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Adaptive Dead Zone Compensation Control Method for Electro-Hydrostatic Actuators Under Low-Speed Conditions

Chinese Journal of Mechanical Engineering 2024年第6期37卷 199-211页

作者： Haoyi Jiang Zhenfei Ling Fengqi Zhou Maowen Sun Hao Liu Lilin Xu Yeming Yao Xiaoping Ouyang Huayong Yang State Key Laboratory of Fluid Power and Mechatronic Systems Zhejiang UniversityHangzhou 310027China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing Engineering Institute of Aircraft SystemNanjing 210000China

This study proposes an accurate dead zone compensation control method for electro-hydrostatic actuators(EHAs)under low-speed ***,the nonlinear dead zone characteristics under low-speed conditions are summarized based on numerous EHA *** adaptive compensation function(ACF)is then constructed for the dead ***,this study proposes an adaptive dead zone compensation control method for EHAs by integrating the ACF with a virtual decomposition controller(VDC)based on the established EHA *** stability of the proposed control method is also ***,the proposed control method is verified using an EHA *** test results show that the dead zone trajectory tracking errors of EHAs are significantly reduced when combined with the ***,since most EHAs are controlled by adjusting the motor speed,the method presented in this study is simpler and easier to use than methods that employ flow compensation.

关键词： Electro-hydrostatic actuator Dead zone Compensation Control Low-speed

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Measurement of aerodynamic heating of micro-scale rotational shearing flow and its heat flux identification

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Chinese Journal of Aeronautics 2025年第4期38卷 70-90页

作者： Yuan LIU Yuanwei LYU Jingyang ZHANG Chunyang LI Jingzhou ZHANG Zhongwen HUANG College of Astronautics Nanjing University of Aeronautics and AstronauticsNanjing 210016China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Beijing 120016China College of Energy and Power Engineering Nanjing University of Aeronautics and AstronauticsNanjing 210016China Key Laboratory of Thermal Management and Energy Utilization of Aircraft Nanjing 210016China

This study conducted the experimental investigation of aerodynamic heating of Micro-scale Rotational Shearing Flow with Axial Limited-Length(MRSFALL).The temperature riseof the stator is captured by the high response *** eccentricity ratio and clearanceheight are guaranteed by means of instantaneous trajectory and torsion monitoring of the *** result shows that the maximum temperature rise takes place upstream of the minimum clear-ance height along circumferential *** distribution of temperature rise presents asymmet-ric curve along axial direction,and peak value occurs near the dimensionless axial position *** effect of aerodynamic heating becomes notable as the rotational speed is larger than3×10^(4)r/*** effect of end leakage and the viscous dissipation have great impact on temper-ature rise of *** specially,the peak value of temperature rise at dimensionless clear-ance height of 0.0080 is larger than the case at dimensionless clearance height of ***,when the eccentricity ratio is too large,the viscous dissipation is induced,and theadditional temperature rise is *** heat flux identification of shear flow has been realizedby Sequential Function Specification Method(SFSM)and its estimation of thermal load has been *** heat flux induced by the aerodynamic heating in this study varies from 950 W/m^(2)to1330 W/m^(2).

关键词： Micro-scale Rotational Shearing Flow with Axial Limited-Length(MRSFALL) Hyper-rotate-speed End leakage Aerodynamic heating experimental measurement Heat flux identification

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Distributed Optimal Formation Control of Multiple Unmanned Surface Vehicles With Stackelberg Differential Graphical Game

IEEE Transactions on Artificial Intelligence

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IEEE Transactions on Artificial Intelligence 2024年第8期5卷 4058-4073页

作者： Yu, Kunting Li, Yongming Lv, Maolong Tong, Shaocheng Liaoning University of Technology College of Science Liaoning Jinzhou121001 China Dalian Maritime University Navigation College Liaoning Dalian116026 China Air Force Engineering University National Key Laboratory of Unmanned Aerial Vehicle Technology National Key Laboratory of Aerospace Power System and Plasma Technology College of Air Traffic Control and Navigation Shanxi Xi'an710051 China

In this work, a cooperative formation control methodology is proposed for multiple six-degree-of-freedom (six-DoF) unmanned surface vehicles (USVs) subject to input saturation. Our method includes several key steps. To begin, we formulate the optimal formation control problem for USVs as Stackelberg differential graphical games. According to this design principle, each USV is partitioned into a primary follower and a secondary follower. The primary followers coalesce into one team, while the secondary followers constitute another team independently. Second, a new type of barrier Lyapunov function (BLF) with a hyperbolic tangent function is introduced to indirectly constrain velocity vector. Third, an auxiliary system is established to compensate for the input saturation. Then, the Lyapunov stability theory is employed to prove that all closed-loop signals of multiple USVs are semiglobal uniform ultimate boundedness (SGUUB). Finally, we present the simulation results of our proposed control scheme. These results demonstrate the effectiveness and feasibility of our proposed methodology for cooperative formation control of multiple USVs. © 2020 IEEE.

关键词： Reinforcement learning

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Modeling and validation of key components of thermal management systems

Modeling and validation of key components of thermal managem...

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

作者： Zekun, Mei Shuai, Xu Fanxin, Meng Guangya, Zhu Dalin, Zhang Weijian, Chen Key Laboratory of Aircraft Environment Control and Life Support MIIT Nanjing University of Aeronautics and Astronautics Nanjing China 805th Research Institute of China Aerospace Science and Technology Corporation Shanghai China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration No.33 Shuige Road Nanjing China

ISBN: (数字)9781837242108

In this paper, two key components of thermal management system are modeled by the underlying logic operation of SIMULINK. Simulink-PS signal conversion module is used to connect the electric grid and the calculation part of the heat grid to build the fuel tank heat grid model. The temperature transient simulation model of phase-change heat exchanger was established by using the integral module in Simulink library. Experimental verification and literature data verification are provided for these two components. The results show that the error between simulation results and experimental data is between 0.1% and 3%, which proves the accuracy and feasibility of the system modeling in this paper. It lays a foundation for the simulation of the overall thermal management scheme. © The Institution of Engineering & technology 2024.

关键词： Fuel tanks

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Research on Calculation Method of Drag Chute Opening Performance Based on Rocket Sled Platform 7th

Research on Calculation Method of Drag Chute Opening Perform...

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7th China Aeronautical science and technology Conference, CASTC 2024

作者： Jin, Lou Cui, Dongyue Yang, Pin Yu, Yuanyuan Aviation Key Laboratory of Science and Technology on Life-Support Technology Xianyang China Overall Technology R&D Department AVIC Aerospace Life-Support Industries Ltd. Xianyang China Institute of Mechanical and Electrical System AVIC The First Aircraft Institute Xi’an China

ISBN: (纸本)9789819797738

This paper proposes a calculation method based on the rocket sled test method to quickly verify the performance of the main drag chute of aircraft. According to the working principle and folding process of the drag chute, combined with the pre-processing folding and calculation folding methods, the simulation folding process of the finite element model of the drag chute is designed, the finite element model of the rocket sled system was established. Then, the S-ALE fluid structure coupling algorithm was used to simulate and calculate the performance parameters of the rocket sled drag parachute system during the parachute deployment process, forming a simulation verification process for the parachute deployment performance of the drag chute. The calculation results show that the force on the rope of the drag chute during the operation process of the rocket sled drag parachute system shows a consistent trend over time, and the error generated by calculating the opening performance parameters of the rocket sled drag parachute system using the method proposed in this article are within 12%, which can meet the requirements of engineering use. The calculation method proposed in this article can to some extent replace the rocket sled test to verify the performance of the parachute. The calculation method proposed can quickly predict the performance of the drag chute instead of physical tests at the initial stage of development. © Chinese Society of Aeronautics and Astronautics 2025.

关键词： Parachutes

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Quantitative Analysis of Flow Resistance in the Ventilation Pipeline of Ejection Seats and Optimization Design of Flow Resistance Reduction 7th

Quantitative Analysis of Flow Resistance in the Ventilation ...

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7th China Aeronautical science and technology Conference, CASTC 2024

作者： Jin, Lou Wu, Jing Chen, Yuxiang Cui, Dongyue Aviation Key Laboratory of Science and Technology on Life-Support Technology Xianyang China Overall Technology R&D Department AVIC Aerospace Life-Support Industries Ltd. Xianyang China Institute of Mechanical and Electrical System AVIC The First Aircraft Institute Xi’an China

ISBN: (纸本)9789819797707

During normal flight, the ejection seat ventilation system provides a dedicated gas transmission channel for electronic oxygen and anti load regulators. The flow resistance of the pipeline directly affects the ventilation and supply performance of the regulator and the anti load protection ability during mobile operations. This article adopts a combination of numerical simulation and experimental testing methods to quantitatively analyze the flow resistance of a certain type of ejection seat ventilation pipeline. Based on the principle of gas supply performance testing and numerical simulation methods, a research process is designed. The simulation accuracy of different simulation models under different ventilation flow rates is analyzed, and the ventilation pipeline is optimized based on the calculation formula of pipeline flow resistance theory and the analysis results of pipeline flow field. The research results indicate that among multiple turbulence models, the Realizable k-e model has the best accuracy in simulating pipeline flow resistance, with a maximum error of 14.2% and a minimum error of 1.3% under different flow conditions, both below 15%, meeting the requirements for engineering use;the vortices generated at the corners and variable diameter areas of the ventilation pipeline can lead to energy dissipation. Optimizing the transition corners and pipeline diameter of the bend can reduce the generation of vortices and reduce the system flow resistance to 17.9% of the original value;under the premise of constant pipeline flow rate, the flow resistance of ventilation pipelines is inversely proportional to the fifth power of pipeline diameter. When optimizing pipeline flow resistance design, emphasis should be placed on optimizing from the pipeline diameter. © Chinese Society of Aeronautics and Astronautics 2025.

关键词： Ejection seats

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A Method for Reconstructing The Shape of Wing Panels Based on Fiber Optic Sensors and Tomographic Imaging Principles 15

A Method for Reconstructing The Shape of Wing Panels Based o...

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15th IEEE Global Reliability and Prognostics and Health Management Conference, PHM-Beijing 2024

作者： Zhan, Jun Zeng, Jie Xiang, Chao Cui, Jinpeng Zeng, Cheng Zhu, Linfeng Lu, Mingyu State Key Laboratory of Mechanics and Control for Aerospace Structures Nanjing University of Aeronautics and Astronautics No. 29 Yudao Street Nanjing210016 China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing Engineering Institute of Aircraft System Jincheng AVIC Nanjing China COMAC Beijing Aircraft Technology Research Institute Changping District Xiaotangshan Future Science and Technology City Beijing102211 China

ISBN: (纸本)9798350354010

The aircraft wing structure shape reconstruction method based on discrete strain information not only provides data support for the digital collaborative health monitoring and prediction technology of wing structure but also helps to improve the aerodynamic shape and flight quality of the aircraft, achieve structural stealth, and enhance the pointing accuracy of the on-board conformal antenna. As result, a wing skin panel shape reconstruction method based on the principle of tomographic imaging and strain information perception is proposed. According to the idea of tomographic imaging, a "non-intrusive" layout form that only requires sensors to be arranged on the periphery of the monitoring area is designed, breaking through the limitation that sensors can not be arranged in the monitoring area under special working conditions. A method for constructing the deflection shape function of the wing skin panel based on the concept of synthetic curvature is proposed, solving the problem of error accumulation and elimination of deformation inversion at non-monitoring points of the measured structure caused by the uncertainty of the limited discrete layout of sensors and the choice of interpolation fitting method. On this basis, a model deformation monitoring and inversion system for wing skin panel based on fiber optic grating sensors is constructed. The experimental results show that under the single-end fixed bending and torsion working condition, the average relative error of the panel model shape reconstruction is 4.17%. Under the double-end fixed double-concentrated load working condition, the average relative error of the shape reconstruction is 8.07%. The wing deformation distribution information reconstructed by the method proposed in this paper can be mapped onto the virtual twin model of the wing, providing technical support for the safety assessment, early warning, and on-condition maintenance of the entire service life of key structures of the aircraft. © 2024

关键词： Fixed wings

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Efects of Defect,Mean Stress and Lower Loading on High Cycle and Very High Cycle Fatigue Behavior of Ti‑6Al‑4V Alloy

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Acta Metallurgica Sinica(English Letters) 2025年第3期38卷 435-448页

作者： Yiyun Guo Lei Wu Yibo Shang Chengqi Sun State Key Laboratory of Nonlinear Mechanics Institute of MechanicsChinese Academy of SciencesBeijing 100190China School of Engineering Science University of Chinese Academy of SciencesBeijing 100049China Guobiao(Beijing)Testing&Certifcation Co. Ltd.Beijing 101400China Fundamentals Department Air Force Engineering UniversityXi’an 710051China National Key Lab of Aerospace Power System and Plasma Technology Air Force Engineering UniversityXi’an 710038China

In this study,the efects of defect,mean stress and lower loading are investigated for high cycle(HCF)and very high cycle fatigue(VHCF)behavior of Ti-6Al-4V *** indicates that the S-N curve of Ti-6Al-4V alloy exhibits a linear decreasing trend or a plateau characteristic in HCF and VHCF regimes,which depends on the defect size and stress *** strength decreases with increasing the defect size,and it is irrespective of stress *** fatigue crack initiates from specimen surface at R=−1 in both HCF and VHCF *** the fatigue crack initiates from the subsurface or the interior of the specimen at R=0.1 in VHCF regime.A sequence of lower stress amplitude below the fatigue strength at 10^(9) cyc has no or negligible infuence on the fatigue life of 10^(5)-10^(9) *** lower stress amplitude in variable amplitude loadings does not afect the failure *** residual compressive stress relaxation is not observed after a large number of lower loadings under ultrasonic frequency fatigue *** formula and Goodman formula give dangerous predictions of VHCF strength for both smooth specimens and specimens with defects.

关键词： Ti-6Al-4V titanium alloy Very high cycle fatigue Defect Stress ratio Lower stress amplitude

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A Decentralized SoC Balancing Technique for Precharging Series Energy Storage systems 48

A Decentralized SoC Balancing Technique for Precharging Seri...

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48th Annual Conference of the IEEE Industrial Electronics Society, IECON 2022

作者： Li, Yao Wu, Donghua Qi, Yang Li, Weilin Northwestern Polytechnical University School of Automation Xi'an China Shaanxi Aero Electric Co. Ltd Aviation Key Laboratory of Science and Technology on Aerospace Power System Xi'an China

ISBN: (数字)9781665480253

ISBN: (纸本)9781665480253

Energy storage systems (ESSs) are widely installed in the present power system. When multiple ESSs are connected in series, proper power sharing is needed to avoid the unbalance SoC issue: some ESSs are not fully charged while others have been overcharged. Due to geographical restriction, there is usually no communication link between different ESSs. In this case, each ESS only knows its local information, such as the state of charge (SoC), output current, and voltage. It is therefore more challenging to achieve the ESS SoC balancing during the pre-charging state. To address this issue, a decentralized SoC balancing control based on complex virtual impedance has been proposed in this paper. The proposed method controls the ESS as a virtual complex impedance, whose impedance angle is correlated with the real-time SoC value. Through this effort, the active power of ESS can be dynamically regulated during the entire pre-charging process to autonomously realize SoC balancing. Finally, hardware-in-loop (HIL) simulation results of a series ESS system are provided for verification. © 2022 IEEE.

关键词： Energy storage

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Optimization of the Structural Parameter in Line-start Permanent Magnet Synchronous Machine for Traction Applications 26

Optimization of the Structural Parameter in Line-start Perma...

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26th International Conference on Electrical Machines and systems, ICEMS 2023

作者： Zou, Hui Hu, Yaohua Zhu, Shushu Avic Aerospace System CO. Ltd General Management Department Beijing China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing Engineering Institute of Aircraft Systems Nanjing China Nanjing University of Aeronautics and Astronautics Center for More-electric-aircraft Power System Nanjing China

ISBN: (纸本)9798350317589

This paper studied the permanent magnet arrangement methods for a 30 kVA line-start permanent magnet synchronous machine for traction applications. By comparing the magnetic flux distribution, no-load starting characteristics, and starting torque of the three structures, the V-shaped structure has the most advantages when all parameters are integrated. At the same time, the selected V-shaped rotor was optimized, such as rotor slot width, slot depth, permanent magnet structure and size. The optimal rotor slot and permanent magnet structure were compared, and the performance of the final machine was analyzed. The simulation results indicate that the machine designed in this paper has the advantages of low starting current and high efficiency. © 2023 IEEE.

关键词： Permanent magnets

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