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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...

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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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A Method for Reconstructing the Shape of Wing Panels Based on Fiber Optic Sensors and Tomographic Imaging Principles

A Method for Reconstructing the Shape of Wing Panels Based o...

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Prognostics and system Health Management Conference (PHM-Qingdao)

作者： Jun Zhan Jie Zeng Chao Xiang Jinpeng Cui Cheng Zeng Linfeng Zhu Mingyu Lu State Key Laboratory of Mechanics and Control for Aerospace Structures 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 system jincheng AVIC Nanjing China Changping District Xiaotangshan Future Science and Technology City COMAC Beijing Aircraft Technology Research Institute Beijing China

ISBN: (数字)9798350354010

ISBN: (纸本)9798350354027

The aircraft wing structure shape reconstruction method based on discrete strain information not only provides data support for the digital collaborative health monitoring and prediction technology of wing structure but also helps to improve the aerodynamic shape and flight quality of the aircraft, achieve structural stealth, and enhance the pointing accuracy of the on-board conformal antenna. As result, a wing skin panel shape reconstruction method based on the principle of tomographic imaging and strain information perception is proposed. According to the idea of tomographic imaging, a “non-intrusive” layout form that only requires sensors to be arranged on the periphery of the monitoring area is designed, breaking through the limitation that sensors can not be arranged in the monitoring area under special working conditions. A method for constructing the deflection shape function of the wing skin panel based on the concept of synthetic curvature is proposed, solving the problem of error accumulation and elimination of deformation inversion at non-monitoring points of the measured structure caused by the uncertainty of the limited discrete layout of sensors and the choice of interpolation fitting method. On this basis, a model deformation monitoring and inversion system for wing skin panel based on fiber optic grating sensors is constructed. The experimental results show that under the single-end fixed bending and torsion working condition, the average relative error of the panel model shape reconstruction is 4.17%. Under the double-end fixed double-concentrated load working condition, the average relative error of the shape reconstruction is 8.07%. The wing deformation distribution information reconstructed by the method proposed in this paper can be mapped onto the virtual twin model of the wing, providing technical support for the safety assessment, early warning, and on-condition maintenance of the entire service life of key structures of the aircraft.

关键词： Employee welfare Shape Deformation Layout Imaging Sensors Aircraft Monitoring Image reconstruction Strain

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

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

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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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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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Hydraulic piston pump in civil aircraft: Current status, future directions and critical technologies

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Chinese Journal of Aeronautics 2020年第1期33卷 16-30页

作者： Shengrong GUO Jinhua CHEN Yueliang LU Yan WANG Hongkang DONG Nanjing Engineer Institute of Aircraft System Jincheng AVICNanjing 211100China Aviation Science and Technology Key Laboratory of Aero Electromechanical System Integration Nanjing 211100China School of Transportation Science and Engineering Beihang UniversityBeijing 100083China

The piston pump is the key power component in the civil aircraft hydraulic system,and the most common pump used in the aviation field is the pressure compensated variable displacement *** this review paper,a basic introduction to the civil aircraft piston pump is presented,including the classification,structure,working principle,design features,and achievements by some research ***,the future directions of the aircraft pump are reported from various ***,the critical technologies are analyzed and summarized in detail from six thrust areas:friction couples,noise reduction,inlet boost,thermal management,fault diagnosis and health management,and mechanical ***,the challenges and limitations of the research on the aircraft pump are discussed to provide valuable insight for future scholars.

关键词： Civil aircraft Engine driven pump High pressure Inlet boost Intelligent control Lubricating gaps Piston pumps Pulsation reduction

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

GPIO Based Iterative Learning Control for Manipulators with ...

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第42届中国控制会议

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

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 *** 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 *** 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 *** effectiveness of the proposed control scheme is finally verified by simulation results.

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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...

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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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Thermal Management of Turbine Disc Cavity system Using Ffbpnn and Nsga Ii Algorithm

SSRN

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SSRN 2024年

作者： He, Zhenzong Zuo, Min Liang, Shuang Mao, Junkui College of Energy and Power Engineering Nanjing University of Aeronautics and Astronautics Nanjing210016 China Collaborative Innovation Center for Advanced Aero-Engine Beijing100191 China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing211106 China

This study addresses the thermal management of the turbine disc cavity system (TDCS) by combining the feed-forward backward propagation neural network (FFBPNN) with the non-dominated sorting genetic algorithm II (NSGA II). First, the heat transfer analysis of the TDCS is carried out using the 1D fluid network method and the 2D finite element method. The impact of different cooling air inlet conditions on the heat transfer performance of the TDCS is investigated. The results show that changing the inlet pressure and temperature significantly affects the heat transfer performance of the TDCS, and the TDCS temperature field can be regulated by the inlet parameters. Then, the prediction model based on the FFBPNN is established to predict the heat transfer performance of the TDCS, and satisfactory result is obtained with mean relative error lower than 1.5% and a coefficient of determination higher than 0.998. Finally, the NSGA II is employed to optimize the cool air inlet condition to achieve thermal management of the TDCS. The Pareto solution set and the optimal solution are obtained. The results indicate that the most comprehensive improvement in the heat transfer performance of the TDCS can be achieved by the present technology. © 2024, The Authors. All rights reserved.

关键词： Temperature control

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Design and Analysis of Dual Three-Phase Winding PMSM for Integrated EMA 4

Design and Analysis of Dual Three-Phase Winding PMSM for Int...

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4th IEEE China International Electrical and Energy Conference, CIEEC 2021

作者： Bi, Ying Liu, Qianqian Zhu, Shushu Liu, Chuang Wang, Kai Hu, Yaohua Nanjing University of Aeronautics and Astronautics Department of Electrical Engineering Nanjing China Nanjing Engineering Institute of Aircraft Systems Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing China

ISBN: (纸本)9781728171494

In modern aerospace electromechanical actuators (EMA), the integrated structure has brought many advantages, such as reducing system components and system volume, etc. In this paper, the design of dual three-phase winding permanent magnet synchronous machine (PMSM) for an integrated EMA is addressed. The motor adopts slot pole combination of 12/10 because of a high winding factor and utilization. The motor is integrated with the EMA system, so the size of it is strictly restricted. Under the condition of limited size, the most suitable stator split ratio is found by analytical calculation and then verified through finite element simulation. Then through the analysis and comparison of three winding configurations, the double-layer winding phase shift 180 degree is selected. Finally, in the case of considering the eddy current loss on the rotor, the optimal design is carried out to obtain the optimal output torque and reduce the torque ripple. © 2021 IEEE.

关键词： electromechanical actuators

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