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公开(公告)号：US20220276620A1
公开(公告)日：2022-09-01
申请号：US17440052
申请日：2020-09-09
Inventor： Ximing SUN , Sixin WEN , Xian DU , Yanhua MA , Xiaoyu LIU , Yuwen HAO
Abstract: The present invention discloses an improved model-free adaptive control method, in particular to an improved method for a compact dynamic linearization model-free adaptive control based on MIMO systems, and belongs to the field of control algorithm design. Firstly, proportional control is added in CFDL-MFAC to improve the problems of low response speed and large overshoot in the original control system. Secondly, an anti-windup control algorithm of an actuator is added in the above control structure so that the actuator does not conduct transfinite operation when reaching the upper or lower saturation limit and the actuator can quickly make a control response when a control instruction enters an unsaturated region again to improve the control accuracy of the system. Then, it is proved through strict analysis that the improved control algorithm can ensure tracking error and BIBO stability under certain conditions. Finally, the above control algorithm is applied to an aero-engine control system, and the effectiveness and superiority of the above control algorithm can be obtained by numerical experiments.
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公开(公告)号：US20210348567A1
公开(公告)日：2021-11-11
申请号：US17052756
申请日：2020-03-19
Applicant: DALIAN UNIVERSITY OF TECHNOLOGY
Inventor： Yanhua MA , Nan DING , Ximing SUN , Xudong ZHAO
Abstract: The present invention belongs to the technical field of control of aero-engines, and proposes an adaptive boosting algorithm-based turbofan engine direct data-driven control method. First, a turbofan engine controller is designed based on the Least Squares Support Vector Machine (LSSVM) algorithm, and further, the weight of a training sample is changed by an adaptive boosting algorithm so as to construct a turbofan engine direct data-driven controller combining a plurality of basic learners into strong learners. Compared with the previous solution only adopting LS SVM, the present invention enhances the control precision, improves the generalization ability of the algorithm, and effectively solves the problem of sparsity of samples by the adaptive boosting method. By the adaptive boosting algorithm-based turbofan engine direct data-driven control method designed by the present invention.
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公开(公告)号：US20210364388A1
公开(公告)日：2021-11-25
申请号：US17252545
申请日：2019-11-21
Applicant: DALIAN UNIVERSITY OF TECHNOLOGY
Inventor： Ximing SUN , Xian DU , Yanhua MA
Abstract: The present invention provides an improved Smith predictive controller-based aero-engine H∞ algorithm, and belongs to the technical field of aero-engine control and simulation. The present invention first establishes a reasonable small deviation linear model for an aero-engine nonlinear model, and selects the state space model data of a certain operating condition as the controlled object for controller design; selects appropriate performance index weighting function parameters, solves the H∞ output feedback controller, and adjusts the parameters to basically meet the control requirements; and designs a Smith predictive compensator with an improved structure based on a closed-loop feedback control system designed according to the H∞ control law to constitute a compound controller, adds a deviation correction controller designed according to the PID control law to the control system to stabilize the controlled object in view that the prediction model and parameters of the controlled object have large deviations from the real model and parameters, and makes adaptive corrections by comparing the output signals of the controlled object and the model so as to further enhance the robustness of the system.
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4.发明申请公开(公告)号：US20190383221A1
公开(公告)日：2019-12-19
申请号：US16462519
申请日：2018-06-15
Applicant: Dalian University of Technology
Inventor： Xian DU , Yanhua MA , Ximing SUN , Zhimin WANG
Abstract: A design method of aero-engine on-line optimization and multivariable control based on model prediction control realizes aero-engine multivariable control and on-line optimization according to thrust, rotational speed and other needs under the condition of meeting constraints. The first part is a prediction model acquisition layer that continuously establishes a small deviation linear model of an aero-engine near different steady state points based on the actual operating state of the aero-engine in each control cycle and external environment parameters and that supplies model parameters to a controller; and the second part is a control law decision-making layer which is a closed loop structure that consists of a model prediction controller and an external output feedback. The model prediction controller determines the output of the controller at next moment by solving a linear optimization problem according to an engine model in the current state, a control instruction and relevant constraints.
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5.发明申请公开(公告)号：US20210131914A1
公开(公告)日：2021-05-06
申请号：US16967313
申请日：2019-11-28
Applicant: DALIAN UNIVERSITY OF TECHNOLOGY
Inventor： Yanhua MA , Xian DU , Ximing SUN , Yuhu WU , Yanlei GAO
Abstract: A stochastic configuration network based turbofan engine health parameter estimation method is disclosed. The stochastic configuration network based turbofan engine health parameter estimation method designed by the present invention combines the model based Kalman filter algorithm and the data-driven based stochastic configuration network, i.e. using the output of the stochastic configuration network as the compensation of the Kalman filter algorithm, so as to take into account the estimated result of the Kalman filter and the estimated result of the stochastic configuration network and improve the estimation accuracy of the original Kalman filter algorithm when the measurable parameters of the turbofan engine are less than the health parameters to be estimated. In addition, the present invention effectively reduces the accuracy loss caused by the poor structure of the neural network through the stochastic configuration network, and improves the generalization ability of the network.
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Patent Agency Ranking
公开(公告)号：US20200339285A1
公开(公告)日：2020-10-29
申请号：US16604042
申请日：2018-12-11
Applicant: DALIAN UNIVERSITY OF TECHNOLOGY
Inventor： Yanhua MA , Xian DU , Rui WANG , Min LIU , Ximing SUN
IPC: B64F5/60
Abstract: The present invention discloses a method for fault diagnosis of the sensors and actuators of an aero-engine based on LFT, and belongs to the field of fault diagnosis of aero-engines. The method comprises: establishing an aero-engine state space model using a combination of a small perturbation method and a linear fitting method; establishing an affine parameter-dependent linear-parameter-varying (LPV) model of the aero-engine based on the model; converting the LPV model of the aero-engine having perturbation signals and sensor and actuator fault signals into a linear fractional transformation (LFT) structure to obtain an synthesis framework of an LPV fault estimator; solving a set of linear matrix inequalities (LMIs) to obtain the solution conditions of the fault estimator; and designing the fault estimator in combination with the LFT structure to realize fault diagnosis of the sensors and actuators of an aero-engine.
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公开(公告)号：US20200183342A1
公开(公告)日：2020-06-11
申请号：US16462521
申请日：2018-12-11
Applicant: Dalian University of Technology
Inventor： Xian DU , Yanhua MA , Ximing SUN
Abstract: A steady state and transition state multi-variable control method of a turbofan engine based on an active disturbance rejection control theory (ADRC) belongs to the technical field of aero-engine control. Firstly, multiple groups of manipulated variables and controlled variables of a turbofan engine are preliminarily selected, and then the manipulated variables and controlled variables with high correlation are further determined by a correlation analysis method. Each group of control instructions is planned as a tracking trajectory by using a tracking differentiator, and is used as the input of a nonlinear proportional-differential controller together with the current state estimated by the extended state observer to calculate the manipulated variables. This achieves the objective that a turbofan engine requires multi-input and multi-output to operate simultaneously according to a predetermined trajectory and meet the control requirements, and has the advantages of less difficult controller design method, fewer parameters to be tuned.
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公开(公告)号：US20230392556A1
公开(公告)日：2023-12-07
申请号：US18032898
申请日：2021-06-04
Applicant: DALIAN UNIVERSITY OF TECHNOLOGY
Inventor： Ximing SUN , Fuxiang QUAN , Chongyi SUN , Yanhua MA
CPC classification number: F02C9/16 , F04D27/02 , G06N7/02 , F05D2270/707
Abstract: An aero-engine surge active control system based on fuzzy controller switching is provided. The present invention selects a basic controller with the most appropriate current state for switching control according to the operating state of a compressor based on the principle of fuzzy switching, and can realize large-range, adaptive and performance-optimized surge active control. Controllers designed by the present invention realize large-range surge active control through fuzzy switching, so that the effective operating ranges of the controllers are expanded and the reliability of the controllers is improved. The designed controllers can be applied to the active control of surge caused by various causes, so that the adaptability of the controllers is improved and is closer to the actual operating condition of the engine. Some optimization indexes are added in the design process of the controllers, which can realize optimal control under corresponding optimization objectives.
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公开(公告)号：US20210140382A1
公开(公告)日：2021-05-13
申请号：US16764304
申请日：2019-03-15
Applicant: DALIAN UNIVERSITY OF TECHNOLOGY
Inventor： Ximing SUN , Xian DU , Rui WANG , Yanhua MA , Xinyue WANG
Abstract: A Simulink modeling method for a mechanical hydraulic device of an aeroengine fuel regulator is proposed. The Simulink modeling method can implement high precision simulation of a mechanical hydraulic device of an engine fuel conditioning system, and greatly increase the simulation speed as compared with the existing modeling simulation in AMESim; solve the problem of a double-layered nested algebraic loop occurring when the mechanical hydraulic device is modeled in Simulink, and improve the simulation precision of the system. In addition, because of having certain universality, the resolving method for a double-layered nested algebraic loop can be generalized to resolve other types of algebraic loops. Meanwhile, the parameters of the simulation model provided by the present invention can be conveniently modified, and can provide a reference for modeling simulation of mechanical and hydraulic devices of engine fuel conditioning systems of other types.
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10.发明申请公开(公告)号：US20210056244A1
公开(公告)日：2021-02-25
申请号：US16763318
申请日：2019-02-25
Applicant: DALIAN UNIVERSITY OF TECHNOLOGY
Inventor： Ximing SUN , Xian DU , Yanhua MA
Abstract: The present invention belongs to the technical field of modeling and simulation of an aeroengine, and provides a method of modeling, simulation and fault injection for a combined high pressure gear pump for an aeroengine, which comprises: extracting the flow regions of a centrifugal pump and a gear pump in the aeroengine and merging into a combined flow region; dividing the combined flow region into different units according to a working principle; meshing each unit by a finite element analysis method, and setting boundary conditions and media parameters; simulating in Pumplinx to obtain the operation performance of the pumps, and adjusting the lateral clearance of the gear to debug the simulation model till a simulation error is within 5%; and then setting faults based on the debugged model to obtain the change of the operation performance of the pumps under the faults.
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