Design method of longitudinal controller region based on conventional aircraft model

Abstract

The invention discloses a design method of a longitudinal controller region based on a conventional aircraft model. The design method solves the technical problem that the traditional design method of the controller can not be used for directly determining overall integrity of a given flying region. According to the design method of the longitudinal controller region based on the conventional aircraft model, a balance point is obtained by using aerodynamic force and moment equation when height and Mach number of a control target are given; a regional stability of a system is determined by using a phase plane analysis model, parameters of a feedback controller are determined on the basis, and the longitudinal motion of an aircraft is controlled directly; incorrect approximations are avoided in the moment equation due to the neglects of aerodynamic action and lateral-directional flying influence, so that the controller can guarantee the stability of the aircraft in the whole design region and can be used for reducing and even avoiding the occurrences of problems of unstable and unsafe flying caused by the analysis model.

Description

technical field [0001] The invention relates to a method for designing a longitudinal controller of an aircraft, in particular to a method for designing a region of a longitudinal 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 us...

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 longitudinal controller area based on a conventional model of an aircraft. The airflow angle of attack and the trim rudder surface of the aircraft are stable at the target altitude and Mach number, the airflow angle of attack and other state feedback controllers are introduced, the regional stability of the system is determined by the phase plane analysis model, and the feedback controller is determined on this basis. Parameters, directly control the longitudinal motion of the aircraft, avoiding incorrect approximations such as ignoring the aerodynamic effects and lateral heading effects 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 analysis model. Instability, unsafe flight and other problems occur

Images