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

共 250 条记录，以下是81-90 订阅

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Simulation Study of Aircraft Active-Active Hydroelectric Hybrid Power Drive Unit 4

Simulation Study of Aircraft Active-Active Hydroelectric Hyb...

引用

2022 4th International Conference on Mechanical Engineering and Automation, MEA 2022

作者： Mo, Wei Li, Wei Lu, Yueliang Chinese Aeronautical Establishment Graduate School Yangzhou225111 China 609 Research Institute Chinese Aeronautical Establishment Nanjing211106 China AVIC Jincheng Nanjing Engineering Institute of Aircraft System Nanjing211106 China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing211106 China

The Power Drive Unit (PDU) is the power source of the aircraft high-lift system (HLS), which converts hydraulic or electric energy into mechanical energy for output, and deflects the flap/slat through the transmission lines to increase the wing area to improve lift. Two sets of hydraulic motor subsystems working simultaneously are used in the Active-Active PDU of traditional aircraft to improve the reliability of the system. In this paper, an Active-Active Hydroelectric Hybrid Power Drive Unit (HPDU) is designed with a fixed-displacement hydraulic motor and a permanent magnet synchronous motor, the fundamental composition of the HPDU is introduced, the mathematical model of main components is analyzed, the HPDU is modeled based on AMESim, and the function and operation performance are investigated by simulation. The results show that the HPDU can realize the functional design requirements such as forward and reverse rotation and the performance design requirements such as withstanding sudden load within the rated load range during running. © 2023 Institute of Physics Publishing. All rights reserved.

关键词： Hydraulic motors

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Modeling of Aircraft Fuel system and Simulation of Fuel Quality Characteristics Based on AMESim

Modeling of Aircraft Fuel System and Simulation of Fuel Qual...

引用

2022 CSAA/IET International Conference on Aircraft utility systems, AUS 2022

作者： Chen, Guanghao Gu, Lixin Guo, Yibo Niu, Meng Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing Engineering Institute of Aircraft Systems 33 Suige Road Nanjing China Zhengzhou University 100 Kexue Road Zhengzhou China

ISBN: (数字)9781839537769

ISBN: (纸本)9781839537769

In this paper, AMESim software is used to simulate the variation characteristics of fuel quality in the fuel tanks. The results show that under the conditions of different flight attitudes and emergency fuel discharge conditions, there are slight differences in the fuel volume and the height of the fuel in different fuel tank. The fuel can be pumped to the engine normally and the fuel collecting tank can be kept full of fuel. According to the corresponding fuel quality and centroid calculation algorithm, the fuel quality characteristics are simulated and calculated, and the change characteristics of the overall fuel mass center coordinates with time are shown. © 2022 IET Conference Proceedings. All rights reserved.

关键词： Aircraft

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RESEARCH ON THE IMPINGEMENT CHARACTERISTICS OF SUPERCOOLED DROPLETS ON RAM AIR TURBINE 3

RESEARCH ON THE IMPINGEMENT CHARACTERISTICS OF SUPERCOOLED D...

引用

3rd International Conference on Mechanical, aerospace and Automotive Engineering, CMAAE 2023

作者： Chen, Tianxiang Hu, Yaping Wang, Biao Yu, Dongyin College of Energy and Power Engineering Nanjing University of Aeronautics and Astronautics No.29 Yudao Street Qinhuai District Nanjing China 2Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration No.33 Shuige Road Jiangning District Nanjing China

ISBN: (纸本)9781839539954

The Euler-Euler method is used to simulate the two-phase flow field of air and supercooled droplets outside the ram air turbine. The impingement characteristics of droplets on the surface of the ram air turbine are studied, and the effects of inflow velocity and blade pitch angle on the droplet collection coefficient of the turbine surface are analyzed. The calculation results show that the impingement of droplets mainly occurs on the pressure side of the turbine blade, the leading edge of the blade, and the front of the hub, while there is almost no impingement of supercooled droplets on the suction side of the turbine blade. When the inflow velocity increases from 51.4 m/s to 155.7 m/s, the droplet collection coefficient decreases on the leading edge of the turbine blades, while it increases on the surfaces in other regions where the droplet impingement occurs. As the blade pitch angle increases, the droplet collection coefficient on the surface of the turbine blades decreases. © The Institution of Engineering & technology 2023.

关键词： Supercooling

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Simulation Research of Low Fuel Penalty Half-Closed Loop Air Cycle Cooling system

Simulation Research of Low Fuel Penalty Half-Closed Loop Air...

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2022 CSAA/IET International Conference on Aircraft utility systems, AUS 2022

作者： Yang, Changbao Wang, Zhisheng Sun, Zhichuan Gao, Zanjun College of Automation Engineering Nanjing University of Aeronautics & Astronautics Nanjing China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration AVIC Nanjing Engineering Insitute of Aircraft Systems Nanjing China

ISBN: (数字)9781839537769

ISBN: (纸本)9781839537769

In order to reduce the fuel penalty and engine bleed air capacity, under the premise of satisfying cooling and pressure stability demands for airtight cabin, a new half-closed loop air cycle system (ACS) driven by a power turbine was presented. To verify the cooling capacity of this new system, a simulation investigation based on LMS AMESim software was carried out. The simulation modules of turbine cooler, ejector, water separator and heat ex-changers have been established. To avoid the ice barrier at condenser outlet, the heat transfer efficiencies of regenerator and condenser were set at 0.25~0.30. Using the same cooling capacity of F-22 fighter's ACS package as the design parameter, the engine bleed air was found to decrease up to 45% for this new half-closed loop ACS when compared to the open-type ACS in theory. © 2022 IET Conference Proceedings. All rights reserved.

关键词： Cooling

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Robust Deadbeat Finite-Set Predictive Torque and Flux Control for PMSM with Dynamic Model

Robust Deadbeat Finite-Set Predictive Torque and Flux Contro...

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Workshop on Predictive Control of Electrical Drives and Power Electronics (PRECEDE)

作者： Taoming Wang Lijun Chen Mengbo Zhang Xi Xiao Zhe Chen Guangzhao Luo School of Automation Northwestern Polytechnical University Xi’an China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing China

Deadbeat finite-set predictive torque and flux control has the advantages of fast dynamic response and reduced computational burden, but the system robustness is still a challenge in real-time implementation. This paper presents a novel deadbeat finite-set predictive torque and flux control strategy with a modified dynamical predictive model for permanent magnet synchronous motor (PMSM) drives to improve the robustness against mismatched parameters. By establishing sensitivity functions, the robustness of the system can be digitally quantified. The torque and flux predictive models with dynamic weighting factors are proposed to minimize phase current distortions and torque tracking errors caused by parameter variations. Finally, the simulation results verify the improved robustness of the proposed method.

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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...

引用

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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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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Propagation Characteristics of Pressure Pulsation in Hydraulic Hose 5

Propagation Characteristics of Pressure Pulsation in Hydraul...

引用

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...

引用

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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