Control method and device, and aero-engine limiting protection control method and device

Abstract

The invention discloses a control method. The existing tight format model-free adaptive control method is improved, an error change rate is added to an input criterion function, so that a control system can respond to a deviation change in advance, and then the robustness of the control system is improved. The invention further discloses a control device and an aero-engine limiting protection control method and device. By adopting the control method disclosed by the invention, the control response speed can be improved, and by adopting the aero-engine limiting protection control method and device disclosed by the invention, the limiting quantity of an aero-engine can return within a limit value within 3s, no oscillation is generated, and the maximum overrun limit is less than 3%; and in addition, the overall control structure adopts an indirect limiting structure that converts the deviation exceeding the limit into reference instruction correction of a main loop controller, so that thelimit loop problem generated in a direct limiting structure and the back and forth switching problem of a controller can be avoided.

Description

technical field [0001] The invention relates to a control method, in particular to an improved model-free adaptive control method and its application in aeroengine control. Background technique [0002] Aeroengine control systems are designed to enable the engine to operate safely, stably and reliably under any working conditions. Generally, during the design process of the control system, the acceleration and deceleration plan of the engine can be made to prevent it from entering abnormal working states such as surge, stall and flameout. However, if there are situations such as engine performance degradation, failure, slow response time of engine actuators, and misoperation caused by human factors, the low-pressure rotor speed of the engine, static pressure at the outlet of the compressor, and exhaust temperature of the low-pressure turbine may exceed their specified limits. Limit value, when any of the above four engine parameters exceeds its limit value, it will cause da...

AI Technical Summary

Problems solved by technology

[0006] Although the traditional model-free adaptive controller can achieve better control effects for nonlinear systems, the aero-engine is a complex system with strong nonlinearity and time-varying, especially when the engine is in a transition state, it will appear in the steady-state The phenomenon that control and transition state control plans are switched, and its output data has complex nonlinear characteristics, making it difficult to obtain good results based on data-driven control

Its performance is that when the traditional model-free adaptive control algorithm is applied to the limit protection control of the aero-engine, it will respond slowly, oscillate, or even diverge.

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