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

作者： Ge, Yibo Hu, Yaohua Peng, Cong 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

ISBN: (数字)9781839537769

ISBN: (纸本)9781839537769

This paper has studied the redundancy fault-tolerant control (FTC) strategy of dual-winding permanent magnet synchronous machine (DWPMSM) for more electric aircraft applications. The open circuit fault (OCF) diagnosis, the short circuit fault (SCF) diagnosis, and the redundant communication policy are studied. The results show, when the system is normal, the two sets of windings of the DWPMSM work at the same time, and each windings outputs 50% of its own power. When the winding diagnosed as fault, which is shut off from the systems, then the fault signals are transported to the normal winding by redundancy communication function, and the control states of the normal winding are changed. © 2022 IET Conference Proceedings. All rights reserved.

关键词： Winding

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Data-Driven Based Model-Free MPC for DTP-PMSM with Optimized Space Vector

Data-Driven Based Model-Free MPC for DTP-PMSM with Optimized...

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International Conference on Electrical Machines and systems (ICEMS)

作者： Xiaojun Zhang Liang Yan Jiaqiang Yang Weiqiang Sun Yuqi Jia Anqi Situ College of Electrical Engineering Zhejiang University Hangzhou China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing China

ISBN: (数字)9784886864406

ISBN: (纸本)9798350379105

Finite control set model predictive control (FCS-MPC) has been extensively investigated owing to its numerous disadvantage, such as fast response and easy implementation. However, FCS-MPC is highly sensitive to system modeling and parameters, and its performance deteriorate when the system has unmodeled dynamics and parameter mismatches. To address this issue, a data-driven based model-free predictive current control (MFPCC) for dual-three phase permanent magnet synchronous machine (DTP-PMSM) is proposed, which use only the input and output data of the system instead of the accurate mathematical models and parameters. In addition, the virtual voltage vectors (V3s) is utilized to reduce the harmonic current. More specifically, the space vector is optimized for reducing the torque ripple. Simulation investigations on DTP-PMSM platform validate the superiority of the proposed strategy.

关键词： Permanent magnet machines Computational modeling Predictive models Harmonic analysis Vectors Data models Mathematical models Robustness Steady-state Torque measurement

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A strong robustness open-circuit fault diagnosis strategy for novel fault-tolerant electric drive system based on d-q-axis current signal

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Chinese Journal of aeronautics 2021年第10期34卷 115-127页

作者： Xuefeng JIANG Shaoshuai WANG Jie LI Daoyu WU Wenxin HUANG Zhenmao HAN School of Automation Nanjing University of Science and TechnologyNanjing 210094China College of Automation Engineering Nanjing University of Aeronautics and AstronauticsNanjing 210016China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing 211106China

To diagnose the Open-Circuit(OC)fault in the novel fault-tolerant electric drive system,based on d-q-axis current signal,a strong robustness diagnosis strategy is proposed and *** independent power supplies and converters are required in the novel fault-tolerant electric drive system based on Dual-Winding Permanent Magnet Motor(DWPMM),and the system’s reliability,usage ratio and power density have been improved compared to the conventional fault-tolerant motor drive ***,the novel fault-tolerant electric drive system has the OC fault diagnostic false alarms issue when load changes suddenly or under light-load *** it lacks the research on the diagnostic method when the system encounters intermittent OC fault in power *** theory derivation,simulation and experimental verification,it can be concluded that the proposed strong robustness OC fault diagnosis strategy based on d-q-axis current signal can overcome the OC fault diagnostic false alarms issue when load changes suddenly or under light-load *** it can detect and locate the OC fault of single-phase winding in real time,and diagnose the intermittent OC fault of power switches.

关键词： Dual-winding motor Electric drive system Fault-tolerant system Open-circuit fault diagnosis Permanent magnet motor Strong robustness

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Three-dimensional flow field mathematical model inside the pilot stage of the deflector jet servo valve

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Journal of Zhejiang University-science A(Applied Physics & Engineering) 2022年第10期23卷 795-806页

作者： Shuang-lu LI Yao-bao YIN Jiang-yang YUAN Sheng-rong GUO School of Mechanical Engineering Tongji UniversityShanghai 201804China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Aviation Industry Corporation of ChinaNanjing 210061China

A new flow field mathematical model is proposed to describe accurately the flow field structure and calculate the static characteristics of the pilot stage in a deflector jet servo valve(DJSV). The flow field is divided into five regions, a 3D turbulent jet is adopted to describe the free jet region, and a velocity distribution expression of the jet is proposed. The jet entrainment model is put forward in the pressure recovery region to describe the coupling relationship between the pressure in the receiving chamber and the jet flow. The static characteristics, including pressure-flow characteristics, pressure characteristics,and flow characteristics of the pilot stage are obtained. The flow field structure and the static characteristics are verified by finite element analysis(FEA) and experiment, respectively, and the mathematical model results are in good agreement with the experimental and simulation results.

关键词： Deflector jet servo valve(DJSV) Pilot stage Three-dimensional jets Jets entrainment Static characteristics Mathematical model

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Research and Verification of Aircraft Visual Fuel Measurement Method

Research and Verification of Aircraft Visual Fuel Measuremen...

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

作者： Zhu, Hongyu Gao, Shan Shao, Yizhou Nanjing Engineering Institute of Aircraft System AVIC Nanjing China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing China Nanjing Institute of Tourism and Hospitality Nanjing China

ISBN: (数字)9781839537769

ISBN: (纸本)9781839537769

In this paper, a fuel measurement method based on monocular vision is proposed, including image collection, image enhancement and fuel calculation model. The visual sensor was used to collect the fuel image inside the fuel tank, and the image enhancement processing was carried out to reduce the distortion, fuzziness and other interference factors in the original image. A neural network model for fuel calculation based on machine learning was constructed, to mine the remaining fuel contained in the fuel image and realize the mapping from image to fuel data. A validation experiment was designed and carried out, and the effectiveness of the method was verified. © 2022 IET Conference Proceedings. All rights reserved.

关键词： Image enhancement

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A High-Frequency GaN-Based Motor Drive for Aircraft Electro-Mechanical Actuators 18

A High-Frequency GaN-Based Motor Drive for Aircraft Electro-...

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18th IEEE Conference on Industrial Electronics and Applications, ICIEA 2023

作者： Luo, Bin An, Zezhou Shen, Hongming Li, Sihai Guan, Wenqing Zhou, Kai Luo, Guagnzhao Xiao, Xi Zeng, Youhua Northwestern Polytechnical University School of Automation Xi'an China Northwestern Polytechnical University Gansu Key Laboratory of Aeronautical Electro-Mechanical Actuator Lanzhou China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing China Avic Beijing ShuGuang Aviation Electric Co.Ltd Beijing China

ISBN: (纸本)9798350312201

Cascade GaN devices extremely attractive for aircraft EMAs application because it has the high switching frequency, low loss and high temperature operating capability. However, owing to complex device structure and high dv/dt and di/dt characteristics, GaN-based motor drive are more prone to current or voltage overshoots and oscillations, even device breakdown. In this paper, a prototype of 5-kW GaN-based motor drive is demonstrated with 100 kHz switching frequency. The mathematical model of turn-ON dv/dt effect and the turn-OFF di/dt effect of cascode GaN based inverter was established to reveal the occurrence mechanism of false trigger and oscillation. Then a systematic design methodology to design the gate driver and snubber parameters is proposed. Finally, experimental are carried out to validate the proposed design methods. © 2023 IEEE.

关键词： electromechanical actuators

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Study on Performance of Autonomous Power Generation and Refrigeration system of the Jamming Pod

Study on Performance of Autonomous Power Generation and Refr...

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

作者： Luo, Kun Lv, Baohua Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration ShuiGe Road Nanjing China China Avionics Systems co. Itd Shuguangxili Courtyard Beijing China

ISBN: (数字)9781839537769

ISBN: (纸本)9781839537769

The traditional electronic jamming pod depends on the power supply of the carrier. Limited by the power supply of the carrier, its ability of electronic jamming is weak, and the difference between the power supply system of the pod and the carrier makes the loading flexibility of the electronic jamming pod poor, which restricts the improvement of the performance of the electronic jamming pod. Under this background, this paper puts forward three schemes of autonomous power generation and refrigeration integrated system of electronic jamming pod. Based on the proposed system scheme, the system simulation model is established to simulate and compare the maximum effective power generation and refrigeration capacity of electronic jamming pod in the whole flight envelope and the fuel penalty of the system in the whole mission curve. The results show that the maximum effective power generation of system scheme 1 is greater under the same working conditions in the whole flight envelope, and the overall cooling capacity of system scheme 3 is stronger. Under certain power generation and cooling demand, the applicable flight envelope range of system scheme 1 is larger when the altitude is more than 4000m, while the total fuel penalty of system scheme 1 is smaller for the given flight mission curve. © 2022 IET Conference Proceedings. All rights reserved.

关键词： Fuels

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Study On Stress Characteristics Of High-Speed aviation Fuel Pump Based On Fluid-Structure Coupling

Study On Stress Characteristics Of High-Speed Aviation Fuel ...

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

作者： Chen, Ya Tian, Qilong Xu, Sanshu Fuel System Department Nanjing Engineering Institute of Aircraft Systems AVIC Nanjing China The Aviation Electromechanical System Integration of Aviation Science and Technology Key Laboratory Nanjing China

ISBN: (数字)9781839537769

ISBN: (纸本)9781839537769

For the purpose of obtain the stress distribution and deformation of the high-speed aviation fuel pump during operation, and select reasonable rotor material, the calculation of full flow field of the fuel pump at 60000r/min speed is carried out based on the N-S control equation and k-Ε turbulence model, the pressure distribution of the rotating impellers is obtained, and the flow field data is transmitted to the solid domain of the fuel pump. The unidirectional fluid-structure coupling calculation is carried out for the fuel pump of different materials, and the strength performance of the rotating impellers is analyzed. The results show that the stress concentration appears at the joint between the inlet root of blade and hub of the inducer, and the connection between blade and shroud and hub of the centrifugal impeller. The deformation of the leading edge tip of the inducer blade and the middle of outlet in the centrifugal impeller blade is larger. Maximum equivalent stress of inducer exceeds the allowable stress value of aluminum alloy, so the rotating impellers material needed to be replaced with titanium alloy during design to avoid strength damage during high-speed operation. © 2022 IET Conference Proceedings. All rights reserved.

关键词： Deformation

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Simulation Study of Fuel Tank Inerting system

Simulation Study of Fuel Tank Inerting System

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

作者： Wang, Yangyang Wang, Chenchen Fuel System Department Nanjing Engineering Institute of Aircraft Systems AVIC Nanjing China The Aviation Electromechanical System Integration of Aviation Science and Technology Key Laboratory Nanjing China

ISBN: (数字)9781839537769

ISBN: (纸本)9781839537769

The mathematical model of fuel tank inerting system(FTIS) is established in this paper by using neural network method, then the performance of FTIS under the full flight envelope of A320 aircraft is calculated and compared with the experimental data to verify the accuracy of mathematical model, and finally the effect of ASM inlet pressure, ASM inlet temperature, ASM membrane area, fuel load, flow control mode on fuel tank oxygen concentration is analyzed. © 2022 IET Conference Proceedings. All rights reserved.

关键词： Flight envelopes

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Research on Optimization Design of Airborne Hollow Fiber Membrane Core Size

Research on Optimization Design of Airborne Hollow Fiber Mem...

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

作者： Zhou, Yu Jiang, Wen Fuel System Department Nanjing Engineering Institute of Aircraft Systems AVIC Nanjing China The Aviation Electromechanical System Integration of Aviation Science and Technology Key Laboratory Nanjing China

ISBN: (数字)9781839537769

ISBN: (纸本)9781839537769

Airborne nitrogen inerting is the most ideal way to suppress the explosion of aircraft fuel tanks, and hollow fiber membrane inerting is the most economical and efficient airborne nitrogen inerting technology. The size of the membrane core in the hollow fiber membrane module determines the nitrogen production performance, and also determines the space size and weight of the module to a certain extent. This paper mainly studies the factors that restrict the size of the membrane core, analyzes the influence of the effective length of the membrane core, the radius of the membrane core and the filling rate on the nitrogen production performance of the module, and gives the calculation method of the nitrogen production performance and quality of the membrane core, and finally obtains the given Optimal solution for spatial membrane core size. The research results can provide a reference for the subsequent optimization design of the hollow fiber membrane size. © 2022 IET Conference Proceedings. All rights reserved.

关键词： Optimal systems

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