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32nd Congress of the International Council of the Aeronautical Sciences, ICAS 2021

作者： Wang, Xiujuan Xu, Jing Wang, Juhao Mi, Jiachen Jiang, Yaming Aerospace Life-support Industries LTD Xiangyang441003 China Aviation Key Laboratory of Science and Technology on Life-support Technology Xiangyang441003 China Tiangong University School of Textile Science and Engineering Tianjin 300387 China Intel Engineering Simulation Technology Co. Ltd. Dalian116023 China

ISBN: (纸本)9783932182914

With the advancement of technology, the functions of pilot helmets are constantly being upgraded. The highly integrated helmets with display, positioning, sensing, night vision and camera are the future development trends. Although the multifunctional and highly integrated design enhances the combat maneuverability, the add-on components will result in local tenderness as the weight gain and center of gravity change, which seriously affects the pilot's wearing comfort, especially in high-speed overload conditions. These factors have become potential factors affecting flight safety. At present, experience-based methods are no longer suitable for new product development. Therefore, it is urgent to establish a simulation model on the pressure comfort of "helmet-head", the finite element method is used for simulation calculation. This paper studies different conditions of the center of gravity, and using the standard head shape, ball shape and real head shape as a control, to analyze the center of gravity, the difference of the head shape, and the influence of overload loading on the pressure distribution. By comparing with the actual flight situation, the simulation results are consistent with the actual situation, which proves that the simulation model has good credibility. © 2021 32nd Congress of the International Council of the Aeronautical Sciences, ICAS 2021. All rights reserved.

关键词： Flight simulators

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Optimization of High-Speed WIG Airfoil with Consideration of Non-ground Effect by a Two-Step Deep Learning Inverse Design Method

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Transactions of Nanjing University of Aeronautics and Astronautics 2025年第1期42卷 56-69页

作者： WANG Chenlu SUN Jianhong ZHENG Daren SUN Zhi ZUO Si LIU Hao LI Pei Key Laboratory of Aircraft Environment Control and Life Support Ministry of Industry and Information TechnologyNanjing University of Aeronautics and AstronauticsNanjing 210016P.R.China Key Laboratory of Civil Aviation Emergency Science&Technology Civil Aviation Administration of ChinaNanjing University of Aeronautics and AstronauticsNanjing 211106P.R.China State Key Laboratory of Mechanics and Control for Aerospace Structures Nanjing University of Aeronautics and AstronauticsNanjing 210016P.R.China

Under complex flight conditions,such as obstacle avoidance and extreme sea state,wing-in-ground(WIG)effect aircraft need to ascend to higher altitudes,resulting in the disappearance of the ground effect.A design of high-speed WIG airfoil considering non-ground effect is carried out by a novel two-step inverse airfoil design method that combines conditional generative adversarial network(CGAN)and artificial neural network(ANN).The CGAN model is employed to generate a variety of airfoil designs that satisfy the desired lift-drag ratios in both ground effect and non-ground effect ***,the ANN model is utilized to forecast aerodynamic parameters of the generated *** results indicate that the CGAN model contributes to a high accuracy rate for airfoil design and enables the creation of novel airfoil ***,it demonstrates high accuracy in predicting aerodynamic parameters of these airfoils due to the ANN *** method eliminates the necessity for numerical simulations and experimental testing through the design procedure,showcasing notable *** analysis of airfoils generated by the CGAN model shows that airfoils exhibiting high lift-drag ratios under both flight conditions typically have cambers of among[0.08c,0.105c],with the positions of maximum camber occurring among[0.35c,0.5c]of the chord length,and the leading-edge radiuses of these airfoils primarily cluster among[0.008c,0.025c]

关键词： conditional generative adversarial network(CGAN) artificial neural network(ANN) airfoil design wing-in-ground(WIG)aircraft ground effect

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Numerical simulation and experimental research on Taylor Couette flow characteristics in air gap of aviation motor

Numerical simulation and experimental research on Taylor Cou...

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

作者： Hui Ma Shuyue Liang Hongbo Zhan Lin Qi Weijian Chen Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration No.33 Shuige Road Nanjing People's Republic of China Key Laboratory of Aircraft Environment Control and Life Support MIIT Nanjing University of Areonautics and Astronautics No.29 Yudao Street Nanjing People's Republic of China

ISBN: (数字)9781837242108

A test bench with PIV technology was built and visualization research on Taylor vortex between concentric rotating cylinders was carried out to explore the flow morphology within the annular gap by changing the rotational speed of the inner cylinder. The numerical method and accuracy were verified by experiments. The selected turbulence model was then applied for numerical simulation of the Taylor Couette flow in a simplified air gap model of an aviation motor with smooth inner and outer walls. The Taylor Couette flow characteristics in the air gap under varying rotational speed were studied, and simulation results were given for flow with axial flow and without axial flow.

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Research on measurement method of six degree of freedom for head based on safetr of aircraft pilot seat

Research on measurement method of six degree of freedom for ...

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CSAA/IET International Conference on Aircraft Utility Systems 2020, AUS 2020

作者： Luo, Guo-Xiong Jin, Zhi-Sheng Xie, Wu-Jun Wang, Ru-Bing Aviation Key Laboratory of Science and Technology on Life-Support Technology Hubei Xiangyang China AVIC Aerospace Life-Support Industries Ltd. Hubei Xiangyang China

ISBN: (纸本)9781839535635

In order to ensure the safety of the pilot's life, the six degree of freedom data of the ATD head need to be obtained through dynamic impact test to evaluate the possibility of head injury in the cockpit. A binocular photogrammetry method by the simplified solution of normal equation based on bundle adjustment was proposed. On the basis of satisfying the imaging requirements of high-speed cameras, the 3D position and posture data of the head were obtained by shooting and analyzing the images of the test process. © 2020 Institution of Engineering and technology. All rights reserved.

关键词： Degrees of freedom (mechanics)

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Analysis of pollutant concentration in aircraft cabin under MCT single engine drift descent status

Analysis of pollutant concentration in aircraft cabin under ...

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

作者： Qianlong Ding Xizhong Jian Haiming Shen Guangya Zhu Dalin Zhang Weijian Chen Key Laboratory of Aircraft Environment Control and Life Support MIIT Nanjing University of Aeronautics & Astronautics Nanjing People's Republic of China Shanghai Aircraft Design and Research Institute of COMAC Shanghai People's Republic of China College of Flight Technology Civil Aviation University of China Tianjin People's Republic of China

ISBN: (数字)9781837242108

Concentration distribution of air pollutants in commercial aircraft cabins are important for providing passengers and crew wi th a healthy and comfortable environment. To verify whether the concentration of air pollutants meets airworthiness standards, this article focuses on the cabin of a specific aircraft and employs numerical simulation to analyze the CO 2 concentration distribution during single-engine drift. The MCT single-engine drift calculations reveal that pollutants initially increase and then decrease as the aircraft descends from 7620m to the emergency ventilation altitude, the concentrations of pollutants in the x section, y section and z section increasing by 66.87%, 55.61%, and 61.08% respectively, maintaining pollutant concentrations within acceptable limits throughout the drift.

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Nonlinear Dynamic Modeling and Body Injuries Analysis of Human/Seat System Under Vertical Impact

SSRN

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SSRN 2022年

作者： Xiao, Huiting Wang, Kejie Liu, Yongshou Guo, Qing Wen, Yongshuai Feng, Zhijie School of Mechanics Civil Engineering and Architecture Northwestern Polytechnical University Xi’an710129 China Aviation Key Laboratory of Science and Technology on Life-Support Technology AVIC Aerospace Lifesaving Equipment Co. Ltd. Xiangyang441000 China

Predicting the responses and injuries of seated pilots caused by emergency landing or ejection is significant for the design of ejection seats. A nonlinear two-dimensional multi-body human/seat model is proposed to predict the responses and body injuries exposed to vertical impact. Then a new force identification method is presented and applied to obtain the external excitation of the system. In addition, the parameters of this model are optimized based on the Error Assessment of Response Time Histories (EARTH) metric and Non-dominated Sorting Genetic Algorithm II (NSGA-II). Furthermore, utilizing the proposed model, this research predicts body injuries with different impact intensities. With body injuries as output, the influence of input parameters is assessed by global sensitivity analysis (GSA) methods. The result shows that the backrest angle plays a crucial role in body injuries. Finally, the influence of backrest angle is further analyzed to obtain the variation of body injuries with backrest angle. This research provides guiding principles for the subsequent design of ejection seats. © 2022, The Authors. All rights reserved.

关键词： Ejection seats

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Simulation study on dynamic opening characteristics of airplane drag chute under the condition of stable crosswind

Simulation study on dynamic opening characteristics of airpl...

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CSAA/IET International Conference on Aircraft Utility Systems 2020, AUS 2020

作者： Jin, Lou Yang, Pin Hu, Xuepeng Li, Hui Zhang, Linling Cui, Dongyue Aviation Key Laboratory of Science and Technology on Life-support Technology Xianyang China AVIC Aerospace Life-support Industries Ltd. Xianyang China AVIC The First Aircraft Institute Institute of Mechanical and Electrical System Xi'an China

ISBN: (纸本)9781839535635

In this paper, the ALE fluid-solid coupling algorithm is used to realize the simulation of the dynamic opening process of a certain type of airplane drag parachute. Based on the drag parachute working principle and folding process, a finite element model of the main parachute in the installed state is established. In the LS-DYNA software, the parachute opening characteristics of the drag parachute were simulated and analyzed under no crosswind conditions and Stable crosswind conditions at speed 10m/s. The results show that, under the condition of no crosswind, the error of the important parameters such as parachute straightening force, parachute opening dynamic load, parachute deflection angle and test data is less than 15%, and the simulation accuracy meets the engineering development requirements. On this basis, the parameters such as the unfolding shape, deflection angle, and stress state of the parachute parachute under stable crosswind conditions, which are difficult to test and simulate, were studied. This will provide a theoretical basis and technical approach for drag chute design and other types of parachute product research. © 2020 Institution of Engineering and technology. All rights reserved.

关键词： Product design

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Equivalent study on delethalization test for sled head injury criteria test of civil aircraft passenger seat

Equivalent study on delethalization test for sled head injur...

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CSAA/IET International Conference on Aircraft Utility Systems 2020, AUS 2020

作者： Jin, Zhi-Sheng Shen, Wen-Bo Luo, Guo-Xiong Li, Ming Jia, Zhi-Xiao Zhou, Wu Jia, Luo Zhang, Le Aviation Key Laboratory of Science and Technology on Life-Support Technology Xiang yang China Test Department AVIC Aerospace Life-Support Industries Ltd No.29 Xinhua road Xiang yang China Science and Technology Development Department AVIC Aerospace Life-Support Industries Ltd No.29 Xinhua road Xiang yang China

ISBN: (纸本)9781839535635

The equivalent study between delethalization test and sled HIC test is in order to improve the efficiency of Head Injury Criteria (HIC) test on civil aircraft passenger seats, as well as to reduce the test consumption and cost. The equivalent impact model was established based on the equal rotatory kinetic energy, then the test of equal energy impact was designed and the delethalization test was carried out. The results of delethalization test and sled HIC test show that all the deviation value of HIC, peak head center of gravity (CG) acceleration in X direction, peak head CG resultant acceleration and the deformation of the seat back (C/B) was within ± 20%. In conclusion, the equivalent impact model in this paper is suitable, and the delethalization test be used as an equivalent method for sled HIC test is feasible. © 2020 Institution of Engineering and technology. All rights reserved.

关键词： Kinetics

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Research on Reliability Assessment Method of Emergency Escape Parachute 5

Research on Reliability Assessment Method of Emergency Escap...

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2020 5th International Conference on Intelligent Computing and Signal Processing, ICSP 2020

作者： Ma, Fangyun Lei, Huajin Wang, Wensheng Liu, Jing Jin, Liying Aviation Key Laboratory Science and Technology on Life-Support Technology Hubei Xiangyang441003 China Aerospace Life-Support Industries Ltd. Hubei Xiangyang441003 China School of Mechanical Engineering Hubei University of Arts and Science Xiangyang441053 China

Aiming at the problem that emergency escape parachute cannot meet the requirements of the index using the binomial evaluation method, combined with the characteristics of emergency escape parachute products, comprehensively using emergency escape parachute components and system test data, the emergency escape parachute Bayesian reliability assessment method is proposed to solve the problem of reliability assessment in the case of small sample size of emergency escape parachute system test, which effectively reducing emergency escape parachute test expenses and development cycle. © 2019 Published under licence by IOP Publishing Ltd.

关键词： Parachutes

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A Novel Cooperative MIMO Transmission Scheme Based on STBC for Event-Driven WSNs

A Novel Cooperative MIMO Transmission Scheme Based on STBC f...

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International Conference on Electronics technology (ICET)

作者： Li Jun Xie Wujun Aviation Key Laboratory of Science and Technology on Life-support Technology AVIC Aerospace Life-support Industries LTD. Xiangyang China

ISBN: (数字)9781728162836

ISBN: (纸本)9781728162843

The cooperative MIMO (CMIMO) technology having characteristics of low energy expended and high reliability can be very well suited to resource-constrained event-driven wireless sensor networks (WSNs), in which collecting date is unpredictable for space and time. A novel energy-efficient STBC-based CMIMO transmission scheme is put forward for event-driven WSNs in this letter, which adopts cross-layer design and dynamic event cluster. Detailed energy models are developed to maximize energy saving by the joint optimization for the number of cooperative nodes and constellation size. Through computer simulation, It can be found that the novel transmission scheme saves more energy in comparison with the traditional transmission protocol.

关键词： CMIMO event-driven WSNs energy-efficient STBC the joint optimization even-driven program space time block coding Energy efficiency transport protocols ENERGY MODELS multiple input multiple output systems

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