Elastic body aircraft adaptive constrained tracking control indirect method

Abstract

The invention discloses an elastic body aircraft adaptive constrained tracking control indirect method. The objective of the invention is to solve the technical problem of low possibility of realizing adaptive tracking of reference instruction signals when an elastic body aircraft has input and state saturation constraints. The method includes the following steps that: a feedforward system is designed based on an instruction former, and tracked signals and the pulses of the former are subjected to convolution, so that new forming signals can be obtained and are adopted as the input of a subsequent feedback system; the design of the feedback system is decomposed into a velocity subsystem, a height subsystem and an elasticity subsystem, and the influence of elastic modality in rigid body dynamic is considered as elastic interference, and uncertain parameters and an external disturbance introduction nominal model are used in combination, and therefore, a controlled system can be obtained; and a saturation constrained adaptive control method can be realized for the controlled system through utilizing an instruction filter and an auxiliary system, and tracking for the forming signals in the feedforward system can be realized, and closed-loop system signals can be uniformly and ultimately bounded, and suppression on elastic modality deformation and vibration can be realized.

Description

technical field [0001] The invention relates to an indirect method for adaptive limited tracking control of elastic body aircraft, which is mainly applied to the speed and height tracking control of elastic body aircraft with input and state saturation constraints and the improvement of elastic modal dynamic response, and belongs to the technical field of aircraft control . Background technique [0002] Modern aircraft have high flying speed, wide flight envelope, and strong maneuverability, which make it have various advantages that conventional aircraft do not have. Due to the general use of engine / airframe integration technology, the working state of the engine and the flight state of the aircraft will affect each other, so certain flight parameters of the aircraft (such as angle of attack, Mach number, dynamic pressure, temperature distribution, elasticity, etc.) must be limited. The range of deformation, etc.) makes the propulsion system work in the best state. Second...

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Problems solved by technology

[0003] On the other hand, in pursuit of a higher lift-to-drag ratio, light-weight materials and large thin-walled structures are widely used in aircraft designs. The aerodynamic layout is generally adopted as a slender waverider. Its special structural materials and aerodynamic layout will bring new aeroelasticity. question

Studies have shown that aircraft flutter is a very destructive aeroelastic instability phenomenon. Severe flutter will have a very adverse effect on the fatigue life and flight performance of the aircraft panel structure, and even cause the aircraft to lose weight in a short period of time. Disintegration and destruction

In the prior art, the elastic mode is defined as the system state variable for control, or the elastic effect is treated as uncertainty, neither of which fully utilizes the characteristic information of the elastic mode to improve the elastic dynamic process

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