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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：US20250052251A1
公开(公告)日：2025-02-13
申请号：US18884715
申请日：2024-09-13
Applicant: DALIAN UNIVERSITY OF TECHNOLOGY
Inventor： Ximing SUN , Chongyi SUN , Fuxiang QUAN , Wei REN , Hongxin LI , Zhibo ZHANG , Mingsui YANG
Abstract: The present invention belongs to the field of aviation compressor control, and relates to an aviation compressor active stabilization control method based on disturbance observation and compensation. Modeling errors and external disturbances of models used in design of a controller are observed, and sub-controllers are individually designed for state variables of interest to compensate for the disturbances, thus to simultaneously solve the problems of rotating stall and surge of an aviation compressor in a variety of complex situations. Partial differential model of the compressor is converted to an ordinary differential equation by Galerkin projection method, partial differential characteristics of the compressor are reserved in the form of disturbances during conversion, and an active stabilization controller of the aviation compressor is designed in combination with disturbance observation and compensation technology, thus to ensure that the models used in the design of the controller have higher accuracy, high robustness and high reliability.
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3.发明公开公开(公告)号：US20240077039A1
公开(公告)日：2024-03-07
申请号：US18025531
申请日：2022-05-11
Applicant: DALIAN UNIVERSITY OF TECHNOLOGY
Inventor： Ximing SUN , Junhong CHEN , Fuxiang QUAN , Chongyi SUN
CPC classification number: F02C9/44 , G05B13/027 , G05B13/042
Abstract: The present invention provides an optimization control method for an aero-engine transient state based on reinforcement learning, and belongs to the technical field of aero-engine transient states. The method comprises: adjusting an existing twin-spool turbo-fan engine model as a model for invoking a reinforcement learning algorithm; to simultaneously satisfy high level state space and continuous action output of a real-time model, designing an Actor-Critic network model; designing a deep deterministic policy gradient (DDPG) algorithm based on an Actor-Critic frame, to simultaneously solve the problems of high-dimensional state space and continuous action output; training the model after combining the Actor-Critic frame with the DDPG algorithm; and obtaining the control law of engine acceleration transition from the above training process, and using the method to control an engine acceleration process.
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