Aircraft guidance and control integrated design method based on preset time sliding mode

Abstract

The invention discloses an aircraft guidance and control integrated design method based on a preset time sliding mode, and belongs to the technical field of aircraft guidance and control. The method comprises the following steps: establishing a guidance and control integration-oriented nonlinear mathematical model of an aircraft; designing an extended state observer, and observing the total disturbance within a preset time; and designing a sliding mode controller, and realizing compensation of observation disturbance and convergence of a control quantity within a preset time. According to the invention, the expansion state observer is designed by applying a preset time theory, so that the observer completes disturbance observation within a preset time; the state tracking and keeping in the preset time are realized; according to the method, convergence is controlled in the preset time, the system state convergence time is not affected by the initial state of the system, the parameters can be preset, and the time delay problem between a guidance loop and a control loop is eliminated on the basis that coupling between aircraft channels is fully considered by using a full-state coupling guidance control integrated architecture.

Description

technical field [0001] The invention relates to an integrated design method for aircraft guidance and control based on a preset time sliding model, and belongs to the technical field of aircraft guidance and control. Background technique [0002] The aircraft has the characteristics of wide airspace and wide speed range. In the process of high dynamic combat in the modern battlefield, the characteristics of strong coupling, nonlinearity and uncertainty of the aircraft are becoming more and more obvious. The response speed and robustness of the traditional guidance and control system design methods are difficult. To meet the mission requirements of high agility and strong confrontation, and the time / frequency coupling characteristics between the guidance loop and the control loop of the aircraft are further intensified, so that the traditional guidance and control system design framework based on "time scale separation" is no longer applicable. Therefore, there is an urgent n...

AI Technical Summary

Problems solved by technology

[0002] The aircraft has the characteristics of wide airspace and wide speed range. In the process of high dynamic combat in the modern battlefield, the characteristics of strong coupling, nonlinearity and uncertainty of the aircraft are becoming more and more obvious. The response speed and robustness of the traditional guidance and control system design methods are difficult. To meet the mission requirements of high agility and strong confrontation, and the time / frequency coupling characteristics between the guidance loop and the control loop of the aircraft are further intensified, which makes the traditional guidance and control system design framework based on "time scale separation" no longer applicable

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