Spacecraft rapid maneuvering attitude tracking adaptive robust control method

Abstract

The invention provides a spacecraft rapid maneuvering attitude tracking adaptive robust control method, which adopts a tracking differentiator to calculate the transition process of reference input and give the differential of the reference input, and solves the contradiction between the overshoot and rapidity of the system by arranging a proper reference signal transition process. The design of the controller is based on a cooperative control method, the problem of intrinsic discontinuity of sliding mode variable structure control is solved, the optimization of performance indexes is achieved, the cooperative control method combines the advantages of sliding mode control and optimal control, and meanwhile the buffeting phenomenon generated by discontinuity in sliding mode variable structure control is improved. Furthermore, based on self-adaptive control, the problem of spacecraft rotational inertia uncertainty and the problem of interference suppression are solved, and spacecraft rapid maneuvering attitude tracking self-adaptive robust high-precision control under the interference condition is achieved.

Description

technical field [0001] The invention relates to a fast maneuvering attitude tracking control method for a spacecraft, and belongs to the technical field of adaptive robust control of a nonlinear control system. Background technique [0002] At present, complex space missions require the spacecraft to have attitude maneuvering and attitude tracking capabilities to ensure that the attitude and command requirements can be achieved after a series of controls. Moreover, with the development of space missions, high-resolution remote sensing satellites have attracted the attention of various countries and fields around the world because of their extremely high spatial resolution in both full-spectrum and multi-spectral bands. With the continuous improvement of user requirements for high-resolution remote sensing satellites, while pursuing high spatial resolution, higher requirements are put forward for the satellite's rapid response capability, earth observation efficiency, and ima...

AI Technical Summary

Problems solved by technology

[0003] Most of the traditional attitude tracking control is PID control or improved PID control, optimal control, variable structure control method, robust control, etc. The design of PID controller is simple but the effect is general; the optimal control can achieve the optimal but robust performance index. The robustness of the variable structure control is relatively good, but it will cause the control output to jitter; the order of the robust control controller is relatively high, and it is rarely used in the actual satellite attitude control system

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