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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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RESEARCH ON THE VIRTUAL-REAL HYBRID integration OF flight SIMULATOR BASED ON MULTI-PROTOCOL HETEROGENEOUS FUSION MECHANISM

RESEARCH ON THE VIRTUAL-REAL HYBRID INTEGRATION OF FLIGHT SI...

引用

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

作者： Li, Shengjie Wang, Hongxin Li, Linwen Xie, Dianhuang COMAC Shanghai Aircraft Design and Research Institute Shanghai China State Key Laboratory of Airliner Integration Technology and Flight Simulation China

It is crucial to confirm the dynamic performance of the flight process during aircraft development. flight simulators provide a low-cost, flexible, and virtual test tool that can support comprehensive operating scenario tests. This technology simulates the real flight process through computer simulation of aircraft digital models, as well as real-time interaction between the models and physical objects such as the flight control devices during pilot-in-the-loop. Traditionally, the reliability of this virtual-real hybrid integration is difficult to guarantee, which restricts the high-fidelity simulation of real flight processes during complex operating scenarios. Therefore, this article proposes a multi-protocol heterogeneous fusion mechanism to ensure the virtual-real hybrid integration for flight simulators. In this method, heterogeneous signal interaction standards are established based on virtual bus (ED-247A), and a flexible and reliable distribution mechanism is constructed by data distribution services (DDS), and reliable virtual-real hybrid integration is achieved by time sensitive network (TSN). The results show that this method is effectively compatible with multi-source heterogeneous signals, supports flexible deployment of high-speed concurrent distributed systems, has zero packet loss, low jitter, and low latency in signal transmission process, which meets the requirements of reliable virtual-real hybrid integration, and ensures the real-time performance of flight simulators. © The Institution of Engineering & technology 2024.

关键词： flight simulators

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RESEARCH ON REAL TIME simulation integration AND PLATFORM EVALUATION OF MULTI SOURCE HETEROGENEOUS MODELS FOR aircraft

RESEARCH ON REAL TIME SIMULATION INTEGRATION AND PLATFORM EV...

引用

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

作者： Chen, Li Li, Linwen Wang, Hongxin Xie, Dianhuang COMAC Shanghai Aircraft Design and Research Institute Shanghai China State Key Laboratory of Airliner Integration Technology and Flight Simulation China

In response to the demand for full aircraft virtual integration simulation in the development process of civil aircraft, this paper proposes a real-time simulation integration and platform evaluation method for multi source heterogeneous models of the entire aircraft system. This method converts different forms of multi source heterogeneous models of the entire aircraft into executable real-time simulation code. The real-time simulation code is loaded into different real-time simulation nodes, combined with human-computer interaction systems, comprehensive control systems, and display systems to form a distributed real-time simulation platform for full aircraft virtual integration. Model evaluation and platform evaluation work are carried out on the integration platform, and the maturity of the integration platform is confirmed based on experimental requirements. Ensure that the integrated platform has the ability to conduct virtual simulation experiments. This technology can support real-time simulation testing of full aircraft virtual integration during the initial design stage of civil aircraft development, and support confirmation of aircraft level functional and safety requirements. © The Institution of Engineering & technology 2024.

关键词： Ability testing

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System and method for detecting the timing of electromechanical control of the aircraft power supply system 8

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

引用

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

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

ISBN: (纸本)9798331506230

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. © 2024 IEEE.

关键词： aircraft power systems

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Research on Calculation Method of Constant Voltage and Constant Frequency Starting Voltage Base on Brushless DC Motor Without Position Sensor 7th

Research on Calculation Method of Constant Voltage and Const...

引用

7th China Aeronautical Science and technology Conference, CASTC 2024

作者： Xue, Mizi Shanghai Aircraft Design and Research Institute Shanghai201210 China State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai200126 China

ISBN: (纸本)9789819797738

This paper analyzes the constant voltage and constant frequency starting method in detail, gives a detailed introduction to the constant voltage and constant frequency starting voltage and phase change frequency of the brushless DC motor with a 120° trapezoidal waveform of the back electromotive force, and analyzes the basic principle of constant voltage and constant frequency starting and the conditions that need to be met for realizing accelerated phase change. Combined with the mathematical model of the motor and the mechanical equations of motion, the motor is analyzed for each phase change of the renewed current phase and the conduction phase, and the calculation method of the constant voltage and constant frequency starting voltage range is deduced and the basis for determining the phase change frequency is given. The rotor motion equations and speed change equations are verified through simulation and compared with the actual rotor position and speed magnitude to verify the accuracy of the calculation results of constant voltage and constant frequency starting voltage and phase change frequency. © Chinese Society of Aeronautics and Astronautics 2025.

关键词： Brushless DC motors

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Nose landing gear strength test strain gauge vs FEA correlation

Nose landing gear strength test strain gauge vs FEA correlat...

引用

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

作者： Xu, Wenmin Cao, Shixu Chen, Wenjie Yang, Shangxin State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai China COMAC Shanghai Aircraft Design & Research Institute Shanghai China

This article conducts finite element modeling analysis on the nose landing gear, and calculates and analyzes several severe load conditions. Strength tests were conducted on the nose landing gear to verify that the static strength of the landing gear meets the requirements. By comparing the strength test and finite element analysis results of the landing gear, it is shown that the analysis and test results are within the tolerance range, indicating that the finite element analysis and results are reliable and can be used for subsequent analysis. © The Institution of Engineering & technology 2024.

关键词： Strain gages

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Research on testing method for damping loss factor of non self supporting materials

Research on testing method for damping loss factor of non se...

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

作者： Hu, Haifeng Dai, Zheng COMAC Shanghai Aircraft Design & Research Institute Shanghai China State Key Laboratory' of Airliner Integration Technology and Flight Simulation Shanghai China

Based on the differences between time-domained and frequency-domained methods, this article proposes an combined testing method for the DLF of non self-supporting materials by using the Oberst beam method. That is, at low frequencies or small damping frequency points, use the DLF of the composite beam, which is obtained from the time-domained method, to replace the results from the frequency-domained method, then the loss factor of non self-supporting damping materials can be calculated. And it was applied to test the DLF of a certain rubber material, successfully obtaining damping results at four modal frequency points. © The Institution of Engineering & technology 2024.

关键词： Damping

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AN IMMERSIVE SUBJECTIVE EVALUATION METHOD FOR THE SOUND QUALITY IN CIVIL aircraft CABINS

AN IMMERSIVE SUBJECTIVE EVALUATION METHOD FOR THE SOUND QUAL...

引用

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

作者： Hu, Haifeng Dai, Zheng Zhao, Yi Wang, Yudi Meng, Lingda COMAC Shanghai Aircraft Design & Research Institute Shanghai China State Key Laboratory' of Airliner Integration Technology and Flight Simulation Shanghai China

The sound quality and comfort inside civil aircraft cabins have gradually become a key factor affecting their market competitiveness. Optimizing the cabin noise environment and improving comfort are of great significance. This article is based on a simulated three-dimensional sound field environment inside an aircraft engineering prototype, selecting eight seats and using the grade scoring method to conduct subjective evaluation tests on the sound quality of a certain type of test aircraft under six operating conditions, including ground taxiing, takeoff, cruising, and so on. After excluding irrelevant results, accurate subjective evaluation results for each seat and working condition are obtained. © The Institution of Engineering & technology 2024.

关键词： Cabins (aircraft)

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Research on drop test methods for four-wheel bogie-type landing gear for large civil aircraft

Research on drop test methods for four-wheel bogie-type land...

引用

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

作者： Dongdong, Ge Zihao, Zhang Kuan, Wang Shanghai Aircraft Design and Research Institute Shanghai China State key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai200126 China

The landing gear drop test primarily verifies the landing gear's buffer system's ability to absorb the aircraft's kinetic energy during the landing process, while ensuring that the load, structure, and filling parameters meet design requirements. Common drop test methods include the reduced mass method and the pseudo-lift method, both based on the principle of energy equivalence. Currently, comparative research on these methods mainly focuses on tandem dual-wheel landing gears, with limited studies comparing drop test methods for bogie-type landing gears. This study focuses on the main landing gear of a specific aircraft, which features a four-wheel bogie-type structure. Using LMS *** Motion dynamics simulation software, simulations were conducted for both the pseudo-lift method and the reduced mass method to compare key parameters such as landing impact loads and system power under the absorption of equivalent energy. © The Institution of Engineering & technology 2024.

关键词： Landing gear (aircraft)

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RESEARCH ON FAILURE MODE ANALYSIS AND REDUNDANT BACKUP DESIGN OF EMA

RESEARCH ON FAILURE MODE ANALYSIS AND REDUNDANT BACKUP DESIG...

引用

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

作者： Hu, Xiaowei Huang, Min State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai China COMAC Shanghai Aircraft Design and Research Institute Shanghai China

The article designs an EMA functional platform that allows for dual inputs, studies the failure modes and probabilities of EMA, and then uses FHA method to calculate the likelihood of EMA functional loss and abnormality. Finally, failure mode experiments were conducted to analyze relevant data, and it was found that redundant backup design can reduce the impact of system failures on performance, improve system availability and safety. © The Institution of Engineering & technology 2024.

关键词： Failure modes

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ELECTRIC LOAD simulation METHOD OF aircraft ELECTRICAL ENERGY DISTRIBUTION BASED ON FPGA

ELECTRIC LOAD SIMULATION METHOD OF AIRCRAFT ELECTRICAL ENERG...

引用

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

作者： Xie, Jianghua Wang, Bangting Cai, Mengdi Ren, Yue COMAC Shanghai Aircraft Design Research Institute shanghai China State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai China

aircraft electrical load management is one of the important functions of aircraft power system, which ensures the normal operation of the whole aircraft electrical equipment. This paper introduces an electric load simulation method of aircraft electrical energy distribution based on FPGA. Based on this method, a hybrid distributed platform of FPGA real-time simulator and traditional real-time simulator is built. And the feasibility of the method is verified by modeling and simulation of a typical aircraft power system architecture. The simulation results are of great significance to the design of electrical load management of aircraft power system. © The Institution of Engineering & technology 2024.

关键词： aircraft power systems

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