Control method and device for aircraft subjected to class gap lag and output constraint

Abstract

The invention discloses a control method and device for an aircraft subjected to class gap lag and output constraint, and the method comprises the steps of building a nonlinear model of an aircraft system according to the class gap lag output; constructing a controller and an adaptive law of the aircraft system according to the nonlinear model; constructing a Lyapunov equation; verifying the stability of the aircraft system according to the Lyapunov equation; and when the stability meets a preset requirement, simulating the aircraft system to obtain a simulation result. The method is high in precision and stability and can be widely applied to the technical field of aircraft control.

Description

technical field [0001] The invention relates to the technical field of aircraft control, in particular to a control method and device for an aircraft subject to gap-like hysteresis and output constraints. Background technique [0002] With the continuous development of science and technology, drone technology has attracted widespread attention. A helicopter is a typical drone. Among them, the helicopter has the advantages of vertical take-off and landing, flexible maneuverability, small size, low take-off environment requirements, and low-altitude flight, which has attracted more and more researchers' attention and has been successfully applied in many fields. However, because the model system is complex and difficult to establish, and has the characteristics of nonlinearity, underactuation, strong coupling, static instability, etc., and it is inevitably affected by external disturbances during flight, this is its controller. Analysis and design increase the difficulty. ...

AI Technical Summary

Problems solved by technology

In the LQR control method, it is mainly aimed at the linear model of the helicopter, and this type of linear model is to linearize the nonlinear system of the helicopter, which will lead to the lack of stability of the helicopter system in practical applications

In fuzzy control and sliding mode control, most of the fighting spirit is applied in the nonlinear system of the helicopter, but in the actual system, the parameters of the helicopter system model are unknown, which makes the proposed control method have limitations

At the same time, in the helicopter system, there will be errors due to various constraints and lags, which will affect the performance of the system and even lead to system instability.

Images