Controller region design method based on quaternion model of aircraft

Abstract

The invention discloses a controller region design method based on a quaternion model of an aircraft, and the method is used for solving the technical problem that in the conventional controller design method, the entire stability of the given flight region cannot be directly confirmed. The method comprises the following steps: a balance point of a given control objective height and a Mach number per hour can be obtained through aerodynamic force and torque equations; the region stability of the system can be confirmed through adopting a phase plane analysis model; and the parameter of a feedback controller is confirmed based on the region stability. The three-dimensional high incidence motion of the aircraft can be controlled directly, the neglect of aerodynamic force action and other incorrect approximation in the torque equation can be avoided, so that the stability of the aircraft of the entire design region can be guaranteed through the controller, and the problems such as instable flight and unsafe flight caused by the analysis model can be reduced even avoided.

Description

technical field [0001] The invention relates to a method for designing an aircraft controller, in particular to a method for designing a controller area based on an aircraft quaternion model. 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 order to obt...

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 the given flight area, the present invention provides a controller area design method based on the aircraft quaternion model, which obtains the given control target through the aerodynamic force and moment equations The airflow angle of attack and the trim rudder surface of the aircraft are stable at altitude and Mach number, and state feedback controllers such as airflow angle of attack and sideslip angle are introduced, and the phase plane analysis model is used to determine the regional stability of the system. On this basis, the feedback The parameters of the controller directly control the three-dimensional high angle of attack motion of the aircraft, avoiding incorrect approximations such as ignoring the aerodynamic effect in the torque equation, so that the controller can ensure the stability of the aircraft in the entire design area, reducing or even avoiding Analyze the occurrence of problems such as instability and unsafe flight caused by the model

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