Input-limited robust fault-tolerant controller for maximum thrust state of aero-engine

Abstract

The invention provides an input-limited robust fault-tolerant controller for the maximum thrust state of an aero-engine. A maximum thrust state robust controller set fault-tolerant control module generates a control vector v and outputs the control vector v to the input limiting module, the input limiting module generates a limited control input vector u and outputs the limited control input vector u to the aero-engine body, and the gas path part fault diagnosis module diagnoses gas path part faults of an engine. The maximum thrust state robust controller group fault-tolerant control module calculates to obtain an adaptive robust controller and generates a control input vector u. According to the invention, safe operation of the engine is ensured; the real engine is still well controlled in the maximum thrust state under the condition that gas circuit parts of the engine fail; the robustness is high, the performance of the engine in the maximum thrust state is improved to the maximum extent, the engine can stably work in the maximum thrust state when gas circuit parts of the engine break down, the optimal performance is achieved, and the maneuvering performance of the fighter aircraft is improved.

Description

technical field [0001] The invention relates to the technical field of aero-engine control, in particular to a robust fault-tolerant controller for the maximum thrust state of an aero-engine with limited input. Background technique [0002] Aeroengine is a complex nonlinear dynamical system, and its control system is easily affected by operating conditions, engine performance degradation, changes in environmental conditions, and it is difficult to know the effects of external disturbances and measurement noises in advance. Because the working process of an aircraft engine is very complicated, it is difficult to establish an accurate mathematical model, so there are always differences between the mathematical model and the actual system. Therefore, it is necessary to design a robust controller for stabilizing the aero-engine control system with good performance in the presence of external disturbance signals, noise disturbances, unmodeled dynamic characteristics and parameter...

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Problems solved by technology

Therefore, the controller designed according to the engine model in the normal state generally cannot guarantee the performance of the engine when the gas circuit components fail, and even cannot guarantee the closed-loop stability of the control system

[0005] Also, excessively large control inputs can cause damage to the engine, so we need to consider the design of controllers with limited control inputs

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