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CSAA/IET International Conference on aircraft Utility Systems (AUS 2024)

作者： Wenmin Xu Shixu Cao Wenjie Chen Shangxin Yang State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai People's Republic of China COMAC Shanghai Aircraft Design & Research Institute Shanghai People's Republic of China

ISBN: (数字)9781837242108

This article conducts finite element modeling analysis on the nose landing gear, and calculates and analyzes several severe load conditions. Strength tests were conducted on the nose landing gear to verify that the static strength of the landing gear meets the requirements. By comparing the strength test and finite element analysis results of the landing gear, it is shown that the analysis and test results are within the tolerance range, indicating that the finite element analysis and results are reliable and can be used for subsequent analysis.

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Experimental study on airfoil flow separation control via an air-supplement plasma synthetic jet

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Advances in Aerodynamics 2022年第1期4卷 721-742页

作者： Ru-Bing Liu Wen-Tao Wei Hai-Peng Wan Qi Lin Fei Li Kun Tang School of Aerospace Engineering Xiamen UniversityXiamen361102China Fujian Provincial Key Laboratory of Plasma and Magnetic Resonance Xiamen361005China Chengdu Aircraft Design and Research Institute Chengdu610041China Shanghai Aerospace Control Technology Institute Shanghai201100China Rotor Aerodynamics Key Laboratory China Aerodynamics Research and Development CenterMianyang621000China Science and Technology on Plasma Dynamics Laboratory Air Force Engineering UniversityXi’an710038China

An air-supplement plasma synthetic jet(PSJ)actuator increases the air supplemental volume in the recovery stage and improves the jet energy by attaching a check valve to the chamber of a conventional *** explore the flow control effect and mechanism of the air-supplement actuator,via particle image velocimetry experiments in a low-speed wind tunnel,the flow field and boundary layer characteristics of a two-dimensional airfoil surface under different actuation states were compared for different attack angles and jet *** experimental results show that,compared with the conventional actuation state,the jet energy of the air-supplement PSJ is higher and the indirect mixing effect of the counter-vortex sequence produced by the jet-mainstream interaction is ***,the boundary layer mixing effect is better,which can further suppress flow separation and improve the critical flow separation attack ***,increasing the jet momentum coefficient can enhance the flow control *** findings of this study could provide guidance for the flow control application of air-supplement PSJs.

关键词： Plasma synthetic jet Check valve Flow separation Active flow control Air-supplement

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A Cellular Strategy for Eliminating the Failure of Nonlinear Energy Sinks Under Strong Excitation

A Cellular Strategy for Eliminating the Failure of Nonlinear...

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International Conference on Applied Nonlinear Dynamics, Vibration, and control, ICANDVC 2023

作者： Li, Sun-Biao Ding, Hu School of Mechanics and Engineering Science Shanghai Key Laboratory of Mechanics in Energy Engineering Shanghai Institute of Applied Mathematics and Mechanics Shanghai University Shanghai200444 China Shaoxing Institute of Technology Shanghai University Shaoxing312074 China Shanghai Institute of Aircraft Mechanics and Control Zhangwu Road Shanghai200092 China

ISBN: (纸本)9789819705535

Nonlinear energy sinks (NES) have numerous advantages, such as wide vibration bandwidth and excellent vibration reduction performance. However, under high excitation intensity, its high vibration attenuation effect often becomes ineffective. Therefore, exploring methods to address this issue and broaden their application range remains a subject for further research. This paper investigates the dynamic characteristics of systems composed of linear oscillators and multiple NES cells and studies the vibration reduction effect of NES cells using the Complexifiction-Averaging (CxA) method, and the obtained results were numerically verified using the Runge-Kutta (R-K) method. The results show that when NES cells are present in the form of cells, increasing the number of cells can reduce the system's saddle-node (SN) bifurcation region, especially shrinking the frequency island region produced by the system under strong excitation. When the number of cells reaches a certain value, the frequency island of the system disappears. Additionally, regardless of whether the system generates frequency islands or not, increasing the number of cells generally improves the vibration reduction efficiency of NES cells. Thus, the cellular strategy proposed in this paper effectively addresses the ineffectiveness of traditional NES under strong excitation and expands its application range. © The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd. 2024.

关键词： Cells

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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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Performance Analysis of PMSM Based on Improved Trapezoidal Halbach Magnet Arrays 17

Performance Analysis of PMSM Based on Improved Trapezoidal H...

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17th IEEE Conference on Industrial Electronics and Applications, ICIEA 2022

作者： Yu, Zihao Yan, Liang Zhou, Yuchen Liu, Jiatong He, Xinghua Aboelhassan, Ahmed Beihang University School of Automation Science and Electrical Engineering Beijing100191 China Beihang University Science and Technology on Aircraft Control Laboratory Beijing100191 China Beihang University Ningbo Institute of Technology Ningbo315800 China College of Engineering & Technology Electrical and Control Engineering Department Alexandria1029 Egypt University of Nottingham Ningbo China Key Laboratory of More Electric Aircraft Technology of Zhejiang Province Ningbo315100 China

ISBN: (纸本)9781665409841

In this paper, a novel trapezoidal Halbach permanent magnet array is introduced to lessen the output torque ripple of a surface-mounted Permanent Magnet Synchronous Motor (PMSM). Finite Element Method (FEM), core loss, output torque, and torque ripple are examined. The harmonic components of the trapezoidal Halbach magnet arrays are analyzed by the Fast Fourier Transform (FFT). Additionally, a traditional trapezoidal Halbach magnet array-based 2D finite element model of the PMSM is also developed. The findings demonstrate the improved trapezoidal Halbach magnet array's capability to reduce the PMSM's torque ripple by lowering the intensity of the third harmonic of the air-gap flux density. In contrast to the PMSM employing traditional trapezoidal Halbach magnet arrays, the PMSM with the introduced trapezoidal Halbach arrays has a lower torque ripple by 11.84 % and a higher torque by 18.03%, while maintaining similar core loss. © 2022 IEEE.

关键词： Finite element method

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Optimization of Narrow-magnet EMAT for Lamb Waves with Low Distortion

Optimization of Narrow-magnet EMAT for Lamb Waves with Low D...

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Sensor technology and control (ISSTC), International Symposium on

作者： Haifeng Qu Zheng Hu Lishuai Liu Yanxun Xiang Shanghai Key Laboratory of intelligent Sensing and Detection Technology East China University of Science and Technology Shanghai China Shanghai Institute of Aircraft Mechanics and Control Shanghai Key Laboratory of intelligent Sensing and Detection Technology East China University of Science and Technology Shanghai China

ISBN: (数字)9798331541637

ISBN: (纸本)9798331541644

Compared to traditional electromagnetic acoustic transducer (EMAT), the narrow-magnet EMAT extends its meander conductors to the edges and outside of the magnet, hence a wider area of the magnetic field can be used to excite stronger ultrasound waves. Because of the magnetic field inhomogeneity, the classical half-wavelength spacing rule is not suitable for the coil used in the narrow-magnet EMAT. Otherwise, obvious waveform distortions will appear. In this work, the coil conductor spacing correction methodology proposed in previous works is testified for Lamb wave excitations, and a simpler wavelength-based adjustment approach is proposed, where waveforms of low distortions can be obtained. Both approaches are evaluated in simulation and practical experiments, where the Lamb wave amplitude enhancement brought by the coil conductor spacing correction method is more than 157.41%, and the improvement achieved by the proposed wavelength adjustment concept is above 179.34%.

关键词： Coils Acoustic distortion Magnetic field measurement Ultrasonic variables measurement Wavelength measurement Electromagnetic scattering Magnetoacoustic effects Conductors Magnetic fields Electromagnetics

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A Health Assessment Strategy for Helicopter Emergency Floatation System

A Health Assessment Strategy for Helicopter Emergency Floata...

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International Conference on Guidance, Navigation and control, ICGNC 2020

作者： Ding, Qiyan Sun, Zhi Cheng, Lihong Lu, Ningyun Jiang, Bin College of Automation Engineering Nanjing University of Aeronautics and Astronautics Nanjing210000 China Key Laboratory of Aircraft Environment Control and Life Support MIIT Nanjing University of Aeronautics and Astronautics Nanjing210016 China Aviation Key Laboratory of Science and Technology on Life-Support Technology Xiangyang441003 China

ISBN: (纸本)9789811581540

When taking salvaging missions, helicopters play important roles but still face high risk because of complex circumstance. Emergency Floatation System (EFS) is critical to ensure flight safety and conduct emergency rescue for helicopters. To achieve this goal, the reliability of EFS itself is the first concern during its design and development. This paper presents a health assessment strategy for EFS of helicopters, based on multi-signal flow graph modeling, fault tree based diagnosis and Bayesian Networks (BN) based assessment. The simulation results can show that the developed strategy is feasible to evaluate the health status of EFS, which will be helpful for the maintenance division to take proper precautions to avoid potential accidents. © 2022, The Editor(s) (if applicable) and The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.

关键词： Bayesian networks

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Numerical Simulation of UAVs Electronic Equipment Heat Dissipation Under a Low-altitude Environment

Numerical Simulation of UAVs Electronic Equipment Heat Dissi...

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2022 CSAA/IET International Conference on aircraft Utility Systems, AUS 2022

作者： Zhu, Guangya Wang, Mingyuan Gong, Huan Chen, Weijian Key Laboratory of Aircraft Environment Control and Life Support Ministry of Industry and Information Technology Nanjing University of Aeronautics & Astronautics Nanjing China AECC Shenyang Engine Research Institute Shenyang China

ISBN: (数字)9781839537769

ISBN: (纸本)9781839537769

Unmanned aerial vehicles are widely applied in military and daily life with the usage of bleeding air to dissipate heat from electronic equipment through cold-plate cooling, which takes advantage of its simple structure and low weight. However, this cooling method is greatly affected by the flight height of the vehicle, especially in hot regions and at low altitude. To evaluate the cooling effect of the cold plate heat sink under different environmental conditions, a numerical model was established and the following parametric studies were carried out. Firstly, a numerical model of bleeding air cold-plate cooling was established via the COMSOL platform and the mesh was automatically generated for simulation based on the physical field control. The solar radiation intensity in the selected cities was also taken into consideration. Subsequent simulations based on partial adjustment of the model were conducted to evaluate the heat dissipation performance of Unmanned aerial vehicles under low attitude conditions. The results indicated that the heat-generating components should be arranged closer to the cold plate, the working modules should be encapsulated with materials with larger thermal conductivity and the advanced electric modules with less heat generation benefit for Unmanned aerial vehicle thermal management. © 2022 IET Conference Proceedings. All rights reserved.

关键词： Numerical models

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Fade probability simulation analysis for aircraft platform wireless optical communication based on Hermite-Gaussian beam

Fade probability simulation analysis for aircraft platform w...

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2022 International Symposium on Aerospace Engineering and Systems, ISAES 2022

作者： Liu, Xin Zhang, Yu Jiang, Dagang Qin, Kaiyu University of Electronic Science and Technology of China School of Astronautics and Aeronautics Sichuan Chengdu China Aircraft Swarm Intelligent Sensing and Cooperative Control Key Laboratory of Sichuan Province Sichuan Chengdu China

Wireless optical communication technology can provide larger channel capacity for aircraft platforms which has great potentiality. In the application scenario of aircraft platform, the pointing error is inevitable. This study analyzes the fade probability of the link based on Hermite-Gaussian beam by using single-layer phase screen with pointing error simulation method and comparing with Gaussian beam. The higher order Hermite-Gaussian beam shows better link stability performance. Atmosphere turbulence has obvious effect on fade probability when the standard variance of pointing error is small, with the increase of standard variance of pointing error, the major influence factor for fade probability is pointing error rather than atmosphere turbulence. © Published under licence by IOP Publishing Ltd.

关键词： aircraft

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Research on the down locking performance of dual side stay landing gear for large civil aircraft

Research on the down locking performance of dual side stay l...

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CSAA/IET International Conference on aircraft Utility Systems (AUS 2024)

作者： Zihao Zhang Kuan Wang Bing Li Hong Yang Shanghai Aircraft Design and Research Institute Shanghai 201210 People's Republic of China State key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai 200126 People's Republic of China

ISBN: (数字)9781837242108

The side brace and drag brace of the dual side stay landing gear are always in two planes during the process of retracting and extending, which is a typical statically indeterminate mechanism. Taking the prototype of a certain type of civil aircraft landing gear principle as the research object, using LMS virtual *** and AMEsim software to establish a simulation model to analyse the effects of unlocking actuator, down lock spring, and aerodynamic load on the landing gear's locking performance. The research found that the effective size of the annular flow passage of the unlocking actuator can prevent the impact load caused by the rapid deployment of the locking link. A large down-lock spring load can help keep the landing gear in the down position, but if the load is too high, it affects the design of the unlocking actuator. Heading aerodynamic loads can cause delays in locking the AFT side brace of the landing gear, with excessive heading aerodynamic loads even preventing the landing gear from achieving the downlock position. Wing deformation can lead to displacement of the landing gear attachment points, affecting the downlock status of the landing gear.

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