A self-adaptive tuning method for flight control system

Abstract

The invention discloses a flight control system self-adaption parameter adjustment method. In the design process, the structure of a flight control system is fixed; and under the condition that flight envelope changes greatly, and by establishing constraint relation between unknown parameters of the flight control system and poles of a closed loop system, robust self-adaptive parameter adjustment of the flight control system is achieved. The method is characterized by, during the design process, to begin with, performing corresponding performance constraint based on flight qualities, such as bandwidth frequency, time delay, magnitude margin and phase margin, of an aircraft model, and establishing an area meeting flight performance requirements; and then obtaining design parameters, meeting area stabilization requirements, of the flight control system by utilizing the protection mapping theory, meanwhile, automatically generating a controller set meeting the requirements, and thus self-adaption parameter adjustment of the control system is achieved. More importantly, during the parameter adjustment process, not only a single parameter can be adjusted, but also coordinated and integrated design of multiparameters can be achieved, thereby meeting the requirement for multiobjective design parameter adjustment of the flight control system.

Description

technical field [0001] The invention relates to an aircraft control method, in particular to an automatic parameter adjustment method for designing a flight control system by using protection mapping theory to complete self-adaptive adjustment of control system parameters. Background technique [0002] As the requirements of modern flight control systems are getting higher and higher, the traditional methods can no longer meet its complex application requirements, and it is very necessary to realize the adaptive adjustment of flight control system parameters by integrating multi-objective requirements. There are two most commonly used methods in traditional flight control system parameter adjustment. The first form is to use the given linearization model near the equilibrium point to design a corresponding set of linear controllers for synthesis. Variables may be endogenous or exogenous. The second form is based on the linear variable parameter (LPV) technology, which conve...

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Problems solved by technology

However, the first form of interpolation becomes a challenging problem when dynamic compensators or actuators are considered, and more importantly its stability cannot be proven

The second form makes the control system design too conservative, especially when the operating area becomes larger, it may lead to unreachable optimization problems, and it is difficult to achieve the global stability of the closed-loop system

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