A composite attitude and vibration control method for an anti-jamming flexible spacecraft

Abstract

A composite anti-jamming attitude control method for a flexible spacecraft, which is characterized in that it includes the following steps: First, by considering the vibration of the flexible attachment, the change of the spacecraft moment of inertia caused by the expansion of the flexible attachment and the space environment disturbance torque on the attitude In order to control the influence of control, a flexible spacecraft dynamics model including neutral uncertain dynamic items and external equivalent disturbance variables is established; secondly, in view of the serious influence of structural vibration on the stability of the spacecraft, and the large existence of flexible accessories such as sailboards, With the characteristics of flexibility and low damping, the PPF active vibration controller is constructed to reduce the impact of vibration modes on the spacecraft body; thirdly, the H∞ anti-jamming controller is designed to suppress vibrations from flexible mechanisms such as sailboards and extension rods. The disturbance caused by the change of the spacecraft rotational inertia caused by the deployment and the bounded disturbance such as the space environment disturbance moment; finally, based on the convex optimization algorithm, the composite anti-jamming output feedback attitude and the vibration composite controller are solved; Design and other advantages, can be used for high stability control of flexible spacecraft.

Description

technical field [0001] The invention relates to a composite anti-jamming attitude control method of a flexible spacecraft, which uses the output feedback form to complete the functions of suppressing the structural vibration, moment of inertia change and space environment disturbance torque of the flexible spacecraft, thereby realizing high-stability attitude control . Background technique [0002] Spacecraft usually has flexible attachments of large and light structures such as solar panels. The flexible structure has the characteristics of low modal frequency and dense, small damping, which is easy to be aroused when the spacecraft completes actions such as maneuvering, turning and docking in the air. Therefore, it is particularly important to seek an active vibration suppression method to actively control the vibration of space flexible structures. When the spacecraft is in orbit, with the expansion and contraction of the flexible appendage, the moment of inertia of the ...

AI Technical Summary

Problems solved by technology

[0004] The technical solution of the present invention is to propose a flexible spacecraft anti-interference attitude for the attitude control of the flexible spacecraft affected by the vibration of the flexible attachment, the uncertainty of the moment of inertia of the star, and the interference torque of the space environment. and vibration composite control method; firstly, active vibration control quickly suppresses the vibration brought by the flexible attachment; secondly, the H ∞ The optimal control method suppresses the disturbance caused by the uncertain moment of inertia and the bounded energy disturbance moment of the space environment; finally, the convex optimization algorithm is used to solve the output feedback control gain matrix of the system; the designed method solves the problems faced by the attitude control of flexible spacecraft The vibration of the flexible attachment, the uncertainty of the moment of inertia of the star and the disturbance moment of the space environment improve the robust stability of the system

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