Design method for wide adaptability of aircraft three-dimensional aviating area controller

Abstract

The invention provides a design method for wide adaptability of an aircraft three-dimensional aviating area controller so as to overcome the defect that an existing controller design method can not ensure stable and safe aviation of an aircraft in a given aviating area. According to the method, an aircraft motion phase plane equation is built, an aircraft stable level aviation flow angle of attack and a trim control surface are obtained in a given control target height and mach number through an aerodynamic force equation and a moment equation, a feedback controller of states such as the flow angle of attack and a sideslip angle is introduced, regional stability of a system is confirmed by adopting a phase plane analyzing model, and parameters of the feedback controller are confirmed based on regional stability. Three-dimensional motion of the aircraft is controlled directly, so that the defect that incorrect approximation such as an aerodynamic force effect is ignored in the moment equation is avoided, stability of the aircraft can be ensured by the controller in the whole designed area, and occurrence of problems such as unstable and unsafe aviation caused by the analyzing model is reduced or even avoided.

Description

technical field [0001] The invention relates to a design method for an aircraft controller, in particular to a wide adaptability design method for an aircraft three-dimensional flight area controller. 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 control theory; in ord...

AI Technical Summary

Problems solved by technology

[0003] In order to overcome the deficiency that the existing controller design method cannot guarantee the stable and safe flight of the aircraft in a given flight area, the present invention provides a wide adaptability design method for the controller of the three-dimensional flight area of ​​the aircraft. The method establishes the motion phase plane equation of the aircraft, This method obtains the airflow angle of attack and trim rudder surface in stable level flight of the aircraft at a given control target height and Mach number through the aerodynamic force and moment equations, and introduces state feedback controllers such as airflow angle of attack and sideslip angle, and adopts the phase plane analysis model Determine the regional stability of the system, determine the parameters of the feedback controller on this basis, and directly control the three-dimensional motion 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 entire design area. The stability of the aircraft reduces or even avoids problems such as instability and unsafe flight caused by the analysis model

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