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

共 252 条记录，以下是101-110 订阅

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Research on Fault-tolerant Operation of Fault-tolerant Permanent Magnet Motor Based on Four-switch Two-phase Fault-tolerant Topology

Research on Fault-tolerant Operation of Fault-tolerant Perma...

引用

International Conference on Power Electronics systems and Applications (ICPESA)

作者： Xuefeng Jiang Siyuan Wang Kaiwen Wang Hongbo Liu Zhijian Wei Zhenmao Han School of Automation Nanjing University of Science and Technology Nanjing China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing China

ISBN: (纸本)9781665486699

Multi - electric aircraft have attracted more and more attention at domestic and abroad in recent years. As the core component of the more-electric aircraft hydraulic system, the partial energy electric pump determines the performance of the aircraft actuating device. However, for the partial energy pump motor system, electrical faults exist objectively, and after the faults, the system will not run stably. In this paper, a fault-tolerant permanent magnet motor(FTPMM) drive system based on four-switch two-phase (FSTP) fault-toleranttopology is proposed. The principle of fault-tolerant control(FTC) before and after the fault is analyzed by means of constant magnetomotive force, and the FTC strategy for winding open-circuit(OC) and short-circuit(SC) faults of the electric drive system is proposed. Through theoretical research, simulation analysis and verification, It is verified that the FTPMM drive system based on the four-switch two-phase fault-tolerant topology can not only perform FTC for winding OC faults, but also perform FTC for winding SC faults. This improves the reliability of the avionics transmission system.

关键词： Fault tolerance Analytical models Torque Magnetic cores Fault tolerant systems Windings aerospace electronics

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Numerical And Experimental Investigations On Cavitation Characteristics Of Inducer And Impeller Combination Fuel Pumps

Numerical And Experimental Investigations On Cavitation Char...

引用

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

作者： Tian, Qilong Lin, Chengwei Hu, Rongxia Ya, Chen Xu, Sanshu Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing211106 China Nanjing Engineering Institute of Aircraft Systems AVIC Nanjing211106 China The Third Military Representative Office of the Shanghai Bureau of the Air Force Equipment Department in Nanjing Nanjing211106 China

ISBN: (数字)9781839537769

ISBN: (纸本)9781839537769

The aviation fuel pump is a significant accessory for aircraft fuel system. Cavitation resistance is very important for aviation fuel pumps. However, most of the current optimization work for centrifugal pumps only focuses on hydraulic efficiency, which may lead to poor cavitation performance. Therefore, it is necessary to explore effective solutions to improve the cavitation performance of the pump without reducing the efficiency of the pump. To enhance the anti-cavitation capability of the pump and reduce hydraulic loss, the paper try to combine the inducer and impeller. Simulations and external characteristics experiments are carried out. Static pressure and the vapor volume fraction distributions on the inducer and the impeller of the pump under various operation conditions are obtained. At the same time, the curves for the drops of the head coefficients obtained from experiments and calculations are also quantitatively compared, which shows that the numerical simulation of the cavitation performance of the fuel pump is in good agreement with the experimental results. The maximum error of both simulation and experiment is less than 6%, which is within the allowable error range. It indicates that the numerical calculation method adopted can better predict the cavitation performance of the fuel pump. © 2022 IET Conference Proceedings. All rights reserved.

关键词： Cavitation

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Simulation Analysis of Electromagnetic Output Force of Linear Motor with Single Magnetic Steel or Dual Magnetic Steel

Simulation Analysis of Electromagnetic Output Force of Linea...

引用

World Conference on Mechanical Engineering and Intelligent Manufacturing (WCMEIM)

作者： Yu–kun Zhou Hai–ling Qiu Nanjing Engineering Institute of Aircraft Systems Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing Jiangsu China

ISBN: (纸本)9781665473705

Taking the dual magnetic steel force motor used in a certain type of direct drive valve as the research object, the corresponding single magnetic steel force motor is derived according to its structure. Due to the similar structure of the single magnetic steel force motor and the dual magnetic steel force motor, the Ansoft electromagnetic simulation software can be used under the same conditions of armature parameters, air gap width, number of coil turns, and parts materials, etc. By analyzing the difference between the output force of single magnetic and dual magnetic force motors, the characteristics of the electromagnetic output force of both are determined.

关键词： Analytical models Atmospheric modeling Force Valves Magnetic analysis Structural engineering Steel

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Numerical Analysis on the Performance and Axial Force Characteristics of Low Specific Speed and High Head aviation Fuel Pump

Numerical Analysis on the Performance and Axial Force Charac...

引用

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

作者： Han, Zhenrong Tian, Qilong Fan, Hongxing Chen, Ya Cui, Zongtai Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing211106 China Nanjing Engineering Institute of Aircraft Systems AVIC Nanjing211106 China The Third Military Representative Office of the Shanghai Bureau of the Air Force Equipment Department in Nanjing Nanjing211106 China

ISBN: (数字)9781839537769

ISBN: (纸本)9781839537769

The research on the axial force is an important issue for the fuel pump. For the aviation fuel pumps with low specific speed and high head, due to the larger projection area of its impeller cover, and the higher fluid pressure in the pump cavity are more likely to cause an excellent axial force. The performance and axial force characteristics of low specific speed and high head aviation fuel pump was numerically simulated and analyzed. The results of the study showed that the main parts of the fuel pump that generate axial force are the front cover, the rear cover, the impeller and the inducer. The axial force can be reduced by increasing the diameter of the rear cover labyrinth ring and adding the balancing holes. Thus, reducing the loss of the fuel pump and improving the hydraulic efficiency, and the problem of excessively high temperature of the fluid in the pump is solved. This study is helpful to improve the operation stability of fuel pump, and provide reference for subsequent research. © 2022 IET Conference Proceedings. All rights reserved.

关键词： Fuels

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PERFORMANCE SIMULATION OF THE CHANNEL OF AIRBORNE CORRUGATED PLATE-FIN PHASE CHANGE HEAT STORAGE HEAT EXCHANGERS

PERFORMANCE SIMULATION OF THE CHANNEL OF AIRBORNE CORRUGATED...

引用

2024 CSAA/IET International Conference on Aircraft Utility systems, AUS 2024

作者： Sun, Zhichuan Xie, Yixuan Yuan, Jiaqi Liu, Ming Rui, Xin Peng AVIC Nanjing Engineering Institute of Aircraft Systems No. 33 Shuige Road Nanjing China Aviation Key Laboratory of Science and Technology on Aero Utility System Integration No.33 Shuige Road Nanjing China The Third Military Representative Office of Air Force Equipment Department in Nanjing No. 33 Shuige Road Nanjing China

Some airborne electronic devices having high power during their short work cycles will produce tens to hundreds of kilowatts of waste heat. In order to solve their thermal management problem, phase change heat storage heat exchangers are widely used to storage the high-power thermal load in a short time and then release it in a long time. Hence, a research on the heat storage performance of an aluminium alloy three-channel corrugated plate-fin heat exchanger was done based on computer simulation and modeling. Results reveal that there exist three regions within this heat exchanger containing "Low-Efficiency Heat Storage Zone", "High-Efficiency Heat Storage Zone" and "Temperature Control Buffer Zone". In short, the temperature of hot fluid flowing through the heat exchanger usually exhibits a phenomenon of rapid decrease in the middle and slow drop at both ends along the flow direction. It was found that the hot fluid outlet temperature decreases with an increase in the fin height of the phase change material channel, and rises with an increase in the fluid channel fin height or fin pitch of all the channels. In addition, a low temperature-control accuracy period of 2 to 3 seconds during the initial operation was also found. © The Institution of Engineering & technology 2024.

关键词： Fins (heat exchange)

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Fault Redundancy Active Removal Fault-tolerant Strategy for Triple-redundancy PMSMs

Fault Redundancy Active Removal Fault-tolerant Strategy for ...

引用

IEEE Student Conference on Electric Machines and systems

作者： Zhiwei Pan Yaohua Hu Shushu Zhu College of Automation Engineering Nanjing University of Aeronautics and Astronautics Nanjing China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing Engineering Institute of Aircraft Systems Nanjing China

The reliability requirements of the aviation electromechanical actuator system are high, and the three-redundancy motor is often used to provide reliable propulsion power. The triple-redundancy PMSMs is composed of a nine-phase stator winding and a permanent magnet rotor. When a redundancy fails, the fault redundancy is actively removed, and the use of other redundancy can still maintain the normal operation of the system to ensure that the entire system can maintain normal operation. However, the traditional 3-dq modeling method ignores the mutual inductance and flux linkage coupling between different windings, and it is difficult to achieve a smooth transition of redundancy removal. The purpose of this paper is to propose a decoupling control method for multi-stator modeling, which eliminates the cross-coupling of mutual inductance between redundancy and retains the modular control characteristics of 3-dq decoupling. When one or two redundant faults occur, the fault winding is actively removed to reduce the dynamic transition time of speed and torque during redundancy switching and realize the smooth transition of fault winding removal.

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Double ESO Aided Nonlinear Flux Observer for Sensorless Control of PMSM

Double ESO Aided Nonlinear Flux Observer for Sensorless Cont...

引用

International Conference on Electrical Machines and systems (ICEMS)

作者： Zhe Chen Jincheng Li Kun Zhang Mingyuan Zhangliu Hang Zhang Guangzhao Luo School of Automation Northwestern Polytechnical University Xi'an China AVIC/Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing Engineering Institute of Aircraft Systems Nanjing China School of Electrical Engineering Xi'an University of Technology Xi'an China

ISBN: (数字)9784886864406

ISBN: (纸本)9798350379105

As one promising sensorless control algorithm, the nonlinear flux observer is widely used in industries. However, it is sensitive to parameter variations and the gradient search gain can greatly affect its stability. Therefore, this paper proposes an improved nonlinear flux observer, which corrects the stator flux estimation by adding an extended state observer (ESO) to reduce the parameter sensitivity. In addition, the position error compensation is realized by another ESO constructed in estimated rotation frame. The effectiveness of the proposed algorithm is verified experimentally.

关键词： Industries Gradient methods Sensitivity Rotors Error compensation Sensorless control Observers Stators Permanent magnet motors

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Thermal Analysis of a Hybride Excitation Flux-Switching Motor with Water-Cooling system 4

Thermal Analysis of a Hybride Excitation Flux-Switching Moto...

引用

4th IEEE Student Conference on Electric Machines and systems, SCEMS 2021

作者： Ni, Shunjie Zhou, Lihua Li, Hao Cao, Ruiwu Nanjing University of Aeronautics and Astronautics College of Automation Engineering Nanjing China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Avic Nanjing Engineering Institute of Aircraft System Nanjing China

ISBN: (纸本)9781665436816

In this paper, to verify the heat dissipation reliability of a new hybrid excitation flux-switching (HEFS) motor, finite element is used to develop a thermal simulation method of electromagnetic-fluid-thermal coupling. First, general methods of motor temperature analysis and topology of new HEFS motor are introduced. Then, based on motor efficiency map, the maximum loss working status of HEFS motor is analysed to calculate the motor loss, which mainly includes copper loss, iron loss and eddy current loss of permanent magnet. Meanwhile, airflow field and water flow field are analysed respectively to calculate the convective heat transfer coefficient of water-cooling motor. With motor loss and convective heat transfer coefficient, the temperature of motor components at rated condition, maximum loss and maximum effciency are checked to ensure the safety of motor operation, which is also significant to further improve motor performance. © 2021 IEEE.

关键词： Thermoanalysis

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Cooperative Control Strategy of Triple Redundant Motor Based on Virtual Impedance

Cooperative Control Strategy of Triple Redundant Motor Based...

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China International Electrical and Energy Conference (CIEEC)

作者： Zhenwei Hu Yaohua Renhua Jiang Zhiwei Pan Shushu Zhu College of Automation Nanjing University of Aeronautics and Astronautics Nanjing China Aviation Key Laboratory of Science and Technology Aero Electromechanical System Integration Nanjing China AVIC Leihua Electronic Technology Research Institute Wuxi China

The motor for electromechanical actuator has high reliability requirements. This paper studies a triple redundancy permanent magnet synchronous motor with winding redundancy structure. However, the triple redundancy system has the problem of asymmetric channel parameters, which leads to unbalanced winding phase current and affects the reliability of the triple redundancy permanent magnet synchronous motor. In this paper, the possible consequences of parameter asymmetry are analyzed. Aiming at the problem of stator current imbalance caused by parameter asymmetry, a cooperative control strategy based on virtual impedance is proposed. The control strategy compensates the parameters through the virtual impedance adjustment module, which can reduce or even eliminate the parameter asymmetry and realize the balanced control of the winding phase current. At the same time, a Simulink model is built to verify the effectiveness of the control algorithm. Finally, the hardware drive platform and software control algorithm based on YXSpace 2000 semi-physical simulator are built for experimental verification.

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STUDY ON THE APPLICATION OF DUAL-MODE VAPOUR COMPRESSION CYCLE system IN HELICOPTER CABIN THERMAL MANAGEMENT

STUDY ON THE APPLICATION OF DUAL-MODE VAPOUR COMPRESSION CYC...

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2024 CSAA/IET International Conference on Aircraft Utility systems, AUS 2024

作者： Luo, Pinggen Sun, Zhichuan Yuan, Jiaqi Xia, Wenqing China Helicopter Research and Development Institute No.6-8 Hangkong Road Jingdezhen China AVIC Nanjing Engineering Institute of Aircraft Systems No.33 Shuige Road Nanjing China Aviation Key Laboratory of Science and Technology on Aero Utility System Integration No.33 Shuige Road Nanjing China Nanjing University of Aeronautics and Astronautics Nanjing China

With the increasingly widespread application of modern helicopters, the demand for high-quality thermal management in helicopter crew cabins and electronic equipment cabins has become increasingly prominent. To construct the thermal management system architecture for a helicopter's dual-cabin environmental control, the technical paradigm of a dual-mode vapour compression cycle has been referenced, and a new design concept of recycling lubricating oil heat for auxiliary cabin heating has been proposed. Through the method of system simulation modelling and analysis, a dynamic simulation analysis of the system’s cooling/heating performance under extreme weather conditions was conducted. The study explored the dynamic fluctuation characteristics of both active control parameters (expansion valve opening and compressor speed) and passive control parameters (air temperature, cooling capacity, and heating capacity) within the cabin. The simulation results indicate that overshooting the system’s cooling capacity towards a higher level can help rapidly reduce the air temperature within the cabin. Additionally, there are significant differences in the response characteristics of parameters between dual-cabin and single-cabin operational scenarios. Verified by the simulation results, the proposed helicopter dual-cabin environmental control thermal management system exhibits the feasibility for engineering applications. © The Institution of Engineering & technology 2024.

关键词： Signal receivers

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