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检索条件"机构=Key Laboratory of Aircraft Control Integration Technology"

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Design of Intentional Eye-blink Signal Acquisition and control System Based on Pressure Sensor 7

Design of Intentional Eye-blink Signal Acquisition and Contr...

引用

7th International Conference on Intelligent Computing and Signal Processing, ICSP 2022

作者： Shao, Xueqi Ning, Haonan Yang, Wenjun Niu, Yafeng Southeast University School of Mechanical Engineering Department of Industrial Design Nanjing China National Key Laboratory of Science and Technology on Aircraft Control Xi'an China

ISBN: (纸本)9781665478571

Eye-blink control means that users blink intentionally to realize human-computer interaction. An intentional eye-blink signal acquisition and control system based on flexible pressure sensor is designed, which aims to control the object through simple eye movements such as blinking and winking. The system uses two pressure sensors to collect the blink signals at the orbicularis oculi muscles of the left and right eyes respectively. The software part realizes the acquisition and recognition of six intentional eye-blink signals, and transmits blink-control instruction signals through Bluetooth, so as to realize the control of the remote-controlled vehicle. The advantage of this system is that it is not affected by illumination and does not need GUI interface for control. The availability of the system is qualified after system test. © 2022 IEEE.

关键词： Human computer interaction

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

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

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Prognostics and System Health Management Conference (PHM-Qingdao)

作者： Jun Zhan Jie Zeng Chao Xiang Jinpeng Cui Cheng Zeng Linfeng Zhu Mingyu Lu State Key Laboratory of Mechanics and Control for Aerospace Structures 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 system jincheng AVIC Nanjing China Changping District Xiaotangshan Future Science and Technology City COMAC Beijing Aircraft Technology Research Institute Beijing China

ISBN: (数字)9798350354010

ISBN: (纸本)9798350354027

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

关键词： Employee welfare Shape Deformation Layout Imaging Sensors aircraft Monitoring Image reconstruction Strain

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Research on Traffic Inspection Method in Urban Irregular Area Based on Multi-UAV 23

Research on Traffic Inspection Method in Urban Irregular Are...

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23rd COTA International Conference of Transportation Professionals: Emerging Data-Driven Sustainable Technological Innovation in Transportation, CICTP 2023

作者： Yue, Guanghua Du, Wentao Yue, Jiangfeng Liu, Chenglong Du, Yuchuan Key Laboratory of Road and Traffic Engineering of Ministry of Education Tongji Univ. Shanghai China Henan Wanli Transportation Technology Group Co. Ltd. Xuchang China Aircraft Swarm Intelligent Sensing and Cooperative Control Key Laboratory of Sichuan Province Univ. of Electronic Science and Technology of China Chengdu China

ISBN: (数字)9780784485040

ISBN: (纸本)9780784485040

When multiple unmanned aerial vehicles (UAV) patrol urban traffic status, the complex road network, and high buildings lead to irregularities in the airspace above. In addition, the communication signals and positioning systems between multi-UAV are often easily blocked by buildings and plants. Traditional multi-UAV path planning algorithms cannot guarantee mission reliability. In this paper, we take the actual typical scene of urban environmental traffic inspection as an example and propose a distributed weak-sensing UAV swarm scanning coverage based on the action mechanism of neighboring members in the cluster, combined with the virtual artificial potential field method to constrain the consistent behavior system. This method can realize the adaptive scanning coverage of irregular areas by multi-UAV coordination under limited communication in the urban environment and avoid collisions between UAVs and buildings. It has a good application sweep coverage in urban traffic inspection in the future. © ASCE.

关键词： Inspection

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A Non-central Multi-Agent Routing Protocol of Self-organized Wireless Network for Missile Swarm Communication 11

A Non-central Multi-Agent Routing Protocol of Self-organized...

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11th IEEE Data Driven control and Learning Systems Conference, DDCLS 2022

作者： Lu, Xiaodong Wang, Chenzhao Huo, Junxin Wang, Wei School of Astronautics Northwestern Polytechnical University Xi'an710072 China National Key Laboratory of Science and Technology on Aircraft Control Facri Xi'an710065 China

ISBN: (数字)9781665496759

ISBN: (纸本)9781665496759

As the fast mobility of position and uncertainty of quantity in the missiles swarm, the flooding routing protocol which is widely used in the communication of self-organized wireless network has unsatisfied communication capability and intolerable energy consumption under the large number of communication nodes with complex topology. To suppress these deficiencies, this paper studied a non-central multiagent routing protocol of self-organized network for missile swarm, which could provide random communication between multiple missiles in cooperative engagement. The proposed protocol regards each node as an agent with the capabilities of autonomous perception, independent decision-making and multihop communication. The agents receive the broadcast information with multihop lists from the neighbour nodes and build the connectivity matrix with the multihop depth. Considering the optimization function with communication load and energy consumption of each node, the agents update the forwarding routing table iteratively under the agents' connectivity matrix and right rotation rule. The mathematical simulation results showed that the proposed multiagent routing protocol could effectively reduce the network load and the energy consumption of each node than the flooding routing protocol. © 2022 IEEE.

关键词： Routing protocols

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A RESEARCH OF THE DISCRETE DIGITAL BRAKE VALVE MATCHING DESIGN AND control FOR LARGE aircraft

A RESEARCH OF THE DISCRETE DIGITAL BRAKE VALVE MATCHING DESI...

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2024 CSAA/IET International Conference on aircraft Utility Systems, AUS 2024

作者： Wang, Yi Wu, Shuai Jin, Hongtao Li, Chuandong Gao, Xiaolong Jiao, Zongxia School of Automation Science and Electrical Engineering Beihang University Beijing100191 China National Key Laboratory of Aircraft Integrated Flight Control Beihang University Beijing100191 China Ministry of Industry and Information Technology Beijing100191 China Ningbo Institute of Technology Beihang University Ningbo315800 China Tianmushan Laboratory Hangzhou310023 China

The aircraft braking system is a vital component of the aircraft, responsible for dissipating the kinetic energy of the aircraft and slowing it down to stop. In the field of aircraft braking systems, hydraulic systems with high power-to-weight ratios are currently the preferred choice. The brake control valve is a crucial component of the braking system, regulating the pressure of the essential components. The use of a discrete digital valve, designed to be pollution-resistant and fault-tolerant, can significantly enhance the performance of the braking system. The majority of existing designs and selections for discrete digital valves are based on experience, which may result in the unnecessary increase in system redundancy, volume and weight. This paper analyses the requirements of an aircraft braking system, combining the load situation and actual working conditions to determine the matching design of discrete digital valves. The efficacy of the designed brake valve in terms of performance and braking effectiveness is validated through the construction of a discrete digital valve braking system model. © The Institution of Engineering & technology 2024.

关键词： aircraft hydraulic systems

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Numerical Simulation of Rain Accumulation on aircraft Windshield

Numerical Simulation of Rain Accumulation on Aircraft Windsh...

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

作者： Lu, Shengfang Chen, Weijian Shen, Hao Zhu, Guangya Shi, Ruxin Key Laboratory of Aircraft Environment Control and Life Support Ministry of Industry and Information Technology Nanjing University of Aeronautics & Astronautics Nanjing China Shanghai Aircraft Airworthiness Certification Center of CAAC Shanghai China

ISBN: (数字)9781839537769

ISBN: (纸本)9781839537769

aircraft windshield rainfall process is a complex two-phase flow problem that includes the movement, collision, fragmentation, merging of raindrops, water film adsorption and water film flow. In this paper, a numerical method based on FLUENT is proposed to simulate this process. And the experiment of rain accumulation on flate-plate is carried out to verify the numerical method. This method combines the Discrete Phase Model and the Lagrangian Water Film Model. The control variable method is adopted to study the effects of aircraft flight speed, Angle of Attack(AOA), rainfall intensity and raindrop temperature on windshield rainfall. The results show that the impact of aircraft AOA on the windshield rainfall is relatively low, while the aircraft flight speed and rainfall intensity are positively correlated with the degree of windshield rainfall. The raindrop temperature has no significant effect on the windshield rainfall, but the lower temperature will bring more difficulty to remove raindrops. © 2022 IET Conference Proceedings. All rights reserved.

关键词： Rain

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Study on icing environment of typical civil aircraft boarding gate

Study on icing environment of typical civil aircraft boardin...

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

作者： Yifan Zhu Xudong Qiu State Key Laboratory of Airliner Integration Technology and Flight Simulation COMAC Shanghai Aircraft Design and Research Institute Shanghai 200126 People's Republic of China

ISBN: (数字)9781837242108

In order to verify the compliance requirements of typical civil aircraft cabin doors to airworthiness provisions in cold weather, a high and low temperature experimental cabin was built with the boarding door as the research object. The freezing opening test of the cabin door's inner handle and outer handle was carried out by means of rain in a low temperature environment. It is found that the ice surface faults are orderly, there is no stuck and no noise during the test, the mechanism is intact, and the hatch door can be closed normally. The opening time of the inner handle after icing is 6.17 s, which meets the requirements of the airworthiness clause. The test results can provide a basis for the design index of the model gate under the icy environment.

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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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Instability threshold analysis and optimization of a rotor system considering the Alford force 57

Instability threshold analysis and optimization of a rotor s...

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57th International Conference on Vibroengineering

作者： Fu, Yao Wang, Fei AVIC Jincheng Nanjing Engineering Institute of Aircraft Systems Nanjing211106 China China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing211106 China College of Aircraft Engineering Nanchang Hangkong University Nanchang China

Under certain circumstances, the Alford force might induce instability of the rotor system. The mechanism and influence factors of the Alford force induced instability were analyzed with the Jeffcott rotor. Then a method for calculating the instability threshold was proposed. Finally, the optimization model of a high-speed micro-turbojet engine was established to optimize the instability threshold. The results show that the anisotropy of support stiffness and the damping ratio can both improve the threshold of instability. The instability threshold can be greatly improved by optimizing bearing stiffness and diameter of the rotor system. Copyright © 2022 Yao Fu, et al.

关键词： Stability

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Numerical Simulation of Supercooled Large Droplet Icing Based on Random Icing Model

Numerical Simulation of Supercooled Large Droplet Icing Base...

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

作者： Shi, Ruxin Zhao, Jingyu Chen, Weijian Shen, Hao Cheng, Qian Lu, Shengfang Key Laboratory of Aircraft Environment Control and Life Support Ministry of Industry and Information Technology Nanjing University of Aeronautics & Astronautics Nanjing China Shanghai Aircraft Airworthiness Certification Center of CAAC Shanghai China

ISBN: (数字)9781839537769

ISBN: (纸本)9781839537769

A major difficulty in the numerical simulation of aircraft icing is to simulate the Supercooled Large Droplet(SLD) icing process. Based on the Euler method, the splash model and deformation model of SLD are added to the governing equation of droplet motion, and the droplet impact characteristic model of SLD is obtained. Using this model, the impact characteristics of NACA23012 under the condition of SLD are calculated, and the local water collection coefficient(β) is obtained. Based on Szilder's random walk model, a modified random icing model(RIM) is established, including the droplet random-walk model(RWM) on the icing surface and the freezing probability model. The numerical simulation of SLD icing is carried out by using this model. The calculated results are in good agreement with the literature data. In particular, the ice shape calculated by RIM is rougher and their microscopic characteristics are more obvious. Therefore, RIM has more advantages in predicting the aerodynamic characteristics of SLD icing shape. © 2022 IET Conference Proceedings. All rights reserved.

关键词： Numerical models

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