Flexible satellite pointing tracking control method containing six-degree-of-freedom vibration isolation platform

Abstract

The invention discloses a flexible satellite pointing tracking control method containing a six-degree-of-freedom vibration isolation platform, and designs a pointing tracking control method easy for engineering realization by taking time domain and frequency domain indexes as the basis for the flexible satellite containing the six-degree-of-freedom vibration isolation platform. Firstly, vibrationcharacteristics of a control moment gyroscope are considered, and kinetic models of an upper platform and a lower platform of a six-degree-of-freedom vibration isolation system are established respectively; then, a vibration isolation supporting rod is equivalent to a three-parameter model, a transfer function of the flexible satellite vibration isolation platform is obtained through simplification, and vibration isolation platform parameters are designed according to vibration isolation indexes; and finally, a controller form and parameters are designed based on a frequency domain theory according to a controller performance index aiming at a problem that a target attitude and an angular velocity change quickly in a certain period of time in a pointing control process. According to the method, the transfer function of the flexible satellite three-parameter vibration isolation platform is established, the designed vibration isolation parameters can effectively attenuate high-frequencyvibration of an executing mechanism, the designed pointing tracking controller can meet the frequency domain index and the time domain precision index, and the method can be widely applied to actual engineering.

Description

technical field [0001] The invention relates to a method for pointing and tracking control of a flexible satellite with a six-degree-of-freedom vibration isolation platform. For the flexible satellite with the control moment gyro as the actuator for overall vibration isolation, the integrated control of the upper and lower platforms for pointing and tracking is realized. It can be applied to the attitude tracking control with rapid changes in the target attitude and angular velocity within a certain period of time, the flexible vibration suppression of the sailboard during the attitude maneuvering process, and the high-frequency vibration isolation of the actuator. Strong robustness. The invention belongs to the field of spacecraft attitude control. Background technique [0002] With the continuous deepening of aerospace applications and space exploration activities such as laser communication, space remote sensing, and deep space telescopes, the functions and structures o...

AI Technical Summary

Problems solved by technology

For the pointing and tracking control of master and slave satellites, the existing control methods include sliding mode control, adaptive control, active disturbance rejection control, regression control an

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