Conventional aircraft model-based lateral-directional controller area design method

Abstract

The invention discloses a conventional aircraft model-based lateral-directional controller area design method, which is used for solving the technical problem of incapability of directly determining the whole stability of a given flight area by the conventional controller design method. According to the method, a trimming control plane, an angle of incidence of airflow and an angle of sideslip for the stable circling under a given turning radius when the altitude and mach number of a control target are given are obtained through aerodynamic force and a moment equation, the area stability of a system is determined by adopting a phase plane analysis model, and the structure and parameters of a feedback controller are determined on the basis of the area stability to directly control the lateral-directional movement of an aircraft, so that inaccurate approximation such as the negation of aerodynamic action in the moment equation is avoided, the controller can ensure the stability of the aircraft in the whole design area, and the problems of instable and unsafe flight and the like caused by the analysis model can be reduced and even solved.

Description

technical field [0001] The invention relates to a method for designing an aircraft controller, in particular to a method for designing a region of a lateral course controller based on a conventional model of an aircraft. Background technique [0002] The basic purpose of flight control is to improve the stability and maneuverability of the aircraft, thereby improving the ability to perform tasks; in recent decades, with the continuous improvement of aircraft performance, great changes have taken place in flight control technology, and active control technology has emerged , integrated control technology, autonomous flight control technology and other advanced flight control technologies, the flight control system and avionics system have a highly integrated trend. Modern high-performance aircraft put forward higher requirements for the flight control system, and it is becoming more and more difficult to design the flight control system of advanced aircraft using classical co...

AI Technical Summary

Problems solved by technology

[0003] In order to overcome the deficiency that the existing controller design method cannot directly determine the overall stability of a given flight area, the present invention provides a method for designing a lateral heading controller area based on a conventional model of an aircraft. When controlling the target altitude and Mach number, the aircraft is in stable level flight, the airflow angle of attack and the trim rudder surface are introduced, the side slip angle and other state feedback controllers are introduced, and the phase plane analysis model is used to determine the regional stability of the system. On this basis, the feedback controller is determined The parameter can directly control the lateral movement of the aircraft, avoiding incorrect approximations such as ignoring the aerodynamic effect in the moment equation, so that the controller can ensure the stability of the aircraft in the entire design area, reducing or even avoiding the error caused by the analysis model. Problems such as stability and unsafe flight occurred

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