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

作者： Zhou, Yu Wang, Yangyang Fuel System Department Nanjing Engineering Institute of Aircraft Systems AVIC Nanjing China The Aviation Electromechanical System Integration of Aviation Science and Technology Key Laboratory Nanjing China

After the fiber membrane material is determined, the aircraft is more concerned about the flow rate of nitrogen-rich gas under a certain nitrogen-rich gas (NEA) concentration, thereby determining the inerting time of the fuel tank. This paper mainly introduces the separation principle and related parameters of fiber membranes, as well as the types and separation performance of different fiber membranes. The asymmetric polyimide membrane, which is more commonly used in airborne nitrogen inerting, is used to verify the effects of different temperatures, pressures, and altitudes on the separation efficiency of the fiber membranes through experiments. The results of the research can provide a basis for the design of subsequent high-efficiency hollow fiber membranes. © The Institution of Engineering & technology 2024.

关键词： Nafion membranes

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An Experimental Study on Water Curtain Cooling and Infrared Concealment Effects

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哈尔滨工程大学学报(英文版) 2025年第3期24卷 567-579页

作者： Nenglin Yuan Meinan Liu Yitao Zou Hong Shi School of Energy and Power Jiangsu University of Science and TechnologyZhenjiang 212003China Key Laboratory of Aircraft Environment Control and Life Support Nanjing University of Aeronautics&AstronauticsNanjing 210016China

The water curtain spray system of the ship helps reduce surface thermal load and lowers thermal infrared radiation, notably enhancing the stealth and survivability of naval ships. The performance of the water curtain spray system is largely influenced by the density of the nozzles and their installation height. Therefore, a test platform was established to investigate these critical influencing factors, employing an orthogonal design methodology for the experimental study. Specifically, the study evaluated the effects of varying distances to the steel plate target and different injection heights on the cooling performance of the system. Results demonstrate that using one nozzle per 4 square meters of the ship's surface area effectively lowers the surface temperature, bringing it closer to the ambient background temperature. This nozzle configuration creates irregular infrared heat patterns, which complicate the task for infrared detectors to discern the ship's outline, thus enhancing its infrared stealth. Additionally, maintaining the nozzle installation height within 0.6 m to prevent the temperature difference between the steel plate and the background temperature from exceeding 4 K. Moreover, as the infrared imaging distance increases from 3 to 9 m, the temperature difference measured by the thermocouple and the infrared imager increases by 141.27%. Furthermore, with the increase in infrared imaging distance, the infrared temperature of the target steel plate approaches the background temperature, indicating improved detectability. These findings have significantly enhanced the stealth capabilities of naval ships, maximizing their immunity to infrared-guided weapon attacks. Moreover, their importance in improving the survivability of ships on the water surface cannot be underestimated.

关键词： Ship water curtain stealth Water curtain nozzles Water curtain cooling Infrared shielding Infrared stealth

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A Method for Reconstructing The Shape of Wing Panels Based on Fiber Optic Sensors and Tomographic Imaging Principles 15

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

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15th IEEE Global Reliability and Prognostics and Health Management Conference, PHM-Beijing 2024

作者： Zhan, Jun Zeng, Jie Xiang, Chao Cui, Jinpeng Zeng, Cheng Zhu, Linfeng Lu, Mingyu State Key Laboratory of Mechanics and Control for Aerospace Structures Nanjing University of Aeronautics and Astronautics No. 29 Yudao Street Nanjing210016 China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing Engineering Institute of Aircraft System Jincheng AVIC Nanjing China COMAC Beijing Aircraft Technology Research Institute Changping District Xiaotangshan Future Science and Technology City Beijing102211 China

ISBN: (纸本)9798350354010

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. © 2024

关键词： Fixed wings

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CONSTRUCTION, VERIFICATION AND ENGINEERING APPLICATION OF BLEED AIR SYSTEM SIMULATION MODEL BASED ON MOC8 TEST ENGINEERING SIMULATOR

CONSTRUCTION, VERIFICATION AND ENGINEERING APPLICATION OF BL...

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

作者： Cao, Yang Cai, Mengdi Qu, Xiaoyu COMAC Shanghai Aircraft Design &Research Institute 5188#Jinke Road Shanghai China State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai200126 China

The engineering simulator is a test platform that simulates the flight environment with high fidelity, and integrates the system simulation model that meets the requirements, so as to support the system design and airworthiness verification test. Based on the test requirements of MOC8 engineering simulator, this paper proposes a set of model development, validation and application methods for the air source system, which provides an effective way for the development of on-board system simulation model of MOC8 engineering simulator, and is of practical significance in engineering. © The Institution of Engineering & technology 2024.

关键词： Flight simulators

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NOSE WHEEL STEERING MODE ANALYSIS BASED ON aircraft OPERATION SCENARIOS

NOSE WHEEL STEERING MODE ANALYSIS BASED ON AIRCRAFT OPERATIO...

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

作者： You, Fan Chen, Wenjie Liu, Leilei Li, Da Li, Hang Shanghai Aircraft Design and Research Institute No. 5188 Jin Ke Road Shanghai China State key laboratory of Airliner Integration Technology and Flight Simulation Shanghai200126 China

aircraft operations encompass a range of intricate scenarios, spanning from pre-flight preparation to parking and end of flight. By conducting scenarios analysis of the nose wheel steering system, this study establishes the usage scenarios for different steering modes, defines the modes' logic, and specifies the conditions for entering and exiting these modes. Simulation analysis is employed to validate the correctness of the nose wheel steering scenarios and mode transitions, providing valuable insights for the design and trade-off analysis of nose wheel steering systems in civil aircraft. © The Institution of Engineering & technology 2024.

关键词： Steering

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STUDY ON THE RELATIONSHIP BETWEEN THE FRICTION PAIRS WEAR AND THE PLUNGER FRACTURE

STUDY ON THE RELATIONSHIP BETWEEN THE FRICTION PAIRS WEAR AN...

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

作者： Zou, Pengjian Zhang, Haoran Gu, Manning Xia, Tianxiang Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing211106 China Nanjing Engineering Institute of Aircraft System Jincheng Corporation AVIC Nanjing211106 China

The plunger pump is one of the most complicated hydraulic components, the fault reason is hidden, the traditional analysis method such as theoretical formula is difficult to study its fault principle and correlation. In some cases of plunger pump failure, the fracture of the plunger is usually accompanied by serious wear of plunger and sliding shoe. In order to study the correlation between kinematic pairs wear and plunger fracture, a flexible-solid coupling dynamic digital prototype of plunger pump is built, which takes into account the action of hydraulic pressure and rotating load in a rotating cycle. The friction force of the friction pair is considered by modifying the contact method of the friction surface of kinematic pair. The simulation results show that the plunger pair wear leads to the increase of supporting force of sliding shoes, the wear of plunger and sliding shoe leads to the sharp increase of stress of plunger neck, the wear of kinematic pair is related to the plunger fracture. © The Institution of Engineering & technology 2024.

关键词： Friction

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An Optimization Method for the Swing of a Quadrotor Flight Suspension System 25

An Optimization Method for the Swing of a Quadrotor Flight S...

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25th IEEE China Conference on System Simulation technology and its Application, CCSSTA 2024

作者： Yang, Sen Zang, Xinlian Tong, Jigang Xie, Tian Jin, Xin Tianjin University of Technology The School of Electrical Engineering and Automation Tianjin China AVIC Xi'an Flight Automatic Control Research Institute National key laboratory of science and technology on aircraft control Xi'an China

ISBN: (纸本)9798350366600

The aim of this study is to explore optimization control methods for suspension systems during the flight of quadcopters. The traditional control method of suspension system has some problems such as oscillation and instability, so an optimization scheme based on Gaussian pseudo-general algorithm is proposed in this paper. Through numerical simulation and actual flight test, the effectiveness of the optimization algorithm in improving system stability and reducing oscillation amplitude is verified. At the same time, this study conducted a comparative analysis of the suspension system of the quadrotor vehicle and the free fall body, and the optimization algorithm is found to be feasible and can well improve the control accuracy and stability of the system, and provide strong support for the safety of the quadrotor vehicle in various application scenarios. © 2024 IEEE.

关键词： Flight testing

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STUDY ON VISIBILITY IN FALLING AND BLOWING SNOW OF CIVIL aircraft APU INLET SYSTEM

STUDY ON VISIBILITY IN FALLING AND BLOWING SNOW OF CIVIL AIR...

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

作者： Zhang, Sheng Zhou, Qiongyao Shanghai Aircraft Design Research Institute Shanghai China State Key Laboratory of Airliner Integration Technology and Flight Simulation 5188 Jinke Road Pudong New Area Shanghai China

According to the requirements of CAAC, FAA and EASA on falling and blowing snow of Auxiliary Power Unit inlet system, the environmental conditions of compliance test were sorted out. The relationships among visibility, water content of falling snow and snow mass flux of blowing snow were studied. The research shows that: 1) FAA and EASA have basically the equivalent requirements for snowfall intensity, wet snow temperature and blowing snow conditions. Compared with falling snow requirements, the requirements of blowing snow test is more briefly;2) Based on the NCEP visibility estimation method, under the same visibility, the water content of different snow types is significantly different, and snowflakes are more likely to cause visibility reduction. The water content value corresponding to 0.4 km suggested by FAA is basically consistent with the snow water content value estimated by NCEP;3) The height of typical civil aircraft APU inlet system above ground is about 5.5 m. Combining with the extreme value of snow flux given in MIL-STD-810G and GJB1172.6-91, 4.5 g/(m2.s) can be used as the test mass flux for blowing snow test. The visibility under this mass flux is about 218.8 m, which is equivalent to the intensity of heavy snow. © The Institution of Engineering & technology 2024.

关键词： Water content

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RESEARCH ON laboratory TESTING AND EVALUATION METHODS FOR aircraft WINDSHIELD WIPER SYSTEMS

RESEARCH ON LABORATORY TESTING AND EVALUATION METHODS FOR AI...

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

作者： Liu, Caixia Liu, Qianqian Shanghai Aircraft Design & Research Institute Shanghai China State Key Laboratory of Airliner Integration Technology and Flight Simulation 5188 Jinke Road Pudong New Area Shanghai China

A laboratory test method for aircraft windshield wiper system based on high speed blowing-rain environment simulation and a semi-quantitative subjective evaluation method for rain removal visual performance are proposed for aircraft windshield wiper system testing. Analyzing CCAR25.773 and related standards and advisory circulars, it is concluded that the two key factors for simulating rainy environments are rainfall intensity and wind speed. The range of rainfall intensity values is (10~25) mm/h, and the range of wind speed values is (40~120) m/s. The definition and calculation method of equivalent blowing-rain intensity are provided. A high-speed rain environment simulation device has been built, which can simultaneously simulate the rain intensity received by the windshield during aircraft rainy flight, as well as the relative velocity between the windshield and free flow and raindrops. A subjective evaluation method for the visual performance of windshield rain removal based on visual evaluation reference objects was proposed. A rain blowing test was conducted on the windshield wiper system of a certain aircraft, and the test results showed a statistically significant difference between the rain blowing environmental conditions and the rain removal characteristics at a significance level of 0.05. Engineering practice has shown that this method is feasible. © The Institution of Engineering & technology 2024.

关键词： Windshield wipers

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A Enhanced Feature Extraction for 3D Object Detection 25

A Enhanced Feature Extraction for 3D Object Detection

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25th IEEE China Conference on System Simulation technology and its Application, CCSSTA 2024

作者： Meng, Qingao Tong, Jigang Yang, Sen Xie, Tian Jin, Xin Tianjin University of Technology The School of Electrical Engineering and Automation Tianjin China Avic Xi'an Flight Automatic Control Research Institute National Key Laboratory of Science and Technology on Aircraft Control Xi'an China

ISBN: (纸本)9798350366600

3D object detection is crucial for autopilot and augmented reality applications. However, accurate feature extraction is the key to achieve high-precision detection, but traditional methods face the challenges of information loss and computational inefficiency. To address this, we propose an enhanced feature extraction method. We first divide the 3D space into voxel grids of varying scales. Then, using 3D sparse convolution, we extract features which are compressed along the Z axis to form BEV (Bird's Eye View) feature images. An efficient multi-scale attention mechanism is then employed to enhance these BEV features. The refined feature map is subsequently located and classified through a CT-stacking module and RPN (Region Proposal Network). Voxel features from the proposal and 3D backbone are passed through a voxel RoI pool to directly extract RoI features from the 3D features for further refinement. Finally, a cascaded attention network refines the proposal and strengthens confidence prediction. Experiments on test set validate our method effectiveness, showing improved accuracy over traditional voxel methods. Overall, this enhanced feature extraction technique offers a promising solution for 3D target detection, particularly in scenarios demanding high real-time performance and precision. © 2024 IEEE.

关键词： Feature extraction

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