Coordinated turning control method for tailless air vehicle on basis of fusion of multiple controllers

Abstract

The invention discloses a coordinated turning control method for a tailless air vehicle on the basis of fusion of multiple controllers and belongs to the technical field of automatic control over air vehicles. According to the coordinated turning control method for the tailless air vehicle on the basis of the fusion of the multiple controllers, the controllers are divided into inner ring controllers and outer ring controllers, wherein robust self-adaptive nonlinear inverse controllers are used as main controllers by the inner ring controllers, H<8> times optimum controllers are used as compensators by the inner ring controllers, and nonlinear inverse controllers are adopted by the outer ring controllers. According to the kinematics characteristics of the tailless air vehicle in the turning process, multiple control methods are fused, and therefore the problems, such as nonlinear coupling, heading static instability and uncertain disturbance, existing in the turning process of the tailless air vehicle are solved. The tailless air vehicle can complete coordinated turning stably, accurately and rapidly by adopting the control mode that the multiple controllers are coordinated and combined.

Description

technical field [0001] The invention relates to a coordinated turning control method for a tailless aircraft, in particular to a coordinated turning control method for a tailless aircraft based on multi-controller fusion, and belongs to the technical field of aircraft automatic control. Background technique [0002] Coordinated turn means that when the aircraft turns in the horizontal plane, the coupling effect of rolling motion and yaw motion is the least, that is, the sideslip angle is zero and the maneuvering action is to maintain the flight altitude. Tailless aircraft (Tailless Plane), because it cancels the empennage, the target feature size and the weight of the mechanism of the aircraft are greatly reduced, thereby greatly improving its stealth performance. However, after canceling the vertical tail, the aircraft will become statically unstable in heading, and the static rolling stability will also decrease. This leads to the gradual increase of the side slip angle o...

AI Technical Summary

Problems solved by technology

This leads to the gradual increase of the side slip angle of the tailless aircraft when turning, and the additional rolling moment generated by the change of the side slip angle will in turn affect the roll control; at the same time, due to the static instability of the yaw, the side slip angle will continue to increase. large divergence trend, which will seriously affect the flight quality and flight safety of the aircraft

The existing coordinated turning control of tailless aircraft only improves the static instability of the heading by introducing sideslip angle feedback, but does not make the yaw rate of the aircraft body accurately follow the yaw rate change of the velocity vector through accurate feed-forward compensation

In addition, in the actual turning process, the disturbance caused by the external environment and the influence of unsteady aerodynamic force and nonlinear motion coupling between yaw and roll channels will have a non-negligible impact on the stability of the entire aircraft, resulting in the presence of flight hazard

Images