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Landing gear system health assessment based on SVM and XGBoost dual-flow modeling

Landing gear system health assessment based on SVM and XGBoo...

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

作者： Chen, Wenjie Chen, Yong Xu, Yongxiang Jia, Zhikai Wan, Zhiping Shanghai Aircraft Design and Research Institute Shanghai5188 China State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai200126 China Commercial Aircraft Corporation of China Shanghai200126 China Harbin Institute of Technology Harbin201109 China Limited Shanghai200233 China

The landing gear system stands as one of an airplane's most crucial components, playing a pivotal role during take-off and landing phases. Its failure could result in catastrophic accidents, including belly landings, with severe consequences such as loss of life and aircraft destruction. Comprising a complex integration of mechanical, electrical, and hydraulic components, the landing gear system operates within a non-pneumatic zone, subjected to harsh working environments. Potential safety hazards, including mechanical wear, inadequate lubrication, and hydraulic equipment leakage, can compromise the system's extension capability, and in severe cases, lead to extension or retraction failure. Hence, effective management of landing gear health and early detection of system insecurities are imperative for ensuring aircraft safety. In this paper, a dual-flow model was developed based on SVM and XGBoost, facilitating accurate prediction of landing gear retraction and release times under varying external environmental conditions. This model serves as a foundation for assessing the health state of landing gear systems. © The Institution of Engineering & technology 2024.

关键词： aircraft accidents

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Control Accuracy Calculation of Flap & Slat System of Civil aircraft

Control Accuracy Calculation of Flap & Slat System of Civil ...

引用

Energy and Power Engineering, Control Engineering (EPECE), International Conference on

作者： Jian Xie State Key Laboratory of Airliner Integration Technology and Flight Simulation China

ISBN: (数字)9798350366099

ISBN: (纸本)9798350366105

The control accuracy of the flap & slat system of civil aircraft greatly affects the actual theoretical position of the flap & slat surface, which influences the aircraft’s ability to gain lift and the design of the structural stop block. Therefore, it is important to analyze the origins of the accuracy components to improve the control accuracy of the system. This paper introduces how the control accuracy of the flap & slat system affects the aircraft, analyzes each main factor of the system control accuracy and makes a specific analysis of its origins, and finally proposes a method based on the self-compensating balance of the computer to improve the control accuracy of the system. It is believed that this study is of great significance for the design of domestic large aircraft design related.

关键词： Power engineering Accuracy Costs Control engineering Gears Aerospace electronics Sensor systems

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DAMPING ORIFICE DESIGN OF A CIVIL aircraft'S TAIL BUMPER

DAMPING ORIFICE DESIGN OF A CIVIL AIRCRAFT'S TAIL BUMPER

引用

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

作者： Zhang, Ying Chen, Wenjie Shanghai Aircraft Design and Research Institution State Key Laboratory of Airliner Integration Technology and Flight Simulation No. 5188 Jinke Road Pudong New District Shanghai China Shanghai Aircraft Design and Research Institution No. 5188 Jinke Road Pudong New District Shanghai China

The damping orifice design and dynamic characteristics of a specific aircraft's tail bumper was studied. The systematic design method combining engineering estimation, theoretical analysis, co-simulation was proposed. To determine the build standard of damping orifice, firstly derived a damping dynamic equation of full-oil buffer, which help to set oil hole parameters, and build an equivalent model of tail bumper buffer drop dynamics, then conducted shock absorption simulation. This analysis yielded the dynamic characteristics against the stroke and time, validating the model and suitable oil hole design. Subsequently, a sleeve-type oil hole with equal diameter but variable distance was creatively designed. The design and analysis methods presented in the paper can serve as a reference for the development and design of future tail bumper buffers, contributing to the control of risks during minimum ground speed flight tests. © The Institution of Engineering & technology 2024.

关键词： Orifices

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Head Detection Method Based on Binocular Stereo Vision

Head Detection Method Based on Binocular Stereo Vision

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International Conference on Computer Engineering and Applications (ICCEA)

作者： Qiannan Zhang Shanghai Aircraft Design & Research Institute State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai China

ISBN: (数字)9798350386776

ISBN: (纸本)9798350386783

Binocular stereo vision technology is a critical area of research in computer vision, with widespread applications across various domains. Addressing the need for real-time crowd flow statistics, this study presents a head detection algorithm utilizing images captured by binocular cameras. The approach involves initial image rectification followed by analysis using binocular disparity and visual target acquisition algorithms. It further identifies head contours by examining depth profiles, depth map characteristics, and geometric features of the head's circular top area obtained from binocular stereo imaging. This method employs a depth-layered approach to extract head presence information, leveraging the circular head outline as a key geometric feature for recognition through a binocular stereo vision matching algorithm. The process efficiently detects head contours under binocular vision, resulting in high accuracy and speed in head detection within complex environments.

关键词： Visualization Head Accuracy Heuristic algorithms Interference Feature extraction Real-time systems

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Design and Implementation of Generator Drive Characteristics simulation Device for Civil aircraft

Design and Implementation of Generator Drive Characteristics...

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2024 8th International Conference on Electrical, Mechanical and Computer Engineering (ICEMCE)

作者： Fan Lv Shanghai Aircraft Design and Research Institute State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai China

ISBN: (数字)9798331506230

ISBN: (纸本)9798331506247

According to ground laboratory airworthiness verification test requirements of the civil aircraft electrical power system in CCAR25, it is necessary to simulate the drive characteristics of the aircraft power unit to the generator. In this paper, a generator drive characteristics simulation device is designed to meet this requirement. According to the requirements of steady state speed control accuracy and dynamic response characteristics, which have an important impact on the simulation of drive characteristics, the core functional modules of the device have been designed and implemented in detail, and the device is applied to the ground laboratory airworthiness verification test of the civil aircraft power system. The tests showed that the device has excellent drive characteristics, as well as the advantage of simple structure.

关键词： Accuracy Power system dynamics Velocity control Generators Regulation Software Steady-state aircraft aircraft propulsion Aerospace control

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Research on Digital Twin System of Large aircraft Ground Dynamics Test Platform

Research on Digital Twin System of Large Aircraft Ground Dyn...

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Chinese Automation Congress (CAC)

作者： Jiyang Sun Hongxin Wang Yifan Shao Shengjie Li State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai Aircraft Design & Research Institute Shanghai China

ISBN: (数字)9798350368604

ISBN: (纸本)9798350368611

The large aircraft ground dynamics test platform is a significant research infrastructure to test and simulate the ground dynamics characteristics of aircraft. However, there exist many problems in physical experiments and traditional model-based virtual experiments of this platform. Here we introduce the emerging digital twin technology to fully expand its comprehensive verification capabilities and enhance the digitized development level of the large aircraft ground dynamics systems. Firstly, the technical requirements of the digital twin system for the large aircraft ground dynamics test platform are analyzed, and its schematic design is completed. Then, a four-tier technical architecture including physical object, data network, digital twin and application scenario is constructed. An in-depth analysis of this digital twin system focusing on its potential research and application scenarios for aircraft ground dynamics is illustrated. Finally, the key technologies of digital twin construction and evaluation, as well as high-performance virtuality-reality hybrid networks are elaborated and analyzed, providing a certain basis for subsequent specific design and development.

关键词： Technical requirements Automation Atmospheric modeling Focusing Digital twins aircraft manufacture aircraft Dynamical systems

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System Engineering-Based flight simulation Device Design technology and Application Research 4th

System Engineering-Based Flight Simulation Device Design Tec...

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4th International Conference on Mechanical Design and simulation, MDS 2024

作者： Wang, Huanyu Zhang, Chao Chen, Yong School of Aerospace Engineering Tsinghua University Beijing10084 China State Key Laboratory of Airliner Integration and Flight Simulation Shanghai201210 China Shanghai Aircraft Design & Research Institute Shanghai201210 China Commercial Aircraft Corporation of China Ltd. Shanghai200126 China

ISBN: (纸本)9789819778867

The development of modern aviation industry urgently needs a large number of high-level flight simulation device (FSD) for multiple applications such as technologies research, aircraft test and pilot training. Traditionally, these FSD are manufactured by different TDM to meet individual requirement, which may encounter difficulty in correctness, integrity or fidelity. How to develop the FSD and its simulation packages for research, engineering and training scenarios with a more coordinated and efficient methodology is the key to the development of high-level FSD for one particular aircraft project. This paper proposes that FSD shall be classified, according to development process and control requirements into three categories, which are flight simulation Training Device (FSTD), flight simulation Engineering Device (FSED) and flight simulation Research Device (FSRD). In particular, the simulation package provide the basis for the evolution of the multiple applications of the FSD. In this paper, the key design of FSD and simulation packages is given by proposing a technical strategy, which is based on system engineering (SE), with the development of FSED simulation packages as the central objective, and evolving and applying them to more mission such as research and training by validation and verification (V&V) of the requirement. This technical strategy shows major value (1) in optimizing correctness, integrity, and fidelity through process assurance, (2) in shortening the development cycle and reducing the cost by reducing duplication of efforts, (3) in reducing the technical risk of the simulation package, which is accompanied by aircraft and system design and development, and (4) in standardizing and eliminating of inconsistencies of the simulation modeling data, which is oriented from FSED with rigor configuration management. This research intends to promote the development of the domestic aircraft and the growth of the FSD-connected technology. © The Author(s) 2

关键词： flight simulators

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Model-based design of airborne equipment vulnerability management and alarm system

Model-based design of airborne equipment vulnerability manag...

引用

International Conference on Computer Engineering and Applications (ICCEA)

作者： Jingyi Wang Sen Zhang Bin Gao Quanxin Cao State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai China

ISBN: (数字)9798350386776

ISBN: (纸本)9798350386783

With the extensive application of information technology in civil aircraft airborne systems, airborne systems are facing the threat of security vulnerabilities. For this reason, this paper adopts model-based system engineering method to analyze the application scenario of vulnerability management alarm for airborne equipment and designs the overall architecture of the vulnerability management and alarm system for civil aircraft airborne equipment, as well as the key subsystems such as vulnerability automatic collection and asset management, vulnerability tracking and alarm, vulnerability management database, which are implemented in Java language, developed based on Spring Boot and VUE frameworks, deployed in microservice mode, with features such as rich functions and easy operation. It's verified by actual use that the system can meet the functional requirements of vulnerability management and alarm of civil aircraft airborne system.

关键词： Java Analytical models Databases Atmospheric modeling Computer architecture Alarm systems systems engineering and theory

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Connection strength analysis for composite fuselage gate structures of civil aircraft 3

Connection strength analysis for composite fuselage gate str...

引用

2024 3rd International Conference on Applied Mechanics and Advanced Materials, ICAMAM 2024

作者： Wu, Yang Qiu, Xudong Bai, Chunyu Liu, Hu State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai201210 China COMAC Shanghai Aircraft Design & Research Institute Shanghai201210 China National Key Laboratory of Strength and Structural Integrity Xi'an710065 China School of Mechanics and Aerospace Engineering Southwest Jiaotong University Chengdu610031 China

Civil aircraft boarding gate is an important channel for passengers to enter and exit the aircraft, and is also an important part of the aircraft structure, with the function of maintaining cockpit pressure. Traditional boarding doors are made of metal, and with the large number of composite materials used in the bearing structure of civil aircraft, composite boarding doors are also used in new civil aircraft. The strength of the connection inside the new composite boarding gate is related to the safety of passengers and crew. This paper focuses on the connection problem of the internal structure of composite boarding gate, aiming to analyze its connection strength under working conditions. This paper establishes a real finite element model of the boarding gate according to the loading condition and force transmission characteristics of the civil aircraft door and analyzes the connection strength of the structure such as the skin and the transverse and longitudinal beams, the skin and the side frame, the transverse and longitudinal beams connection, and the stop block in turn. The study shows that the strength of the connecting structures of the boarding gate designed by using composite materials is reasonable and can meet the service requirements of the boarding gate, thus demonstrating the rationality of the boarding gate structure designed with composite materials. © Published under licence by IOP Publishing Ltd.

关键词： Cockpits (aircraft)

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System and method for detecting the timing of electromechanical control of the aircraft power supply system

System and method for detecting the timing of electromechani...

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2024 8th International Conference on Electrical, Mechanical and Computer Engineering (ICEMCE)

作者： Gang Yang Shanghai Aircraft Design and Research Institute Shanghai China State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai China

ISBN: (数字)9798331506230

ISBN: (纸本)9798331506247

The electric power multiplexing path of aircraft power supply system is mainly realized by a large number of electromechanical/intelligent control units performing combined actions in accordance with the requirements of the power distribution logic. In order to demonstrate the compliance of the aircraft power supply system distribution logic design, the overall working timing of the electromechanical control units needs to be detected and verified during the ground development test phase. An electromechanical control timing detection system and method of the aircraft power supply system is designed and implemented, which has three levels, and the three levels are cited each other and realized hierarchically. The system has the ability to visually check the sketch page instructions, monitor the accuracy of the unit’s actions and its control timing, and detect the validity of its actions and power supply in case of a fault state. The system and method have the advantages of being based on a real power supply system under test, a comprehensive system architecture implementation, and a standardised and efficient detection process. The system and method can meet the needs of electromechanical control timing detection, and has been successfully applied to compliance verification test and airworthiness certification work for power supply system of a certain type of civil aircraft.

关键词： Power supplies systems architecture Power distribution Control systems Conformance testing Timing aircraft aircraft propulsion Certification Aerospace control

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