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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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2.发明申请公开(公告)号：US20220309122A1
公开(公告)日：2022-09-29
申请号：US17440093
申请日：2020-09-28
Inventor： Ximing SUN , Chen WANG , Xian DU , Lu AI
Abstract: The present invention belongs to the technical field of numerical calculation of aero-engines, and provides an iterative algorithm for an aero-engine model based on hybrid adaptive differential evolution, comprising the following steps: establishing a component-level model of an aero-engine; solving the engine model by a hybrid adaptive differential evolution algorithm; and establishing a dynamic calculation model of the aero-engine. The aero-engine model established by the algorithm of the present invention is widely suitable for traditional turbojet engines and turbofan engines, advanced integrated engine propulsion systems and variable cycle engines, can maintain the dynamic model calculation without dead engine or interruption, and satisfies real-time requirements under most operating conditions.
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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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公开(公告)号：US20210201155A1
公开(公告)日：2021-07-01
申请号：US16981682
申请日：2020-02-28
Applicant: DALIAN UNIVERSITY OF TECHNOLOGY
Inventor： Yanhua MA , Xian DU , Ximing SUN , Weiguo XIA
Abstract: An intelligent control method for a dynamic neural network-based variable cycle engine is provided. By adding a grey relation analysis method-based structure adjustment algorithm to the neural network training algorithm, the neural network structure is adjusted, a dynamic neural network controller is constructed, and thus the intelligent control of the variable cycle engine is realized. A dynamic neural network is trained through the grey relation analysis method-based network structure adjustment algorithm designed by the present invention, and an intelligent controller of the dynamic neural network-based variable cycle engine is constructed. Thus, the problem of coupling between nonlinear multiple variables caused by the increase of control variables of the variable cycle engine and the problem that the traditional control method relies too much on model accuracy are effectively solved.
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Patent Agency Ranking
公开(公告)号：US20210189973A1
公开(公告)日：2021-06-24
申请号：US16761031
申请日：2019-06-13
Applicant: DALIAN UNIVERSITY OF TECHNOLOGY
Inventor： Yanhua MA , Xian DU , Rui WANG , Tongjian LIU
Abstract: A bumpless transfer fault tolerant control method for aero-engine under actuator fault is disclosed. For an aero-engine actuator fault, by adopting an undesired oscillation problem produced by an active fault tolerant control method based on a virtual actuator, in order to solve the shortage of the existing control method, a bumpless transfer active fault tolerant control design method for the aero-engine actuator fault is provided, which can guarantee that a control system of the reconfigured aero-engine not only has the same state and output as an original fault-free system without changing the structure and parameters of a controller, to achieve a desired control objective, and that a reconfigured system has a smooth transient state, that is, output parameters such as rotational speed, temperature and pressure do not produce the undesired transient characteristics such as overshoot or oscillation.
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公开(公告)号：US20210156314A1
公开(公告)日：2021-05-27
申请号：US16770801
申请日：2019-11-05
Applicant: DALIAN UNIVERSITY OF TECHNOLOGY
Inventor： Nan DING , Yanhua MA , Yanlei GAO , Xian DU , Rui WANG
Abstract: A method for active fault tolerant control of a turbofan engine control system designs a linear parameter varying gain scheduling robust tracking controller with good dynamic performance. Adaptive estimation of fault amplitude of a sensor and an actuator is realized according to the change of the operating state of the turbofan engine to accurately reconfigure a fault signal. An active fault tolerant control strategy based on a virtual actuator is designed according to a fault estimation result. Without redesigning the controller, through the designed active fault tolerant control strategy, on the premise of ensuring the stability of the control system, a control effect similar to that of the control system without fault is obtained.
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8.发明申请公开(公告)号：US20200063665A1
公开(公告)日：2020-02-27
申请号：US16462504
申请日：2018-01-25
Applicant: Dalian University of Technology
Inventor： Yanhua MA , Xian DU , Ximing SUN
Abstract: An aero-engine full flight envelope model adaptive modification method based on a deep learning algorithm. A dynamic parallel compensator based on a recursive neural network is adopted to compensate the error of the original nonlinear model within the full flight envelope under the condition without aero-engine performance deterioration. A modifier based on a genetic algorithm is also adopted to conduct adaptive adjustment on correction coefficients of health parameters to be modified in the original nonlinear component-level model. The health parameters to be modified are determined by a multi-attribute decision algorithm based on integrated evaluation. The sum of the modified nonlinear component-level model output and the compensator output is consistent with the aero-engine operation test output data. This provides powerful support for the design of aero-engine control systems and fault diagnosis systems.
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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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