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检索条件"机构=Aviation Science and Technology Key Laboratory of Aero Electromechanical System Integration"

共 250 条记录，以下是81-90 订阅

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Semi-Physical Simulation of EHA Electric Drive system

Semi-Physical Simulation of EHA Electric Drive System

引用

China International Electrical and Energy Conference (CIEEC)

作者： ChangBao Mi ZhiWen Zhao JingXing Zhou Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration AVIC Nanjing Engineering Institute of Aircraft Systems Nanjing China Hangzhou Institute of Technology Xidian University Xian China

ISBN: (数字)9798350359558

ISBN: (纸本)9798350359565

Electro-hydrostatic actuator (EHA) electric drive system is commonly used in more electric aircraft (MEA) and can improve aircraft performance. This article designs a high-speed permanent magnet synchronous motor (PMSM) with a rated speed of 12,000 rpm for EHA. It establishes the design and system simulation of a semi-physical real-time simulation model based on the EHA electric drive model, verifying the normal operation of the EHA electric drive system's load spectrum. This provides a reliable basis for the highly integrated and high-performance design of the EHA system, thus improving the research and development efficiency.

关键词： Actuators Atmospheric modeling Reliability engineering Permanent magnet motors Real-time systems systems simulation Aircraft

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Research on Fault-Tolerant Reconstruction technology for aerospace electromechanical systems Based on CPLD

Research on Fault-Tolerant Reconstruction Technology for Aer...

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China International Electrical and Energy Conference (CIEEC)

作者： Xiaokai Zhang ZhiWen Zhao Qian Wei Chunqiang Liu Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration A VIC Nanjing Engineering Institute of Aircraft Systems Nanjing China Hangzhou Institute of Technology Xidian University Xian China

ISBN: (数字)9798350359558

ISBN: (纸本)9798350359565

To address the high reliability requirements of aviation electromechanical control systems, this paper focuses on exploring control reconfiguration strategies for aviation electromechanical control systems. The article first establishes a reconfiguration strategy combining redundancy switching with robustness and adaptive capabilities for typical electromechanical control systems. Building upon this foundation, a fault-tolerant strategy is proposed specifically for the core controller of electromechanical control systems in aviation.

关键词： Adaptive systems Fault tolerant systems Redundancy systems architecture Switches Reconstruction algorithms Control systems

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Propagation Characteristics of Pressure Pulsation in Hydraulic Hose 5

Propagation Characteristics of Pressure Pulsation in Hydraul...

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2021 5th International Conference on Electrical, Automation and Mechanical Engineering, EAME 2021

作者： Meng, Yuzhen Han, Lei Zhao, Wenkui Zhang, Lishan Beijing University of Posts and Telecommunications Beijing China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing China

Most modern aircraft hydraulic systems use variable plunger pumps. The pulsating flow output is its inherent characteristic. The resulting pressure pulsation often causes serious damage to the energy pipeline system and endangers the lives of the occupants. This paper studies the propagation law of hydraulic oil in hydraulic hoses, fully considers the coupling vibration of hydraulic oil high-pressure fluid and flexible solids of the hose, establishes a fluid-solid coupling vibration model of hydraulic hoses, and uses ANSYS for numerical simulation to study different frequencies and pipe bending. Using ANSYS for numerical simulation to study the influence of different frequencies and pipe bending radii on the amplitude of fluid pressure pulsation, after comparative analysis, the law of fluid pressure pulsation propagation in hydraulic hoses is obtained. © 2021 Institute of Physics Publishing. All rights reserved.

关键词： Numerical models

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Multi-input Convolutional Neural Network Fault Diagnosis Algorithm Based on the Hydraulic Pump 5

Multi-input Convolutional Neural Network Fault Diagnosis Alg...

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2021 5th International Conference on Electrical, Automation and Mechanical Engineering, EAME 2021

作者： Zhang, Lishan Han, Lei Meng, Yuzhen Zhao, Wenkui Beijing University of Posts and Telecommunications Beijing China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing China

Convolutional neural network used in fault diagnosis can effectively extract fault features in vibration signals. However, in the feature extraction of mechanical fault diagnosis, usually more than two feature signals including at least axial and radial vibration signals can be extracted. This paper proposes two multi-input convolutional neural network models based on the fault data of the aircraft hydraulic pump including axial and radial vibration. The first is the Independent Input Multi-input Convolutional Neural Network model. The two inputs are respectively used for convolution pooling operation with CNN, and are combined through the concatenate function before the fully connected layer, and then all frames are integrated and flattened by the flatten function. A one-dimensional array, finally enters the fully connected layer and outputs the result through the softmax function. The second is the Combined Input Multiinput Convolutional Neural Network, that is, combine two one-dimensional signals into a twodimensional signal in the input layer of the convolutional neural network and then perform convolution pooling, and finally output the result through the softmax function. The results show that the two models have good accuracy and stability, and the second one has a higher convergence and fitting efficiency than the first one. © 2021 Institute of Physics Publishing. All rights reserved.

关键词： Failure analysis

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Design of the magnetic circuit compensation type of large angle measurement of RVDT

Design of the magnetic circuit compensation type of large an...

引用

CSAA/IET International Conference on Aircraft Utility systems (AUS 2024)

作者： Hongchao Wang Hongyan Jiang Shijie Mao Yin Wang Chao Han Yuqing Zhao Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing Engineering Institute of Aircraft Systems Jincheng AVIC Nanjing Jiangsu 211106 People's Republic of China

ISBN: (数字)9781837242108

In order to meet the need of large angle measurement of actuating system, the miniaturization and dexterity is taken as the design idea. By redesigning the structure of rotor core and stator coil, the measuring angle is expanded without increasing the number of components, the volume and weight of RVDT. In addition, in order to improve the linearity of induced voltage of RVDT, the method of magnetic circuit compensation is adopted. When making the rotor core, tilting its side, the total magnetic flux of RVDT is stable when the rotor core rotates at any angle. By using theoretical analysis, simulation experiment and prototype test, the design of magnetic circuit compensation type of large angle measurement of RVDT is verified.

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Quadrotor Attitude Control Based on Modified Linear Active Disturbance Rejection Control

Quadrotor Attitude Control Based on Modified Linear Active D...

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International Conference on Control and Automation (ICCA)

作者： Biao Wang Chaoying Tang Zhennan Yao Feng Yang Nanjing University of Aeronautics and Astronautics Nanjing China Nanjing University of Aeronautics and Astronautics SEMEI Nanjing China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing China

ISBN: (数字)9798350354409

ISBN: (纸本)9798350354416

Attitude control of a quadrotor unmanned aerial vehicle is still a hot research topic. Active disturbance rejection control attracts more attention recently. This paper takes into account the dynamics of the propulsion system and designs a higher-order active disturbance rejection controller with compensation of partial model information. Simulation and experiment demonstrate that the proposed controller presents better performance and robustness compared with the traditional active disturbance rej ection controller.

关键词： Robust control Attitude control Control design Bandwidth Propulsion Autonomous aerial vehicles Robustness

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Electromagnetic Design of a Six-Phase Low-Inertia Fault-Tolerant Permanent Magnet Synchronous Machine

Electromagnetic Design of a Six-Phase Low-Inertia Fault-Tole...

引用

China International Electrical and Energy Conference (CIEEC)

作者： Ziyu Zhou Yi Sui Xiaoying Qiu Ping Zheng Hui Ma School of Electrical Engineering and Automation Harbin Institute of Technology Harbin China AVIC Nanjing Engineering Institute of Aircraft Systems Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing China

ISBN: (数字)9798350359558

ISBN: (纸本)9798350359565

Multiphase permanent magnet (PM) synchronous machine features the advantages of high reliability and high fault-tolerant capability, which has great potential in the fields like aviation servo and electric vehicles. In order to meet the design criteria of low moment of inertia and high post-fault torque performance, three different rotor structures are analyzed and compared for a low-inertia fault-tolerant permanent magnet synchronous machine(SLIFT-PMSM) by finite-element method. The influence of winding structure on torque performance is investigated, and the winding structure is optimized to improve the post-fault torque performance. The electromagnetic performance of the improved scheme is evaluated under both the normal and fault conditions.

关键词： Fault tolerance Torque Windings Fault tolerant systems Rotors Permanent magnets Torque measurement

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GPIO Based Iterative Learning Control for Manipulators with Time-Varying Disturbances 42

GPIO Based Iterative Learning Control for Manipulators with ...

引用

42nd Chinese Control Conference, CCC 2023

作者： Lu, Huangyuwei Wang, Zuo Sun, Jiankun Xiao, Xi Li, Shihua School of Automation Southeast University Nanjing210096 China Key Laboratory of Measurement and Control of Complex Systems of Engineering Ministry of Education Nanjing210096 China Shenzhen Research Institute Southeast University Shenzhen518063 China School of Artificial Intelligence and Automation Huazhong University of Science and Technology Wuhan430074 China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing211106 China

ISBN: (纸本)9789887581543

To improve the disturbance rejection ability and repetitive tracking accuracy of manipulators, a composite iterative learning control (ILC) scheme via generalized proportional integral observer (GPIO) is proposed. A high-order polynomial is first employed to model the time-varying disturbances that include unmodeled dynamics, parameter uncertainties and load fluctuations. A GPIO is then designed to estimate the disturbances and high-order time derivatives. By introducing estimations into a PD-type ILC at each iteration, a composite control scheme is obtained, such that the undesirable influence of time-varying disturbances can be effectively attenuated in the repetitive tracking process of manipulators. In this paper, the rigorous stability analysis of the closed-loop system is presented to guarantee that the tracking error exponentially converges to zero as the iteration number tends to infinity. The effectiveness of the proposed control scheme is finally verified by simulation results. © 2023 Technical Committee on Control Theory, Chinese Association of Automation.

关键词： Disturbance rejection

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Nonlinear dynamic characteristics analysis of a rotor system supported on aerodynamic bearings 58

Nonlinear dynamic characteristics analysis of a rotor system...

引用

58th International Conference on Vibroengineering

作者： Fu, Yao Wang, Fei AVIC Jincheng Nanjing Engineering Institute of Aircraft Systems Nanjing211106 China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing211106 China College of Aircraft Engineering Nanchang Hangkong University Nanchang China

Due to the compressibility of gas, the aerodynamic bearings supported rotor system has strong nonlinearity. In this paper, the finite difference method is adopted to solve the Reynolds equation of the compressible fluid and obtain the forces of the gas film. Then the dynamic model of the aerodynamic bearing-rotor system is established, and the Runge-Kutta method is applied to solve the nonlinear equations of motion. With theories of nonlinear dynamics, the bifurcation characteristics of the rotor system supported by aerodynamic bearings are studied. Results show that the rotational speed and the unbalance has great influence on the nonlinear characteristics of the rotor, both periodic and non-periodic responses might emerge. Copyright © 2022 Yao Fu, et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

关键词： Finite difference method

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Simulation calculation and optimization of aerial refueling of aircraft fuel system

Simulation calculation and optimization of aerial refueling ...

引用

CSAA/IET International Conference on Aircraft Utility systems (AUS 2024)

作者： Chenchen Wang Yangyang Wang Lixin Gu AVIC Nanjing Engineering Institute of Aircraft Systems The Aviation Electromechanical System Integration of Aviation Science and Technology Key Laboratory Nanjing 211106 People's Republic of China

ISBN: (数字)9781837242108

In order to ensure that the initial design of the fuel system meets the requirements of aircraft aerial refueling and related standards, a simulation model of an aircraft fuel system was established based on the AMESim simulation platform. The aerial refueling process was calculated under given conditions, and the initial design of the fuel system is optimized based on the calculation results. Results showed that both the initial and optimized fuel systems meet the requirements for refueling time , and the requirements of electrostatic protection for the fuel flow rate inside the pipeline and inlet of the fuel tank during refueling. The optimized fuel system has a more similar refueling rate for each fuel tank and can effectively reduce the weig ht of fuel system's pipelines. The calculation results can provide guidance for the initial design of fuel system .

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