Time-varying reliability evaluation method for uncertain PID control system

A control system, uncertainty technology, applied in the direction of controllers with specific characteristics, electric controllers, electrical testing/monitoring, etc.

Active Publication Date: 2019-11-15
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0007] The above analysis is based on the time-invariant model, but the actual response is time-varying, and the reliability will also change with time.

Method used

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  • Time-varying reliability evaluation method for uncertain PID control system
  • Time-varying reliability evaluation method for uncertain PID control system
  • Time-varying reliability evaluation method for uncertain PID control system

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Embodiment 1

[0129] Such as Figure 4 As shown, the 5-DOF mass spring damping system has degrees of freedom only in the direction of horizontal motion, the mass of each mass m=1kg, the spring stiffness k=1000N / m, and the damping c=1N / ms -1 . A horizontal pulse load f(t) with an amplitude of 10000N is applied to the mass 5. Both mass m and stiffness k have uncertainties. Let the horizontal displacement response of mass block 5 be Y(m).

[0130] The open-loop response of the system is as Figure 5 (a) shown. The requirement for the closed-loop response is: at t 0 = After 1s, the displacement amplitude of mass block 5 does not exceed y cr = 0.02m. Optimized to get J min =6.9773, at this time K P =0,K I =0,K D = 5.22. Considering the uncertainty of mass matrix and stiffness matrix, the uncertain variable interval is divided into 5 subintervals for calculation. When the uncertainty of mass matrix and stiffness matrix is ​​5%, the closed-loop response interval is as follows Figure...

Embodiment 2

[0137] Such as Figure 6 Shown is a 10m×4m sheet with a density of ρ=7850kg / m 3 , elastic modulus E = 210GPa, Poisson's ratio μ = 0.3, plate thickness d = 0.1m. The damping adopts Rayleigh damping C=αM+βK, taking Rayleigh damping coefficient α=0.5, β=0.0002. Both mass m and stiffness k have 5% uncertainty. Now, the two corners at the left end of the plate model constrain the translational degrees of freedom in three directions, and the vertical plate at the two corners at the right end applies different loads in the in-plane direction as the initial disturbance. The disturbance load is as follows: Figure 7 As shown in (a), the black circle point is used as the observation position.

[0138] The open-loop response of the system is as Figure 7 (b) shown. The requirement for the closed-loop response is: the displacement amplitude of the observation point does not exceed y cr = 0.3m. Consider applying single-group PID control and applying dual-group PID control, respectiv...

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Abstract

The invention discloses a time-varying reliability evaluation method for an uncertain PID control system. The method is aimed at the PID closed-loop control system with interval uncertain variables. The time-varying reliability is calculated and evaluated by combining a closed-loop response interval. The method comprises the steps as follows: firstly, determining optimal PID parameters of a deterministic system when control force amplitude is the minimum with an optimization algorithm, then calculating the closed-loop response interval with interval uncertainty variables with a subinterval method, and finally, calculating the time-varying reliability in combination with the first crossing theory for reliability evaluation.

Description

technical field [0001] The present invention relates to the technical field of vibration control and reliability evaluation, in particular to a time-varying reliability evaluation method for uncertain PID control systems Background technique [0002] In the process of structural design, especially the design of aerospace structures, vibration is a problem that cannot be ignored. Excessive vibration will cause a series of problems, and severe vibration can lead to a decrease in structural reliability or even destruction. Simply relying on traditional passive vibration reduction methods, such as increasing the size of components and using new materials, will increase the structural weight on the one hand, which is not allowed in the design of aerospace structures; on the other hand, passive control is suitable for high However, it is difficult to achieve the desired effect in the control of low-frequency vibrations, which are common in aerospace structures. Therefore, the ac...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B11/42G05B23/02
CPCG05B11/42G05B23/02
Inventor 王磊刘嘉祥刘亚儒
Owner BEIHANG UNIV
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