Aircraft track inclination angle control method based on minimum parameter studying method

Abstract

The invention discloses an aircraft track inclination angle control method based on a minimum parameter studying method. The aircraft track inclination angle control method comprises the following four steps; 1, analyzing and modeling a longitudinal aircraft control system; 2, controlling and designing a neural network dynamic surface based on the minimum parameter studying method; 3, testing tracking performance and regulating parameters; and 4, ending the design. In the aircraft track inclination angle control method, for a longitudinal aircraft model, an unknown function of a neural network approximating system is established; the number of parameters to be estimated is reduced by the minimum parameter studying method; the virtual control is gradually designed; a first-order low-pass filter is introduced in each step; and the neural network dynamic surface control is ultimately deduced. A differential explosion phenomenon in a reversal deduction control is overcome, and the rapid and accurate tracking of the aircraft track inclination angle on a preset track can be realized.

Description

(1) Technical field [0001] The present invention relates to a method of controlling aircraft track inclination angle based on the minimum parameter learning method, which is aimed at the longitudinal plane dynamic model of the aircraft, and provides a neural network dynamic surface control method based on the minimum parameter learning method, which is used to control the aircraft The utility model relates to an inclination angle of a track, which belongs to the technical field of flight control. (2) Background technology [0002] The track inclination angle of the aircraft is the angle between the flight speed direction and the horizontal direction, and is an important motion parameter of the aircraft. By stably and accurately controlling the inclination angle of the flight path, not only can the aircraft run according to the predetermined trajectory, but also the operating altitude of the aircraft can be guaranteed. The longitudinal model of the aircraft is a nonlinear st...

AI Technical Summary

Problems solved by technology

However, there are some defects in the feedback linearization method, such as requiring the uncertain part to meet the matching conditions, being sensitive to modeling errors, etc.

Although the backstepping control design can make up for these defects well, there is a phenomenon of "differential explosion"

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