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2021 6th International Conference on Information science, Computer technology and Transportation, ISCTT 2021

作者： Zhou, Qi-Fan Zhao, Wanli Li, Kai Qiao, Yan-Ping Guo, Ying-Qing School of Power and Energy Northwestern Polytechnical University Xi’an710072 China Science and Technology on Altitude Simulation Laboratory Mianyang621700 China

ISBN: (纸本)9783800757282

In order to achieve the data management and data analysis of aero-engine experimental equipment, it is necessary to perform data migration on the data in the historical database. In this paper, two real-time data synchronization methods based on the JDBC interface and Mybatis structure under the Spring Boot framework were proposed, and they were applied to the altitude simulation test facility experiment to achieve the real-time data synchronization function between the historical database and the local database. For the JDBC interface mode, the switching mode that integrated full data synchronization and incremental data synchronization was used to achieve continuous data synchronization tasks. For the Mybatis structure mode, the integration of master-slave data source configuration logic and multi-threaded parallel processing flow grouping autonomy methods, the continuous data synchronization task was achieved. The simulation test results verify the efficiency and real-time performance of the two methods proposed in this paper. © VDE VERLAG GMBH · Berlin · Offenbach.

关键词： Information management

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An Energy-Constrained Optimization-Based Structured Pruning Method for Deep Neural Network Compression 22

An Energy-Constrained Optimization-Based Structured Pruning ...

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22nd IEEE International Conference on Communication technology, ICCT 2022

作者： Liu, Siping Li, Qiang Peng, Bo Qiao, Yanping Lin, Maosong Zeng, Qiang School of Information Engineering Southwest University of Science and Technology Mianyang China Science and Technology on Altitude Simulation Laboratory Mianyang China School of Computer Science and Technology Southwest University of Science and Technology Mianyang China

ISBN: (纸本)9781665470674

Deep neural networks are widely used in modern intelligent applications due to their superior ability to express reality, and these intelligent applications run on highly energy-constrained edge devices. Neural network structured pruning is an efficient method to reduce the energy consumption of neural networks. This paper proposes an energy-constrained optimization-based structured pruning method to compress deep neural network. This method uses the energy budget provided by edge devices as a constraint for neural network pruning. The key idea is to formulate deep neural network structured pruning as an optimization problem, in which the energy estimate of each layer is used as the Frobenius norm optimization constraint for the convolution kernel weights. Then the importance of all convolution kernels in the network can be evaluated, thereby the neural network structure can be pruned according to the importance to reduce the energy consumption and memory size of the neural network. Compared with traditional heuristic structured pruning methods, our proposal enables neural networks to achieve higher accuracy with the same or lower energy budget. © 2022 IEEE.

关键词： Deep neural networks

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Finite-time Sliding Mode Control Method for a Class of Air Intake Testing Devices 4

Finite-time Sliding Mode Control Method for a Class of Air I...

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4th International Symposium on Artificial Intelligence and Intelligent Manufacturing, AIIM 2024

作者： Li, Yunli Pu, Ming Zhang, Gexiang Dan, Zhihong Zhang, Song School of Automation Chengdu University of Information Technology Chengdu China Science and Technology on Altitude Simulation Laboratory AECC Sichuan Gas Turbine Establishment Mianyang China

ISBN: (纸本)9798331541729

This paper proposes a novel finite-time sliding mode control method for the enhancement of the velocity and precision in the control of temperature and pressure within a class of air intake testing devices. Initially, a simulation model of the device without heat transfer characteristics is constructed in MATLAB, followed by the design of a sliding mode control strategy for the device. Then an auxiliary function characterized by a normal distribution is introduced, facilitating the formulation of a novel finite-time reaching law and an integral sliding mode surface, and culminating in the derivation of a finite-time sliding mode controller. Employing the Lyapunov stability theorem, it is demonstrated that the system state attains its equilibrium point within a finite time. Finally, three different reaching laws are used with the proposed sliding mode surface to construct the three controllers. simulation experiments are conducted in the simulation model using the aforementioned three sliding mode controllers. The simulation results indicate that the sliding mode controller under the influence of the reaching laws presented in this paper significantly enhances the servo tracking performance of temperature and pressure. © 2024 IEEE.

关键词： MATLAB

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Modified robust optimal adaptive control for flight environment simulation system with heat transfer uncertainty

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Chinese Journal of Aeronautics 2021年第2期34卷 420-431页

作者： Meiyin ZHU Xi WANG Xitong PEI Song ZHANG Zhihong DAN Nannan GU Shubo YANG Keqiang MIAO Huairong CHEN Jiashuai LIU School of Energy and Power Engineering Beihang UniversityBeijing 100083China Collaborative Innovation Center for Advanced Aero Engine Bejing 100083China Science and Technology on Altitude Simulation Laboratory AECC(Aero Engine Corporation of China)Sichuan Gas Turbine EstablishmentMianyang 621000China

To solve the rapid transient control problem of Flight Environment simulation System(FESS) of altitude Ground Test Facilities(AGTF) with large heat transfer uncertainty and disturbance, a new adaptive control structure of modified robust optimal adaptive control is *** mathematic modeling of FESS is given and the influence of heat transfer is analyzed through energy view. To consider the influence of heat transfer in controller design, we introduce a matched uncertainty that represents heat transfer influence in the linearized system of FESS. Based on this linear system, we deduce the design of modified robust optimal adaptive control law in a general way. Meanwhile, the robust stability of the modified robust optimal adaptive control law is proved through using Lyapunov stability theory. Then, a typical aero-engine test condition with Mach Dash and Zoom-Climb is used to verify the effectiveness of the devised adaptive controller. The simulation results show that the designed controller has servo tracking and disturbance rejection performance under heat transfer uncertainty and disturbance;the relative steady-state and dynamic errors of pressure and temperature are both smaller than 1% and 0.2% respectively. Furthermore,the influence of the modification parameter c is analyzed through simulation. Finally, comparing with the standard ideal model reference adaptive controller, the modified robust optimal adaptive controller obviously provides better control performance than the ideal model reference adaptive controller does.

关键词： altitude ground test facilities Flight environment simulation system Heat transfer Model reference adaptive control Optimal control modification Uncertainty

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Intention Estimation of Adversarial Spatial Target Based on Fuzzy Inference

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Intelligent Automation & Soft Computing 2023年第3期35卷 3627-3639页

作者： Wenjia Xiang Xiaoyu Li Zirui He Chenjing Su Wangchi Cheng Chao Lu Shan Yang School of Information and Software Engineering University of Electronic Science and Technology of ChinaChengdu610054China Institute of Logistics Science and Technology Beijing100166China Science and Technology on Altitude Simulation Laboratory Sichuan Gas Turbine Establishment Aero Engine Corporation of ChinaMianyang621000China Department of Chemistry Physics and Atmospheric SciencesJackson State UniversityJacksonMS 39217USA

Estimating the intention of space objects plays an important role in air-craft design,aviation safety,military and otherﬁelds,and is an important refer-ence basis for air situation analysis and command *** paper studies an intention estimation method based on fuzzy theory,combining prob-ability to calculate the intention between two *** method takes a space object as the origin of coordinates,observes the target’s distance,speed,relative heading angle,altitude difference,steering trend and etc.,then introduces the spe-ciﬁc calculation methods of these *** calculation,values are input into the fuzzy inference model,andﬁnally the action intention of the target is obtained through the fuzzy rule table and historical weighted ***-iﬁed by simulation experiment,the target intention inferred by this method is roughly the same as the actual behavior of the target,which proves that the meth-od for identifying the target intention is effective.

关键词： Intension estimation motion parameters calculation fuzzy inference fuzzy rule table historical weighted probability

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Fault Diagnosis for Hydraulic Loading System of altitude simulation Test Facility Based on Multichannel 1D-CNN 13

Fault Diagnosis for Hydraulic Loading System of Altitude Sim...

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13th International Conference on Mechanical and Aerospace Engineering, ICMAE 2022

作者： Guo, Pengfei Peng, Jin Zhao, Wanli Diao, Xinyu Guo, Yingqing Northwestern Polytechnical University School of Power and Energy Xi'an710072 China Aecc Sichuan Gas Turbine Establishment Science and Technology on Altitude Simulation Laboratory Mianyang621700 China

ISBN: (数字)9781665472357

ISBN: (纸本)9781665472357

The hydraulic loading system is the system that simulates the operation of the aircraft airborne pump by extracting the power of the aero-engine during the altitude simulation test, and its safety and stability is very important during operation. Aiming at the shortcomings of traditional fault diagnosis in feature extraction, the intelligent method based on deep learning combines feature extraction and classification to automatically isolate faults. In this paper, a method based on multi-channel one-dimensional convolutional neural network(1D-CNN) for fault diagnosis of hydraulic loading system is proposed. First, the four sequential sensor signals are preprocessed to form the input of the multi-channel 1D-CNN. Then, Multi-channel CNN extracts complex features from sensor signals and fuses features deeply. Finally, fully connected layer uses extracted features for fault classification. This paper uses indicators such as precision rate, recall rate and confusion matrix to analyze the effect of fault diagnosis. Compared with the multi-layer perceptron-based fault diagnosis method, the multi-channel 1D-CNN has higher accuracy and solves the problem of misjudging the health state as a fault. Experiments show that the method based on multi-channel 1D-CNN can effectively and accurately identify faults of the hydraulic loading system of altitude simulation test platform (HLS-ASTF). © 2022 IEEE.

关键词： Failure analysis

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μ-Synthesis control with reference model for aeropropulsion system test facility under dynamic coupling and uncertainty

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Chinese Journal of Aeronautics 2023年第10期36卷 246-261页

作者： Jiashuai LIU Xi WANG Xi LIU Meiyin ZHU Xitong PEI Song ZHANG Zhihong DAN School of Energy and Power Engineering Beihang UniversityBeijing 100191China Zhongfa Aviation Institute Beihang UniversityHangzhou 311115China Research Institute of Aero-Engine Beihang UniversityBeijing 100191China Science and Technology on Altitude Simulation Laboratory AECC(Aero Engine Corporation of China)Sichuan Gas Turbine EstablishmentMianyang 621703China

Due to the dynamic coupling and multi-source uncertainties,it is difficult to accurately control the pressure and temperature of the Aeropropulsion System Test Facility(ASTF)in the presence of rapid command and large *** paper presents the design ofμ-synthesis control to solve the *** incorporating the pressure ratio into the linear equation of the control valve,the modeling error of ASTF in the low frequency range is effectively ***,an uncertain model is established by considering various factors,including parameter variations,modeling error in the low frequency range,unmodeled dynamics,and changes in the working *** address the dynamic coupling,a diagonal reference model with desired performance is incorporated intoμ-***,all weighting functions are designed according to the performance ***,theμ-controller is obtained by using the standardμ-synthesis *** results indicate that theμ-controller decouples the pressure and temperature dynamics of *** with the multivariable PI controller,integral-μcontroller,and double integral-μcontroller,the proposedμ-controller can achieve higher transient accuracy and better disturbance ***,the robustness of theμ-controller is demonstrated by Monte Carlo simulations.

关键词： Aeropropulsion System Test Facility(ASTF) Decoupling Robustness μ-Synthesis Uncertainty

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Extended State Observer based Attitude Control of a Bird-like Flapping-wing Flying Robot

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Journal of Bionic Engineering 2020年第4期17卷 708-717页

作者： Keqiang Bai YunZhi Luo Zhihong Dan Song Zhang Meiling Wang Qiumeng Qian Jun Zhong School of Information Engineering Southwest University of Science and TechnologyRobot Technology Used for Special Environment Key Laboratory of Sichuan ProvinceMianyang 621010China Automation Research Institute Co. Ltd.of China South Industries Group CorporationMianyang 621000China Science and Technology on Altitude Simulation Laboratory AECC Sichuan Gas Turbine EstablishmentMianyang 621703China AECC Sichuan Gas Turbine Establishment Mianyang 621703China Chinese Academy of Sciences Hefei Institutes of Physical Science Hefei 230022China College of Mechanical and Electrical Engineering Hohai UniversityChangzhou 213022China

The attitude control system of a flapping-wing flying robot plays an important role in the precise orientation and tracking of the *** this paper,the modeling of a bird-like micro flapping-wing system is introduced,and the design of a sliding mode controller based on an Extended State Observer(ESO)is *** main design difficulties are the control law and the adaptive law for the attitude control *** address this problem,a sliding mode adaptive extended state observer algorithm is ***,a new extended state approximation method is used to estimate the final output as a disturbance ***,a sliding mode observer with good robustness to the model approximation error and external disturbance is used to estimate the system *** with traditional algorithms,this method is not only suitable for more general cases,but also effectively reduces the influence of the approximation error and ***,the simulation and experiment example is given to illustrate the implementation *** results show that the algorithm can effectively estimate the state of the attitude control system of the flapping-wing flying robot,and further guarantee the robustness of the model regarding error and external disturbance.

关键词： bionic attitude control flapping-wing flying robot sliding mode adaptive control extended state observer

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Neural Machine Translation by Fusing Key Information of Text

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Computers, Materials & Continua 2023年第2期74卷 2803-2815页

作者： Shijie Hu Xiaoyu Li Jiayu Bai Hang Lei Weizhong Qian Sunqiang Hu Cong Zhang Akpatsa Samuel Kofi Qian Qiu Yong Zhou Shan Yang School of Information and Software Engineering University of Electronic Science and Technology of ChinaChengdu610054China Science and Technology on Altitude Simulation Laboratory Sichuan Gas Turbine Establishment Aero Engine Corporation of ChinaMianyang621000China School of Power and Energy Northwestern Polytechnical UniversityXi’an710072China School of Computer Science Southwest Petroleum UniversityChengdu610500China Department of Chemistry Physics and Atmospheric SciencesJackson State UniversityJacksonMS 39217USA

When the Transformer proposed by Google in 2017,it was first used for machine translation tasks and achieved the state of the art at that *** the current neural machine translation model can generate high quality translation results,there are still mistranslations and omissions in the translation of key information of long *** the other hand,the most important part in traditional translation tasks is the translation of key *** the translation results,as long as the key information is translated accurately and completely,even if other parts of the results are translated incorrect,the final translation results’quality can still be *** order to solve the problem of mistranslation and missed translation effectively,and improve the accuracy and completeness of long sentence translation in machine translation,this paper proposes a key information fused neural machine translation model based on *** model proposed in this paper extracts the keywords of the source language text separately as the input of the *** the same encoding as the source language text,it is fused with the output of the source language text encoded by the encoder,then the key information is processed and input into the *** incorporating keyword information from the source language sentence,the model’s performance in the task of translating long sentences is very *** order to verify the effectiveness of the method of fusion of key information proposed in this paper,a series of experiments were carried out on the verification *** experimental results show that the Bilingual Evaluation Understudy(BLEU)score of the model proposed in this paper on theWorkshop on Machine Translation(WMT)2017 test dataset is higher than the BLEU score of Transformer proposed by Google on the WMT2017 test *** experimental results show the advantages of the model proposed in this paper.

关键词： Key information transformer fusion neural machine translation

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CFD OPTIMUM DESIGN OF SUPERSONIC EJECTOR SYSTEM STRUCTURE OF TEST CELL 32

CFD OPTIMUM DESIGN OF SUPERSONIC EJECTOR SYSTEM STRUCTURE OF...

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32nd Congress of the International Council of the Aeronautical sciences, ICAS 2021

作者： Su, Jinyou Tang, Zhili Tian, Jinhu Pan, Biao Luo, Shaojun Key Laboratory of Unsteady Aerodynamics and Flow Control Ministry of Industry and Information Technology Nanjing University of Aeronautics and Astronautics Nanjing210016 China Science and Technology on Altitude Simulation Laboratory Sichuan Gas Turbine Establishment Aero Engine Corporation of China Sichuan Mianyang621000 China

ISBN: (纸本)9783932182914

In order to study the test requirements of vectoring nozzle aeroengine in high altitude simulation test bed, and the matching between the vectoring nozzle and the exhaust ejector of the test bed in the supersonic working state. Numerical simulation method is used to determine the straight section inner diameter, length diameter ratio and injection ratio of the exhaust ejector of the test bench, and the relative position of the vectoring nozzle and the exhaust ejector, and the aerodynamic structure of the ejector of the test bench under the condition of vectoring nozzle test. Using the typical working points of vectoring nozzle to check the applicability of the ejector aerodynamic structure, The results show that the aerodynamic structure of the ejector meets the test requirements of the vectoring nozzle. © 2021 32nd Congress of the International Council of the Aeronautical sciences, ICAS 2021. All rights reserved.

关键词： Computational fluid dynamics

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