the actuator of the space station, the control moment gyro, needs to be unloaded frequently due to rapid saturation. If a magnetic torquer is used for unloading, a 7KW magnetic torquer needs to be designed, which cannot be realized in engineering. Therefore, only the jet unloading method can be used, which will lead to frequent consumption of fuel and affect the on-orbit life of the space station. The long-life design requirement makes the space station need to manage the angular momentum while controlling the attitude. [0003] During the development of the International Space Station, NASA proposed a real-time angular momen...

AI Technical Summary

Problems solved by technology

For the ground-oriented space station, using the internal model principle to manage the angular momentum needs to expand the system to 24 dimensions and design a 3×24-dimensional controller, and it is impossible to realize the attitude control and control of the space station when the angular rate gyro of the measurement system fails. angular momentum management

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