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Method for designing structural vibration PID (Proportion Integration Differentiation) control system based on non-probabilistic reliability optimization

A technology for actively controlling system, structural vibration, applied in the direction of electric controllers, controllers with specific characteristics, etc.

Active Publication Date: 2016-08-24
BEIHANG UNIV
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Problems solved by technology

[0004] The technical problem to be solved by the present invention is: to overcome the disadvantage that the existing PID control cannot handle the uncertainty of the model, and to provide a PID active vibration control system design method based on non-probabilistic reliability optimization, thereby improving the reliability of the PID active control system sex

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  • Method for designing structural vibration PID (Proportion Integration Differentiation) control system based on non-probabilistic reliability optimization
  • Method for designing structural vibration PID (Proportion Integration Differentiation) control system based on non-probabilistic reliability optimization
  • Method for designing structural vibration PID (Proportion Integration Differentiation) control system based on non-probabilistic reliability optimization

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specific Embodiment

[0076] consider as image 3 A certain type of aircraft equipment compartment. Five rigid surfaces and one elastic surface are made of aluminum alloy, elastic modulus E=68GPa, Poisson’s ratio μ=0.3, density ρ=2770kg / m 3 , the structural damping is proportional damping P=αM+βK, α=5.5, β=1.8×10 -5 . The thickness of the elastic surface h 1 =1.8mm, rigid surface thickness h 2 = 20mm. The uncertainties are the thickness and modulus of the elastic plate: h respectively 1 I =[1.6,2.0]mm and E I =[66,70]GPa. Since one sensor and two drivers are placed on the elastic board, the closed-loop system is a multi-input single-output system.

[0077] The first step: according to the structural vibration finite element equation and the transfer function of the PID controller, establish a structural vibration PID active control system, such as figure 1 As shown, there is an initial disturbance in the closed cavity structure, and n microphone sensors are arranged inside the cavity, and...

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Abstract

The invention relates to a method for designing a structural vibration PID (Proportion Integration Differentiation) control system based on non-probabilistic reliability optimization. The method comprises the steps of firstly, establishing a closed-loop system of structural vibration PID control; then, putting forward a structural vibration active PID control system performance non-probabilistic reliability analysis method for the established closed-loop active control system; and performing non-probabilistic reliability optimization on three parameters of the PID controller based on the put-forward non-probabilistic reliability analysis method, and finally obtaining a closed-loop controller meeting the reliability index. According to the method, the parameters of the PID controller are determined from the viewpoint of reliability, so that the problem of indetermination in the design process of the PID controller is solved, and the closed-loop control system can also meet the design requirements under the condition of parameter perturbation.

Description

technical field [0001] The invention relates to the technical field of active control of structural vibration, in particular to a parameter design method of a structural vibration PID controller based on non-probabilistic reliability optimization. Background technique [0002] Active control of structural vibration has become an important issue in aircraft structural design. Structural vibration not only affects the comfort of passengers, but military aircraft also affects the reliability of weapons and equipment due to high levels of vibration and noise. The vibration and noise levels of hypersonic vehicles are sufficient to cause structural acoustic fatigue, damage the aircraft structure, and in more serious cases, damage the electrical equipment and control systems of the aircraft. As for the aerospace structure, the Explorer-I of the United States failed due to the continuous vibration of the antenna, which caused the overall attitude of the satellite to change. Due to...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B11/42
CPCG05B11/42
Inventor 王晓军李云龙邱志平王冲许孟辉王磊仇翯辰陈贤佳
Owner BEIHANG UNIV
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