Combination spacecraft posture model-free self-adaptive controller parameter setting method

Abstract

The invention discloses a combination spacecraft posture model-free self-adaptive controller parameter setting method. The method includes following steps: S1, designing a corresponding all-format model-free self-adaptive controller for the posture motion process of a common combination spacecraft; S2, selecting a plurality of reference input to complete a group of closed-loop experiments according to parameter performance index of the controller; S3, utilizing closed-loop experiment result to iteratively calculate optimized controller parameter value. The model-free controller aiming at a common time discretization nonlinear system is built, and an improved iterative feedback setting method is adopted for parameter setting of controller parameters in the model-free controller, so that independent completing ability of spacecraft posture control and controller control accuracy are improved.

Description

technical field [0001] The invention relates to the field of control methods for combined spacecraft, in particular to a method for parameter setting of a model-free adaptive controller for the attitude of a combined spacecraft. Background technique [0002] After the spacecraft captures the non-cooperative target, it will form a combined spacecraft. Since the digital model of the non-cooperative target is unknown, it is difficult to determine the overall model of the combined spacecraft. Since the non-cooperative target may have angular velocity and impact during the capture process, the attitude of the combined spacecraft needs to be stabilized. [0003] The model-free adaptive controller does not require accurate modeling of the controlled object, and can perform dynamic modeling and control only by using the input and output data of the control process. It is suitable for the attitude control process of the combined spacecraft. However, the parameters of the model-free ...

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Problems solved by technology

[0004] The purpose of the present invention is to provide a parameter tuning method for a model-free adaptive controller of an assembled spacecraft attitude, which overcomes the difficulties in determining the parameters of the assembled spacecraft formed by capturing space non-cooperative targets, and the difficulty in determining the initial value of the parameters of the model-free adaptive controller. For the problem of debugging, a full-format model-free adaptive controller for composite attitude control is determined, parameter performance indicators are designed, and a set of closed-loop experiments is designed to obtain optimized controller parameters for the minimized performance indicator function Vector, using iterative tuning method to gradually optimize the controller parameter vector

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