Turbofan engine steady state transition state multivariable control method based on self-disturbance rejection theory

Abstract

The invention relates to a turbofan engine steady state transition state multivariable control method based on a self-disturbance rejection theory, and belongs to the technical field of aero-engine control. The turbofan engine steady state transition state multivariable control method comprises the following steps that firstly, the control quantity and the controlled quantity of a plurality of sets of turbofan engines are preliminarily selected, then a correlation analysis method is used for further determining the control quantity and the controlled quantity which are relatively large in correlation; a tracking differentiator is adopted for planning each group of control instructions into a tracking track, then is taken together with the current state estimated by the expansion state observer to serve as an input of the nonlinear proportional-differential controller an input calculation control amount for nonlinear proportional-differential controller, meanwhile, a proper structure isused for offsetting the expansion state observer to observe the total disturbance including the coupling among the multiple variables, so that a good control effect is achieved. According to the turbofan engine steady state transition state multivariable control method, multi-input multi-output of turbofan engine requirement is met, meanwhile, target for control requirements is achieved accordingto preset trajectory operation, compared with the design method of a traditional control controller, the difficulty is smaller, the number of parameters needing to be adjusted is small, the physicalsignificance is very clear, and the robustness of the system is greatly improved.

Description

technical field [0001] The present invention relates to a turbofan engine steady-state transition state multivariable control method based on the ADRC theory. Specifically, based on the ADRR theory, the multivariable control framework of the aeroengine is established to optimize the turbofan engine at idle and The control effect during the operation process of the above rotational speed belongs to the technical field of aero-engine control. Background technique [0002] The background that the present invention relies on is the control technology of a certain type of twin-rotor turbofan engine. At present, the relevant technologies of my country's aero-engines mostly improve the efficiency of aero-engines from the perspective of materials and structures, and seldom improve and optimize from the control field. Improvements from the perspective of materials and structures can certainly improve the efficiency of turbofan engines, but optimizing it from the control field can be...

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Problems solved by technology

[0009] Aiming at many problems in the design process of the turbofan engine control system in the existing method, such as complex flow and difficult realization of multivariable control depending on the plan, the present invention provides a turbofan engine steady-state transition state multivariable control based on the active disturbance rejection theory method

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