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

共 219 条记录，以下是71-80 订阅

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Research On The Layout Plan Of Inerting Gas Filling Inlet And Outler Of A Complex Fuel Tank

Research On The Layout Plan Of Inerting Gas Filling Inlet An...

引用

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

作者： Wang, Chenchen Wang, Yangyang Li, Chaoyue AVIC Nanjing Engineering Institute of Aircraft Systems The Aviation Electromechanical System Integration of Aviation Science and Technology Key Laboratory Nanjing211106 China School of Mechanical and Electrical Engineering Jinling Institute of Technology Nanjing211169 China

ISBN: (数字)9781839537769

ISBN: (纸本)9781839537769

According to the inert gas filling requirements of a certain type of aircraft fuel tank, three different inlet and outlet layout plans are designed. Based on CFD, the simulation calculation of the inert gas filling effect of the fuel tank under different inlet and outlet layout plans is calculated. The changes of the oxygen volume fraction (Vo2) in the gas space in the tank under different inert gas flow rates, concentrations and fuel load are analyzed. The calculations show that with the increase of inerting time, the average Vo2 in the tank decreases, and finally tends to the Vo2 of inert gas. Considering the overall average Vo2 of the tank and the uniform distribution of inert gas in the gas space of each tank, it can be seen that the best inerting performance can be achieved by adopting the inlet and outlet layout plan 3. The calculation results can provide a basis for the optimization of the gas distribution design of the tank inerting system. © 2022 IET Conference Proceedings. All rights reserved.

关键词： Volume fraction

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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...

引用

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...

引用

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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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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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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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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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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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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