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7th China Aeronautical Science and technology Conference, CASTC 2024

作者： Zhu, Yuanchun Sun, Libing Ren, Jian AVIC Aerospace Life-Support Industries Ltd. Xiangyang441000 China Key Laboratory of Aviation Science and Technology for Aviation Protection and Life-Saving Technology Xiangyang441000 China

ISBN: (纸本)9789819797738

The life-saving platform can provide remote life-saving materials and refuge facilities for victims who encounter sudden natural disasters and accidents within the delivery radius, and has the ability to improve the survival chances of victims. The rescue platform in this article is equipped with a modular floating airbag to provide the rescue platform with long-term floating capacity. In order to evaluate whether the connection belt and airbag pressure of the modular floating airbag and the selection of airbag material and connection belt material meet the requirements when the life-saving platform enters the water with different posture, three water entry posture were simulated and calculated. The simulation results show that the pressure of the connecting belt and the airbag of the water entry posture 2 is the most tested, and the design of the connecting belt and the airbag has a large safety space. © Chinese Society of Aeronautics and Astronautics 2025.

关键词： Disasters

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Research on Calculation Method of Drag Chute Opening Performance Based on Rocket Sled Platform 7th

Research on Calculation Method of Drag Chute Opening Perform...

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7th China Aeronautical Science and technology Conference, CASTC 2024

作者： Jin, Lou Cui, Dongyue Yang, Pin Yu, Yuanyuan Aviation Key Laboratory of Science and Technology on Life-Support Technology Xianyang China Overall Technology R&D Department AVIC Aerospace Life-Support Industries Ltd. Xianyang China Institute of Mechanical and Electrical System AVIC The First Aircraft Institute Xi’an China

ISBN: (纸本)9789819797738

This paper proposes a calculation method based on the rocket sled test method to quickly verify the performance of the main drag chute of aircraft. According to the working principle and folding process of the drag chute, combined with the pre-processing folding and calculation folding methods, the simulation folding process of the finite element model of the drag chute is designed, the finite element model of the rocket sled system was established. Then, the S-ALE fluid structure coupling algorithm was used to simulate and calculate the performance parameters of the rocket sled drag parachute system during the parachute deployment process, forming a simulation verification process for the parachute deployment performance of the drag chute. The calculation results show that the force on the rope of the drag chute during the operation process of the rocket sled drag parachute system shows a consistent trend over time, and the error generated by calculating the opening performance parameters of the rocket sled drag parachute system using the method proposed in this article are within 12%, which can meet the requirements of engineering use. The calculation method proposed in this article can to some extent replace the rocket sled test to verify the performance of the parachute. The calculation method proposed can quickly predict the performance of the drag chute instead of physical tests at the initial stage of development. © Chinese Society of Aeronautics and Astronautics 2025.

关键词： Parachutes

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Quantitative Analysis of Flow Resistance in the Ventilation Pipeline of Ejection Seats and Optimization Design of Flow Resistance Reduction 7th

Quantitative Analysis of Flow Resistance in the Ventilation ...

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7th China Aeronautical Science and technology Conference, CASTC 2024

作者： Jin, Lou Wu, Jing Chen, Yuxiang Cui, Dongyue Aviation Key Laboratory of Science and Technology on Life-Support Technology Xianyang China Overall Technology R&D Department AVIC Aerospace Life-Support Industries Ltd. Xianyang China Institute of Mechanical and Electrical System AVIC The First Aircraft Institute Xi’an China

ISBN: (纸本)9789819797707

During normal flight, the ejection seat ventilation system provides a dedicated gas transmission channel for electronic oxygen and anti load regulators. The flow resistance of the pipeline directly affects the ventilation and supply performance of the regulator and the anti load protection ability during mobile operations. This article adopts a combination of numerical simulation and experimental testing methods to quantitatively analyze the flow resistance of a certain type of ejection seat ventilation pipeline. Based on the principle of gas supply performance testing and numerical simulation methods, a research process is designed. The simulation accuracy of different simulation models under different ventilation flow rates is analyzed, and the ventilation pipeline is optimized based on the calculation formula of pipeline flow resistance theory and the analysis results of pipeline flow field. The research results indicate that among multiple turbulence models, the Realizable k-e model has the best accuracy in simulating pipeline flow resistance, with a maximum error of 14.2% and a minimum error of 1.3% under different flow conditions, both below 15%, meeting the requirements for engineering use;the vortices generated at the corners and variable diameter areas of the ventilation pipeline can lead to energy dissipation. Optimizing the transition corners and pipeline diameter of the bend can reduce the generation of vortices and reduce the system flow resistance to 17.9% of the original value;under the premise of constant pipeline flow rate, the flow resistance of ventilation pipelines is inversely proportional to the fifth power of pipeline diameter. When optimizing pipeline flow resistance design, emphasis should be placed on optimizing from the pipeline diameter. © Chinese Society of Aeronautics and Astronautics 2025.

关键词： Ejection seats

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Interval-based scale-span topology optimization considering reliable manufacturing limits via the parameterized level set method and image recognition techniques

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Thin-Walled Structures 2025年 214卷

作者： Li, Zeshang Wang, Lei Gu, Kaixuan Liu, Yaru National Key Laboratory of Strength and Structural Integrity Institute of Solid Mechanics School of Aeronautic Science and Engineering Beihang University Beijing 100191 China Ningbo Institute of Technology Beihang University Ningbo315100 China Aviation Key Laboratory of Science and Technology on Life-support Technology Xiangyang441003 China School of Mechanical and Aerospace Engineering Nanyang Technological University 50 Nanyang Avenue 639798 Singapore

With the continuous development of additive manufacturing technology, designing materials and structures with diverse functions and complex configurations to meet special needs has become a hot topic. However, the various manufacturing limits result in deviations between the design results and the actual results. This paper proposes an interval-based scale-span topology optimization method considering reliable manufacturing limits via the parameterized level set method and image recognition techniques. Firstly, this paper describes the boundaries of topology configurations based on the parameterized level set method. Then, based on the image recognition technology, explicit expression of structural boundaries is achieved, and various geometric features are further quantified and controlled based on the recognition results. Considering the uncertainty effects of structural size and size constraints, a reliability-based topology optimization design has been achieved. Design optimization has been carried out for metamaterial problems, mechanical problems, and thermal problems of multiscale structures. Finally, numerical validation and manufacturing are carried out on the design results, which demonstrates the effectiveness of the proposed method. © 2025 Elsevier Ltd

关键词： Convergence of numerical methods

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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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Study of velocity effects on parachute inflation performance based on fluid-structure interaction method

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Applied Mathematics and Mechanics(English Edition) 2014年第9期35卷 1177-1188页

作者：程涵张鑫华余莉陈猛 College of Aerospace Engineering Nanjing University of Aeronautics and Astronautics Aviation Key Laboratory of Science and Technology on Aeronautical Life-Support AVIC Aerospace Life-Support Industries Ltd.

The inflation of a five-ring cone parachute with the airflow velocity of 18 m/s is studied based on the simplified arbitrary Lagrange Euler （SALE）/fluid-structure interaction （FSI） method. The numerical results of the canopy shape, stability, opening load, and drag area are obtained, and they are well consistent with the experimental data gained from wind tunnel tests. The method is then used to simulate the opening process under different velocities. It is found that the first load shock affected by the velocity often occurs at the end of the initial inflation stage. For the first time, the phenomena that the inflation distance proportion coefficient increases and the dynamic load coefficient decreases, respectively, with the increase in the velocity are revealed. The above proposed method is competent to solve the large deformation problem without empirial coefficients, and can collect more space-time details of fluid-structure-motion information when it is compared with the traditional method.

关键词： fluid-structure interaction （FSI） parachute inflation performance velocity,empirical coefficient opening shock load

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Measuring Center of Gravity of Pilot Helmet Based on Binocular Vision 4

Measuring Center of Gravity of Pilot Helmet Based on Binocul...

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4th International Conference on Advances in Computer technology, Information Science and Communications, CTISC 2022

作者： Jun, Li Xie, Wujun Wan, Chuanqi Jia, Zixiao Yang, Junwei Avic Aerospace Life-Support Industries LTD. Aviation Key Laboratory of Science and Technology on Life-Support Technology Xiangyang China

ISBN: (数字)9781665458726

ISBN: (纸本)9781665458726

A variety of functions are integrated into the pilot helmet, making it an intelligent weapon platform for pilots to improve situational awareness and target attacks capabilities. However, the mass distribution of the helmet has also been changed, which has a negative impact on the pilot's health and safety. Accurate measurement of the Center of Gravity (CG) of pilot helmet is of great significance for the ergonomic design. Benefiting from the rapid development of 3D computer vision technology, a 3D coordinate of CG measurement scheme for pilot helmet based on binocular vision is proposed by adopting suspension method. The measuring equipment and program are introduced in detail, and the calculation model for the center of gravity is also established. The calibration results show that the proposed measurement scheme based on binocular vision is effective. © 2022 IEEE.

关键词： Binocular vision

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A Novel Cooperative MIMO Transmission Scheme Based on STBC for Event-Driven WSNs 3

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

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3rd IEEE International Conference on Electronics technology, ICET 2020

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

ISBN: (纸本)9781728162836

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. © 2020 IEEE.

关键词： Wireless sensor networks

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Research on High Precision Measurement of Head Position and Posture

Research on High Precision Measurement of Head Position and ...

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

作者： Luo, Guoxiong Liu, Xiang Gao, Hongyi Jin, Zhisheng Xie, Wujun Cui, Wenming Aviation Key Laboratory of Science and Technology on Life-support Technology Hubei Xiangyang China AVIC Aerospace Life-support Industries Ltd. Hubei Xiangyang China

ISBN: (数字)9781839537769

ISBN: (纸本)9781839537769

For the safety of pilots, it is necessary to explore the change process of ATD head spatial position and posture in the dynamic impact test of driver's seat. Therefore, a comprehensive position and posture solution method was proposed, which mainly including bundle adjustment method, forward intersection method and feature line projection method. This method achieves the high precision of the ATD head position and posture measurement requirements, and its measurement accuracy reaches the level of mm and degree respectively. © 2022 IET Conference Proceedings. All rights reserved.

关键词： attitude measurement biomechanics CCD image sensors computer vision impact testing position control position measurement vehicle dynamics

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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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