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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 Method for Reconstructing The Shape of Wing Panels Based on Fiber Optic Sensors and Tomographic Imaging Principles 15

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

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15th IEEE Global Reliability and Prognostics and Health Management Conference, PHM-Beijing 2024

作者： Zhan, Jun Zeng, Jie Xiang, Chao Cui, Jinpeng Zeng, Cheng Zhu, Linfeng Lu, Mingyu State Key Laboratory of Mechanics and Control for Aerospace Structures Nanjing University of Aeronautics and Astronautics No. 29 Yudao Street Nanjing210016 China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing Engineering Institute of Aircraft System Jincheng AVIC Nanjing China COMAC Beijing Aircraft Technology Research Institute Changping District Xiaotangshan Future Science and Technology City Beijing102211 China

ISBN: (纸本)9798350354010

The aircraft wing structure shape reconstruction method based on discrete strain information not only provides data support for the digital collab.rative 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. © 2024

关键词： Fixed wings

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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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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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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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Particle-ellipse IoU loss for accurate drogue detection

Particle-ellipse IoU loss for accurate drogue detection

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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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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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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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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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