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

作者： Ke Tan Jiafei Fan Boqian Fan Kang Ji Aviation Key Laboratory of Science and Technology On Aero Electromechanical System Integration Nanjing Engineering Institute of Aircraft Systems AVIC Nanjing People's Republic of China

ISBN: (数字)9781837242108

Drogue detection is widely used in autonomous aerial refueling and drogue control, with high accuracy and speed requirements. However, since the image of the drogue is usually an ellipse with different axis ratios, the Intersection over Union (IoU) based on rectangular bounding boxes can hardly accurately measure the similarity between the predicted region and the ground truth. To solve the above issue, we propose a novel particle-ellipse IoU (PEIoU) loss for drogue detection in this work. By setting particles on the image and calculating the proportion occupied by the overlapping part, an estimation of true IoU for two elliptical regions can be obtained. Furthermore, an improved network based on YOLOv8 was designed, and the PEIoU loss was integrated into the model. Finally, a drogue dataset was created containing real images, which was used to perform experiments. The extensive experiments demonstrate that the method proposed in this paper not only outperforms the baseline but also operates efficiently in real-time on edge devices.

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Optimization of the Structural Parameter in Line-start Permanent Magnet Synchronous Machine for Traction Applications 26

Optimization of the Structural Parameter in Line-start Perma...

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26th International Conference on Electrical Machines and systems, ICEMS 2023

作者： Zou, Hui Hu, Yaohua Zhu, Shushu Avic Aerospace System CO. Ltd General Management Department Beijing China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing Engineering Institute of Aircraft Systems Nanjing China Nanjing University of Aeronautics and Astronautics Center for More-electric-aircraft Power System Nanjing China

ISBN: (纸本)9798350317589

This paper studied the permanent magnet arrangement methods for a 30 kVA line-start permanent magnet synchronous machine for traction applications. By comparing the magnetic flux distribution, no-load starting characteristics, and starting torque of the three structures, the V-shaped structure has the most advantages when all parameters are integrated. At the same time, the selected V-shaped rotor was optimized, such as rotor slot width, slot depth, permanent magnet structure and size. The optimal rotor slot and permanent magnet structure were compared, and the performance of the final machine was analyzed. The simulation results indicate that the machine designed in this paper has the advantages of low starting current and high efficiency. © 2023 IEEE.

关键词： Permanent magnets

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Design and analysis of a Tubular Flux-Switching Permanent Magnet Linear Motor for aviation actuator 5

Design and analysis of a Tubular Flux-Switching Permanent Ma...

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5th IEEE International Electrical and Energy Conference, CIEEC 2022

作者： Shu, Qixuan Zhou, Lihua Cao, Ruiwu Nanjing University of Aeronautics and Astronautics Department of Electrical Engineering Nan Jing China Electromechanical System Integration Avic Nanjing Engineering Institute of Aircraft System Aviation Key Laboratory of Science and Technology on Aero Nan Jing China

ISBN: (数字)9781665411042

ISBN: (纸本)9781665411042

Traditional linear actuators are driven by rotating motors and use a mechanical structure to converts rotational motion into linear motion. Due to the complex transmission mechanism, this kind of actuator is difficult to meet the need of rapid action, high reliability, high frequency response in the aviation field. Therefore, linear motor actuators have received extensive attention from scholars at home and abroad, but traditional linear motors have their own drawbacks. In this paper, a Tubular Flux-Switching Permanent Magnet Linear Motor (TFSPMLM) is proposed, which combines the high efficiency and high power density of the traditional Permanent Magnet Linear Motor (PMLM) with the high reliability of the Switched Reluctance Linear Motor (SRLM). Firstly, a novel segmented secondary structure based on the traditional slotted secondary structure is proposed, and their topological structures and working principles are introduced. Secondly, combined with finite element method (FEM), the two motors are designed and optimized respectively based on the performance requirements of an existing aeronautical actuator. Finally, the FEM is used to analyze and compare the electromagnetic characteristics of the two types of motors. The results show that the novel secondary structure has the advantages of small positioning force, small thrust fluctuation and low back EMF THD, and it is feasible to apply them to this kind of aviation actuator. © 2022 IEEE.

关键词： Finite element method

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Prediction method of compressive strength after impact for fiber reinforced plastic composite based on damage fractal dimension

Prediction method of compressive strength after impact for f...

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

作者： Wen Jiang Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing Engineering Institute of Aircraft Systems AVIC Nanjing 211106 People's Republic of China

ISBN: (数字)9781837242108

The bearing capacity of fiber reinforced plastic (FRP) composite is highly sensitive to low-speed impact damage, making the prediction of compressive strength after impact crucial for their engineering applications. In this study, residual compressive strength tests were conducted on laminates of carbon fiber reinforced plastic (CFRP) 5284RTM/U3160 with three different layups under barely visual inspection damage (BVID). Prior to compression testing, the impact damage morphology of laminates with different layups was captured using C-scanning, and the impact damage morphology was studied based on fractal dimension. The research results indicate that specimens with higher damage fractal dimensions exhibit lower compressive strength after impact. Based on this, a prediction model for the compressive strength of composite materials after impact was proposed, which is based on the fractal dimension of the impact damage morphology. This method takes the impact damage morphology as an equivalent geometric component – Sierpinski carpet, and obtains the area of laminates no longer participating in load-bearing after damage through the damage fractal dimension, thereby obtaining the residual compressive strength of the laminates. The predicted results of the model match well with experimental results, and it does not require impact energy as an input parameter, making it convenient for engineering applications.

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

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

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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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Study on the Impact of Novel Flow Channel Structures With Spherical Obstacles on SOFC Performance

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Kung Cheng Je Wu Li Hsueh Pao/Journal of Engineering Thermophysics 2025年第4期46卷 1343-1346页

作者： Zhao, Weiwei He, Zhenzong Mao, Junkui Liang, Fengli Wang, Zaixing Fu, Yao Nanjing University of Aeronautics and Astronautics College of Energy and Power Engineering 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

To enhance the performance of Solid Oxide Fuel Cells (SOFCs), a new flow channel with spherical obstacles is proposed and compared with traditional designs. It is concluded that compared with the basic straight channel, the current density of SOFC with rectangular baffles and SOFC with spherical obstacles increases by 6.42% and 7.14%, and the total pressure drop increases by 3.62 times and 2.16 times, respectively. It is thus evident that the new SOFC design proposed in this paper can be used for better overall performance. © 2025 science Press. All rights reserved.

关键词： Numerical models

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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...

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

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

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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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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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