Online estimation method for dynamic gain

Abstract

The invention discloses an online estimation method for dynamic gain. The method comprises the following steps: (1) acquiring a dynamic model of a controlled object; (2) establishing a compression function of the controlled object to obtain an error-free compression form of the controlled object; (3) solving the derivative of output y on line by adopting a differentiator; (4) estimating the stateand the input coefficient of the nonlinear controlled object on line; and (5) calculating to obtain the dynamic gain. An error-free compression method of the nonlinear function and the online estimation method of the dynamic gain are provided, multiple types of controlled objects including spacecraft controlled objects, industrial controlled objects and the like are covered, the self-adaptive control problem based on a feature model is solved, the solving problem of the dynamic gain is solved, and the method is universal.

Description

technical field [0001] The invention relates to the field of aerospace, in particular to an online estimation method of dynamic gain. Background technique [0002] The characteristic model theory was proposed by Academician Wu Hongxin in the 1980s. After more than 40 years of research, important progress has been made in theory and application, and a complete set of highly practical adaptive control theory and methods has been formed. This method has been successfully applied in manned spacecraft reentry lift control, rendezvous and docking control, and lunar exploration return control, and the parachute opening accuracy has reached the world's advanced level. Therefore, the characteristic model theory has important application value and application prospect. The theoretical basis of the characteristic model theory is "the sum of all coefficients is equal to 1". "The sum of all coefficients is equal to 1" was also proposed by Academician Wu Hongxin, which refers to the sum...

AI Technical Summary

Problems solved by technology

There are two problems with this method: one is that the value of the nominal trajectory is different from the real flight trajectory; the other is that in the dynamic process, the ratio of the output to the input is directly used, and the derivative of the output is ignored

Both of the above two problems lead to errors in the dynamic gain adopted, which will further affect the accuracy of guidance and control

Currently, there is no solution to this problem

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