Model-free self-adaptive control method for attitude of assembled spacecraft

Abstract

The invention discloses a model-free self-adaptive control method for an attitude of an assembled spacecraft. The method comprises the following steps: S1) establishing a full-format dynamic equivalent linear data model for an attitude movement of a general assembled spacecraft; S2) designing a parameter self-adaptive estimating equation and estimating a pseudo gradient for the pseudo gradient in the full-format dynamic equivalent linear data model; and S3) establishing an error criterion function according to the dynamic equivalent linear data model, and designing a weighting one-step forward controller through a minimizing error criterion function. The dynamic equivalent linear model is established for a general discrete time nonlinear system, and a modified projection algorithm is adopted for performing online parameter estimation for the unknown variable in the dynamic equivalent linear model, so that the attitude determination accuracy of a flexible spacecraft movement simulator is increased.

Description

technical field [0001] The invention relates to the field of combined spacecraft control methods, in particular to a model-free adaptive control method for combined spacecraft attitude. Background technique [0002] With the development of space missions, the task requirements for capturing non-cooperative targets in space are getting higher and higher. After the spacecraft captures the non-cooperative target, it forms a new combined spacecraft with the target. Since the capture operation will produce shock disturbances to the spacecraft, it is necessary to stabilize the combined spacecraft formed after capture. [0003] Since the model parameters of non-cooperative targets are not available, it is difficult to accurately model the combined spacecraft formed after capture. Some traditional control methods can solve control problems with uncertain model parameters, but these control methods need to know the nominal values ​​of model parameters or the upper and lower bounds ...

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to provide a model-free adaptive control method for the attitude of an assembled spacecraft, which overcomes the problems that the assembled spacecraft formed by capturing non-cooperative targets in space is difficult to accurately model and the traditional control method is difficult to effectively use, and establishes a method for The dynamic equivalent linearization model of the general time-discrete nonlinear system, aiming at the unknown variables in the dynamic equivalent linearization model, adopts an improved projection algorithm for online parameter estimation, and constructs the parameter estimation value based on the dynamic equivalent linearization model to The previous step forecast error criterion function, by minimizing the criterion function, the weighted one-step forward adaptive controller of the combined spacecraft is designed, and the design of the controller does not require any model parameter information of the controlled system, which improves the motion simulation of flexible spacecraft attitude determination accuracy

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