检索结果-内蒙古大学图书馆

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

来源：评论

学校读者我要写书评

暂无评论

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

来源：评论

学校读者我要写书评

暂无评论

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)

来源：评论

学校读者我要写书评

暂无评论

MODEL-BASED TESTING METHOD FOR FLIGHT SIMULATOR QTG TESTING

MODEL-BASED TESTING METHOD FOR FLIGHT SIMULATOR QTG TESTING

引用

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

作者： Qu, Xiaoyu Xie, Gangtao Tang, Qing Shanghai Aircraft Design and Research Institute Commercial Aircraft Corporation of China Ltd. Shanghai China State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai China

Fidelity of the simulator directly reflects the consistency of flight characteristics between the flight simulator and the aircraft. Generally, the fidelity of the flight simulator is evaluated through QTG objective testing and pilot-in-loop subjective testing. QTG objective testing injects flight test data of specific test items into the flight simulator, drives the simulator in reverse, and examines whether the deviation between the simulator response and flight test data meets tolerance requirements. The engineering simulator will be frequently modified in the progress of aircraft design, so QTG objective testing method for training simulator fidelity test based on guide of airworthiness standards is no longer suitable. In addition, the QTG test cases of the engineering simulator may experience significant changes depending on the changes of scope and test cases. Considering the above characteristics of engineering simulators and the complexity of modern civil aircraft design, a new method is needed for effective and efficient QTG test of simulators. In this paper, a Model-based Testing Method for QTG objective testing of engineering simulators is proposed, which achieves flexibility and adaptability by designing a test model. Based on the model of test cases, a workflow for automatically generating test cases is formed. © The Institution of Engineering & technology 2024.

关键词： Flight simulators

来源：评论

学校读者我要写书评

暂无评论

PREDICTION METHOD OF COMPRESSIVE STRENGTH AFTER IMPACT FOR FIBER REINFORCED PLASTIC COMPOSITE BASED ON DAMAGE FRACTAL DIMENSION

PREDICTION METHOD OF COMPRESSIVE STRENGTH AFTER IMPACT FOR F...

引用

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

作者： Jiang, Wen Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing Engineering Institute of Aircraft Systems AVIC Nanjing211106 China

The bearing capacity of fiber reinforced plastic (FRP) composite is highly sensitive to low-speed impact damage, making the prediction of compressive strength after impact crucial for their engineering applications. In this study, residual compressive strength tests were conducted on laminates of carbon fiber reinforced plastic (CFRP) 5284RTM/U3160 with three different layups under barely visual inspection damage (BV1D). Prior to compression testing, the impact damage morphology of laminates with different layups was captured using C-scanning, and the impact damage morphology was studied based on fractal dimension. The research results indicate that specimens with higher damage fractal dimensions exhibit lower compressive strength after impact. Based on this, a prediction model for the compressive strength of composite materials after impact was proposed, which is based on the fractal dimension of the impact damage morphology. This method takes the impact damage morphology as an equivalent geometric component - Sierpinski carpet, and obtains the area of laminates no longer participating in load-bearing after damage through the damage fractal dimension, thereby obtaining the residual compressive strength of the laminates. The predicted results of the model match well with experimental results, and it does not require impact energy as an input parameter, making it convenient for engineering applications. © The Institution of Engineering & technology 2024.

关键词： Compression testing

来源：评论

学校读者我要写书评

暂无评论

Design and simulation of aircraft altitude control based on RBFPID controller

Design and simulation of aircraft altitude control based on ...

引用

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

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

Altitude control is crucial for flight. In cruise flight, it is important to avoid longitudinal movement of the aircraft. Maintaining a fixed favorable altitude can improve the economy of the aircraft and increase its range. This can be achieved by using a longitudinal dynamics model of the aircraft and the root trajectory method, which is constructed based on the pitch angle and pitch angle rate feedback of the stabilizing and damping controllers. To enhance the control performance and robustness of altitude control, it is suggested to replace the traditional altitude P1D controller with the RBFPID(Radical Basis Function Proportion Integral Differential) controller. The results indicate that the use of the RBFPID controller is beneficial for improving the control performance of the altitude modes . © The Institution of Engineering & technology 2024.

关键词： Flight paths

来源：评论

学校读者我要写书评

暂无评论

SIMULATION CALCULATION AND OPTIMIZATION OF AERIAL REFUELING OF aircraft FUEL SYSTEM

SIMULATION CALCULATION AND OPTIMIZATION OF AERIAL REFUELING ...

引用

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

作者： Wang, Chenchen Wang, Yangyang Gu, Lixin AVIC Nanjing Engineering Institute of Aircraft Systems The Aviation Electromechanical System Integration of Aviation Science and Technology Key Laboratory Nanjing211106 China

In order to ensure that the initial design of the fuel system meets the requirements of aircraft aerial refueling and related standards, a simulation model of an aircraft fuel system was established based on the AMESim simulation platform. The aerial refueling process was calculated under given conditions, and the initial design of the fuel system is optimized based on the calculation results. Results showed that both the initial and optimized fuel systems meet the requirements for refueling time, and the requirements of electrostatic protection for the fuel flow rate inside the pipeline and inlet of the fuel tank during refueling. The optimized fuel system has a more similar refueling rate for each fuel tank and can effectively reduce the weight of fuel system's pipelines. The calculation results can provide guidance for the initial design of fuel system. © The Institution of Engineering & technology 2024.

关键词： aircraft fuels

来源：评论

学校读者我要写书评

暂无评论

A hybrid piecewise FDD strategy for refrigeration charge fault of airborne vapor-compression cycle system

引用

INTERNATIONAL JOURNAL OF REFRIGERATION 2022年 135卷 164-173页

作者： Sun, Chengbin Wang, Hexu Jiang, Yanlong Gao, Zanjun Wang, Ju [a]Key Laboratory of Aircraft Environment Control and Life Support MIIT Nanjing University of Aeronautics and Astronautics 29 Yudao St. Nanjing 210016 China [b]Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing 211106 China

Many researchers have carried out study on refrigerant charge fault for variable refrigerant flow (VRF) airconditioning system, while few pay attention to refrigerant charge fault for vapor-compression refrigerant cycle system (VCS) of enhanced vapor injection (EVI) with a flash tank onboard. To develop a strategy for refrigerant charge fault of the above system, the optimization methods have been implemented to predict the refrigerant charge level (RCL) based on virtual refrigerant charge (VRC) models. Firstly, Pearson correlation coefficient analysis is employed to obtain the characteristic parameters. Secondly, a piecewise modified VRC model with the different characteristic parameters from VRC models is obtained for two cases of RCL < 75% and RCL > 75%. Meanwhile, combined with the principal component analysis (PCA) and the support vector machine (SVM) algorithm, a PCA-SVM model is developed to improve the prediction accuracy, and the average root mean squared error (RMSE) is only 7.8 compared to 14.9 of the modified VRC model when RCL > 75%, meanwhile, the correctly detected ratio is improved from 62.8% to 84.5%. Then, for solving the difficulty of fault detection and diagnosis (FDD) when RCL > 160%, the moving time window average (MA) algorithm is introduced and an online PCA-MA-SVM model is developed. Finally, a hybrid piecewise FDD strategy combined with three models for refrigeration charge fault in airborne VCS of EVI with a flash tank is obtained.

关键词： Vapor-compression refrigeration cycle system Enhanced vapor injection Refrigerant charge fault Support vector machine Moving time window average

来源：评论

学校读者我要写书评

暂无评论

DNN performance optimization based on Gemmini neural network hardware accelerator 4

DNN performance optimization based on Gemmini neural network...

引用

4th International Conference on Advanced Algorithms and Neural Networks, AANN 2024

作者： Zhao, Denghui He, Jianrui Jing, Xuyu Hou, Xibiao AVIC Xi’an Flight Automatic Control Research Institute Aviation Key Laboratory of Science and Technology on Aircraft Control Xi’an710065 China

ISBN: (纸本)9781510686106

Gemmini is an open-source, full-stack DNN accelerator generator. For an DNN algorithm running on Gemmini, traditional optimizations focus on changing Gemmini's hardware configuration (e.g., changing the size of internal storage and the size of the systolic array). This work proposes an an optimization-test iteration route combining Spike simulation and FPGA simulation under the constraints of unacceptable running speed of verilator simulator and limited FPGA resources. According to this route, this work starts from two aspects of hardware optimization and algorithm optimization. The internal storage size and calculation scale of Gemmini are changed in hardware, and the convolutional layer of Resnet50 neural network algorithm is optimized in algorithm. The experimental results show that for Resnet50 DNN algorithm, Gemmini with basic configuration provides 2000x speedup compared with running on CPU. On the platform of Gemmini accelerator, the optimization of hardware configuration provides 1.59x speedup for Resnet50. On the basis of the hardware optimization, the algorithm optimization provides 1.012x speedup. © 2024 SPIE.

关键词： Mathematical optimization Neural networks Field programmable gate arrays Data storage Evolutionary algorithms Convolution Detection and tracking algorithms Performance modeling Matrices

来源：评论

学校读者我要写书评

暂无评论

Influence of different weight reduction configurations of thermal/acoustic insulation blankets on the transmission loss of aircraft panel 4

Influence of different weight reduction configurations of th...

引用

2024 4th International Conference on Mechatronics technology and Aerospace Engineering, ICMTAE 2024

作者： Zhao, Yi Dai, Zheng Meng, Lingda State Key Laboratory of Airliner Integration Technology and Flight Simulation Shanghai200000 China COMAC Shanghai Aircraft Design & Research Institute Shanghai200000 China

Thermal/acoustic insulation blankets are the main material for noise reduction of aircraft panel structures. Due to the lack of design experience of domestic civil aircraft manufacturers, it is difficult to carry out the weight reduction design of the thermal/acoustic insulation blankets based on meeting the cabin noise requirements. Therefore, the sound insulation performances of the metal fuselage panel with different weight reduction configurations of the thermal/acoustic insulation blankets are tested by using the sound intensity method under the condition of an anechoic-reverberation chamber. Based on the analysis of the experimental results, the influence laws of different weight reduction configurations of the thermal/acoustic insulation blankets on the sound insulation performance of the composite panel are summarized, which have important guiding significance for the weight reduction design of the thermal insulation and sound insulation layers for civil aircraft manufacturers. © 2025 Institute of Physics Publishing. All rights reserved.

关键词： Sound insulation

来源：评论

学校读者我要写书评

暂无评论

建议与咨询留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

时间限定

文献类型

馆藏选择

核心期刊

语言

文献类型

帮助

文字说明：

检索规则说明：

检索范例：

分类表

所选分类

限定检索结果

文献类型

馆藏范围

日期分布

学科分类号

主题

机构

作者

语言

请选择保存的检索档案：

请选择收藏分类：

通借通还

建议与咨询 留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

时间限定

文献类型

馆藏选择

核心期刊

语言

文献类型

帮助

文字说明：

检索规则说明：

检索范例：

分类表

所选分类

限定检索结果

文献类型

馆藏范围

日期分布

学科分类号

主题

机构

作者

语言

请选择保存的检索档案： 新增检索档案 确定 取消

请选择收藏分类： 新增自定义分类 确定 取消

通借通还

建议与咨询留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

请选择保存的检索档案：

请选择收藏分类：