Aero-engine adaptive controller design method considering uncertainty

Abstract

The invention belongs to the field of aero-engine control algorithm design, and provides an aero-engine adaptive controller design method considering uncertainty. Aiming at the design of a multivariable self-adaptive controller under the uncertainty of performance degradation, manufacturing work difference, unmodeled dynamics and the like of an aero-engine, a novel identification model selection mechanism is included, the state of a reference model set on the premise is tracked, and the multivariable control requirement of the aero-engine is met. And meanwhile, more-dimensional unknown parameters can be processed on the design of the filter. Besides, two performance indexes with different priorities are selected in an identification model selection mechanism, and the first-level index canbetter reflect the information of the system model, so that the transient performance of the system can also be improved. Finally, a built Simulink simulation structure is convenient to add and modifyan identification model or change system parameters, and is suitable for simulation verification of other systems with unmodeled dynamics and affine terms.

Description

technical field [0001] The invention proposes a method for designing and verifying an adaptive controller aiming at the uncertainties of aero-engine due to performance degradation, manufacturing error and unmodeled dynamics, etc., belonging to the field of aero-engine control algorithm design. Background technique [0002] Based on the background of a certain type of aero-engine control system, the present invention designs and verifies a multi-variable adaptive controller that satisfies the performance of the system in view of the effects of aero-engine performance degradation, manufacturing error, and unmodeled dynamics of the system. [0003] Aeroengine is an important part of aviation aircraft, which greatly affects the performance and safety factors of the aircraft. When the engine runs for a long time, its performance will gradually decline. In practice, it may cause the thrust mismatch of the engines on both sides of the aircraft, causing the aircraft to yaw or other ...

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Problems solved by technology

In addition, regarding the selection of multi-identification models, existing studies mainly use performance indicators with forgetting factors as the basis for selecting identification models, but under this selection mechanism, the finite-time identification model constructed with filters is only used The real parameters of the system are reset to one of the fixed identification models whose parameters can be reset, and the unknown parameters of the system obtained are not associated with the selection mechanism of the identification model

At the same time, the performance index of the traditional identification model switching only considers the identification error at the current moment and the identification error accumulated in the previous period, but the accuracy of the identification model is not only reflected in the above-mentioned state error, but the derivative of the state is often better reflected. The information of the model, so the present invention proposes a performance index using the derivative term of the identification error, so as to better reflect the model information

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