公开(公告)号：US11965578B2

公开(公告)日：2024-04-23

申请号：US17430548

申请日：2020-10-06

Applicant: DALIAN UNIVERSITY OF TECHNOLOGY

Inventor： Ximing Sun ,  Nan Duan ,  Yuhu Wu ,  Chongquan Zhong

IPC: F16F15/31 ,  F16F15/133 ,  F16F15/134 ,  F16F15/139

CPC classification number: F16F15/31 ,  F16F15/1333 ,  F16F15/13484 ,  F16F15/139

Abstract: A design method for an inerter with adaptively adjusted inertia ratio is based on a lead screw-flywheel inerter, which is to change the positions of mass blocks on a flywheel along the radial direction of the flywheel, so as to change of the moment of inertia of the flywheel, and thus to realize adaptive adjustment of the inertia ratio of the inerter. Specifically, the change of angular velocity of the flywheel is caused by the change of an external force load on a lead screw, a centrifugal force on the mass blocks in spring-mass block structures is changed by the angular velocity, and the positions of the mass blocks in the radial direction of the flywheel is determined by the balanced relation of the centrifugal force and a spring restore force, so that the design purpose is achieved.

公开(公告)号：US11788473B2

公开(公告)日：2023-10-17

申请号：US17052756

申请日：2020-03-19

Applicant: DALIAN UNIVERSITY OF TECHNOLOGY

Inventor： Yanhua Ma ,  Nan Ding ,  Ximing Sun ,  Xudong Zhao

IPC: G06F17/12 ,  F02C9/00 ,  G06N20/10 ,  G06F18/214 ,  G06F18/2411

CPC classification number: F02C9/00 ,  G06F18/214 ,  G06F18/2411 ,  G06N20/10 ,  F05D2200/11 ,  F05D2200/12 ,  F05D2200/13 ,  F05D2200/14 ,  F05D2200/24 ,  F05D2270/02 ,  F05D2270/304 ,  F05D2270/3061 ,  F05D2270/44 ,  F05D2270/71 ,  F05D2270/803

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.

公开(公告)号：US11594991B1

公开(公告)日：2023-02-28

申请号：US17429880

申请日：2021-01-07

Applicant: DALIAN UNIVERSITY OF TECHNOLOGY

Inventor： Ximing Sun ,  Jianyi Zhang

IPC: H02P21/00 ,  H02P21/22

Abstract: A robust position control method for a permanent magnet synchronous motor considering current limitation is provided. The method fully considers the influence of current limitation on a closed loop system in controller design, stability analysis and other theoretical analysis phase, can effectively overcome the influence of system disturbances including system parameters uncertainty and unknown load torque, and finally realize a control objective of accurate tracking of the motor position. More importantly, the technology is a continuous control method which can overcome the inherent chattering problem while having strong robustness of sliding mode control. Meanwhile, a controller designed by the present invention also has the advantages of simple structure, etc. The technical solution proposed by the present invention has wide practical application prospect due to the characteristics of excellent anti-disturbance capability, and simple and feasible structure.

公开(公告)号：US11993370B2

公开(公告)日：2024-05-28

申请号：US17414715

申请日：2020-05-13

Applicant: DALIAN UNIVERSITY OF TECHNOLOGY

Inventor： Yuhu Wu ,  Zongyang Lv ,  Ximing Sun ,  Xiangyu Shen ,  Rui Wang

IPC: B64C29/00 ,  B64C11/48 ,  B64C39/02 ,  B64U10/10 ,  B64U10/25 ,  B64U70/80

CPC classification number: B64C29/0033 ,  B64C11/48 ,  B64C39/024 ,  B64U10/10 ,  B64U10/25 ,  B64U70/80

Abstract: A coaxial tilt-rotor unmanned aerial vehicle (CTRUAV) and a control method thereof. The CTRUAV includes three rotor modules, five rotors with motors and a control system. The three rotor modules are in an inverted triangle layout. The left and right coaxial tiltable rotor modules in the front of the CTRUAV can rotate around the plane of a fuselage. A rear rotor is installed on the rear fixed-axis rotor module. Two pairs of coaxial rotors are respectively installed on the left and right coaxial tiltable rotor modules. The left and right coaxial tiltable rotor modules include an upper rotor and a lower rotor respectively; the upper rotor and the lower rotor have opposite rotation directions and the same rotation speed during the flight. In the two pairs of coaxial rotors, the rotors on the same layers have opposite rotation directions, and the rotors on different layers have the same rotation directions.

公开(公告)号：US11823057B2

公开(公告)日：2023-11-21

申请号：US16981682

申请日：2020-02-28

Applicant: DALIAN UNIVERSITY OF TECHNOLOGY

Inventor： Yanhua Ma ,  Xian Du ,  Ximing Sun ,  Weiguo Xia

IPC: G06N3/084 ,  G06N3/048

CPC classification number: G06N3/084 ,  G06N3/048

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.

公开(公告)号：US11657150B2

公开(公告)日：2023-05-23

申请号：US17887027

申请日：2022-08-12

Applicant: DALIAN UNIVERSITY OF TECHNOLOGY

Inventor： Tianju Sui ,  Qingfeng Liu ,  Ximing Sun

IPC: G06F21/55

CPC classification number: G06F21/554 ,  G06F2221/031

Abstract: A two-dimensionality detection method for industrial control system attacks: collecting data; transmitting the data to a PLC and an embedded attack detection system; uploading, by the PLC, received data to an SCADA system; transmitting, by the SCADA system, the data to the embedded attack detection system after classifying and counting the data; before starting detection, directly reading, by the embedded attack detection system, the data measured by sensors; refining data association relationships and probability distribution characteristics of the sensors of normal operation to complete storage of health data model; after starting detection, in first dimensionality, comparing the data collected directly by the sensors with statistical data of the SCADA system to judge the attacked condition of the SCADA system, and in second dimensionality, comparing the characteristics of the data collected directly by the sensors and counted online with the health data model to judge the attacked condition of the sensors.

公开(公告)号：US11333575B2

公开(公告)日：2022-05-17

申请号：US16629423

申请日：2018-03-01

Applicant: DALIAN UNIVERSITY OF TECHNOLOGY

Inventor： Shuo Zhang ,  Jibang Li ,  Ximing Sun ,  Tao Sun

IPC: G01M13/045 ,  G06K9/62 ,  G06N20/20 ,  G06F17/14 ,  G06K9/00

Abstract: The present invention belongs to the technical field of fault diagnosis of aero-engines, and provides a method for fault diagnosis of an aero-engine rolling bearing based on random forest of power spectrum entropy. Aiming at the above-mentioned defects existing in the prior art, a method for fault diagnosis of an aero-engine rolling bearing based on random forest is provided, wherein test measured data for an aero-engine rolling bearing provided by a research institute are used for establishing a training dataset and a test dataset first; and based on an idea of fault feature extraction, time domain statistical analysis and frequency domain analysis are conducted on original collection data by adopting wavelet analysis; thereby realizing effective fault diagnosis from the perspective of engineering application.

公开(公告)号：US11802895B2

公开(公告)日：2023-10-31

申请号：US17625307

申请日：2021-02-22

Applicant: DALIAN UNIVERSITY OF TECHNOLOGY

Inventor： Ximing Sun ,  Ping Lin

IPC: G01R25/00

CPC classification number: G01R25/005

Abstract: The present invention belongs to the technical field of aviation electrics and electric power, and provides an aircraft grid phase angle tracker based on nonlinear active disturbance rejection, which is used to estimate the grid phase angle on AC side of an aircraft grid. A embedded generator in the aircraft grid is arranged inside a compressor of an aviation gas turbine engine, and the embedded generator is directly coupled with the aviation gas turbine engine so that the AC frequency of the embedded generator varies with the speed of the aviation gas turbine engine. The present invention applies the nonlinear active disturbance rejection technology to the phase angle tracking of the more electric aircraft grid, is simple in operation and high in accuracy, and can realize high-accuracy tracking of the grid phase angle. The method has certain extensibility and can be extended to other fields.

公开(公告)号：US11635734B2

公开(公告)日：2023-04-25

申请号：US16609940

申请日：2019-01-10

Applicant: Dalian University of Technology

Inventor： Yanhua Ma ,  Xian Du ,  Ye Wang ,  Rui Wang ,  Ximing Sun

IPC: G05B13/04 ,  G05B23/02 ,  G06F30/20 ,  G05D1/10

Abstract: The present invention provides an interval error observer-based aircraft engine active fault tolerant control method, and belongs to the technical field of aircraft control. The method comprises: tracking the state and the output of a reference model of an aircraft engine through an error feedback controller; compensating a control system of the aircraft engine having a disturbance signal and actuator and sensor faults through a virtual sensor and a virtual actuator; observing an error between a system with fault of the aircraft engine and the reference model through an interval error observer, and feeding back the error to the error feedback controller; and finally, using a difference between the output of the reference model of the system with fault and the output of the virtual actuator as a control signal to realize active fault tolerant control of the aircraft engine.

公开(公告)号：US11124317B2

公开(公告)日：2021-09-21

申请号：US16629513

申请日：2018-01-26

Applicant: DALIAN UNIVERSITY OF TECHNOLOGY

Inventor： Shuo Zhang ,  Jibang Li ,  Ximing Sun ,  Min Liu

IPC: B64F5/60 ,  G01M15/14 ,  G06N20/10

Abstract: A method for prediction of key performance parameters of an aero-engine in transition condition. Bench test data for an aero-engine in transition condition provided by a research institute is used for establishing a training dataset and a testing dataset first; parameter combination is used for predicting and analyzing engine exhaust temperature based on the idea of information fusion; and the method of rolling windows is used for rolling learning in order to predict the parameters such as low pressure rotor speed and exhaust temperature of an engine from the perspective of practical engineering application.