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检索条件"机构=State Key Laboratory of Aircraft Systems Integration Technology and Flight Simulation"

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NOSE WHEEL STEERING MODE ANALYSIS BASED ON aircraft OPERATION SCENARIOS

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

引用

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

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

引用

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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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...

引用

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 AND IMPACT ON THE TARGET INJECTION POWER SMOOTHING ALGORITHM IN aircraft SYSTEM-LEVEL HIRF TESTING

RESEARCH AND IMPACT ON THE TARGET INJECTION POWER SMOOTHING ...

引用

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

作者： Zhao, Zijin Meng, Fanjiao Shanghai Aircraft Design Research Institute of COMAC Shanghai China Shanghai Aircraft Design Research Institute of COMAC Experimental Verification Center State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai China

The avionics system and brake system of an aircraft are critical, and their system-level HIRF test plays a key role in aircraft airworthiness certification, During the system-level Reverberation Chamber (RS) HIRF test process, the injected power value required at each frequency point during testing varies greatly, which leads to unstable output of the power amplifier and makes the actual received field strength in the reverberation chamber too high or too low, thus adversely affecting the test results. After studying and discussing the DO-160 standard and its supplementary guidance standard DO-357, it is found that the injected power smoothing algorithm can be introduced during the test to reduce the error between the actual received field strength in the reverberation chamber and the required field strength for testing. The test results show that after introducing the smoothing algorithm, the forward power curve is smoother, and the field strength obtained in the reverberation chamber is more stable, greatly reducing the situation of over-testing or under-testing, and improving the test stability. © The Institution of Engineering & technology 2024.

关键词： Reverberation

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Effective Aerodynamics Modeling Based on Physics-Informed Neural Network and flight Data 43

Effective Aerodynamics Modeling Based on Physics-Informed Ne...

引用

43rd AIAA DATC/IEEE Digital Avionics systems Conference, DASC 2024

作者： Wang, Huanyu Zhang, Chao Chen, Jiateng Tsinghua University School of Aerospace Engineering Beijing China Shanghai Aircraft Design & Research Institute State Key Laboratory of Airliner Integration and Flight Simulation Shanghai China

ISBN: (纸本)9798350349610

A high-performance aircraft aerodynamic model is a core component of the flight simulation device (FSD) and a critical function for the scenario-based airborne system validation and verification process. Thus, effective aerodynamics modeling is the key problem for the airborne system, integrated modular avionics (IMA) for example, integration and certification. In this paper, an aerodynamic modeling method was proposed, based on a neural network that makes use of the physical knowledge of computational fluid dynamics (CFD) and training data from real flight. Using another flight data as validation data, simulation analysis is conducted and the results show that (1) the accuracy performance is improved compared with the traditional methods, which means the aerodynamic characteristics model with effective prediction can be integrated into the FSD real-time environment;and (2) the method has an increased degree of generalization performance. This model was used in airborne system development, with other potential applications for pilot training, and scientific research in a D-level FSD. © 2024 IEEE.

关键词： flight simulators

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UNCERTAINTY ANALYSIS METHOD FOR HIRF TEST OF CIVIL aircraft SYSTEM

UNCERTAINTY ANALYSIS METHOD FOR HIRF TEST OF CIVIL AIRCRAFT ...

引用

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

作者： Meng, Fanjiao Wei, Jiasi Shanghai Aircraft Design and Research Institute of CO MAC Experimental Verification Center State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai China Key Laboratory of Bioanalvsis and Metrology for State Market Regulation Shanghai Institute of Measurement and Testing Technology Shanghai China

Utilizing the reverberation chamber to build a system-level HIRF test system for civil aircraft, and the influencing factors of the uncertainty of the test system were qualitatively analyzed through the establishment of a mathematical model. The uncertainty is extended by quantitative analysis of the mathematical model, the measurement uncertainty of the HIRF test system is calculated, and the uncertainty factor influence is controlled to ensure the accuracy and reliability of the test results. © The Institution of Engineering & technology 2024.

关键词： Reverberation

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A Head and Eye Pose Detection and Tracking Method in Intelligent Cockpits 16

A Head and Eye Pose Detection and Tracking Method in Intelli...

引用

16th International Conference on Intelligent Human-Machine systems and Cybernetics, IHMSC 2024

作者： Fan, Minghao Guo, Weihong Cheng, Sheng Zhang, Shenghai Zhao, Qijie Shanghai University School of Mechatronic Engineering and Automation Shanghai China State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai Aircraft Design and Research Institute Shanghai China Commercial Aircraft Corporation of China Ltd Shanghai China

ISBN: (纸本)9798331540241

With the ongoing progress in artificial intelligence, human-machine interaction technologies, rooted in electrification, connectivity, intelligence, and sharing, have emerged as the predominant focus for the future of intelligent cockpits. This paper, by scrutinizing the present requirements for information processing from a human-machine interaction standpoint, proposes a head and eye pose detection and tracking method in intelligent cockpits, enabling accurate perception of the driver's intentions. This scheme incorporates three core modules: information acquisition, information processing, and intention perception. To implement this, we employ a Driver Monitoring System (DMS) to gather comprehensive facial data from drivers. By integrating both depth and grayscale feature information from these recordings, we accurately identify key facial landmarks and the precise detection of the head and eye pose of the driver. Leveraging our custom-built simulated driving environment, we then undertake an in-depth analysis of the drivers' behavioral intentions using the proposed head and eye position detection method, effectively validating the reliability and efficacy of our proposed intention awareness solution. This research thereby charts a new course for advancing human-machine interaction designs and strategies for intelligent cockpits, offering a fresh perspective of the head and eye pose detection and tracking method that can pave the way for enhanced safety, efficiency, and user experience in the cockpits of tomorrow. © 2024 IEEE.

关键词： Reliability analysis

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RESEARCH ON INSTALLATION RELATIONSHIP BETWEEN DOOR UPLOCK AND ROLLER FOR CIVIL aircraft

RESEARCH ON INSTALLATION RELATIONSHIP BETWEEN DOOR UPLOCK AN...

引用

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

作者： Leilei, Liu Qingtang, Meng Wenjie, Chen Yifan, Song Hao, Wang Shanghai Aircraft Design and Research Institute State Key Laboratory of Airliner Integration Technology and Flight Simulation No. 5188 Jin Ke Road Shanghai China Shanghai Aircraft Design and Research Institution No.5188 Jinke Road Shanghai China

This paper has performed an research for the installation relationship of MLG(Main Landing Gear) inner door uplock and roller. The interaction between hook, end stop of uplock and roller of MLG door is analyzed, key factors to stop the roller from moving away from uplock when it’s unlocked have been found. Tests of three cases on Iron Bird have been designed to verify the analysis result. The findings in this paper can be used to instruct the match installation design of MLG door uplock and the roller. © The Institution of Engineering & technology 2024.

关键词： Rollers (machine components)

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Nonlinear optimal control of rope hook recovery process

Nonlinear optimal control of rope hook recovery process

引用

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

作者： Huang, Min He, Cheng Hu, Xiaowei State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai China COMAC Shanghai Aircraft Design and Research Insti Shanghai China Nanjing University of Aeronautics Astronautics UAV Research Institute Shanghai200126 China

Fixed-wing UAV recovery technology is a key factor in determining the performance of fixed-wing UAVs, and as a new type of recovery method, rope hook recovery has the advantages of simple form and high recovery efficiency, but also has the defects of high overload and uncontrollable recovery process. In order to compensate for this defect, control is introduced into the rope hook recovery system. Firstly, a fixed-damped and variable-damped UAV hook recovery dynamics model is established, and the input and output of the UAV hook recovery process are decoupled and decomposed into two S1SO systems. After that, a linear quadratic controller is used to track the velocity and displacement in all directions and feedback is well realized to approximate the planning results . The results show that the variable damping recovery system has the advantages of rapid recovery and smooth overloading over the fixed damping recovery system. © The Institution of Engineering & technology 2024.

关键词： Hooks

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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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