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International Conference on Guidance, Navigation and control, ICGNC 2022

作者： Feng, Tao Liu, Yishi Li, Qingdong Ren, Zhang Duchengweiye Group Co. Ltd. Beijing100010 China School of Automation Science and Electrical Engineering Science and Technology on Aircraft Control Laboratory Beihang University Beijing100191 China

ISBN: (纸本)9789811966125

This paper combines the artificial intelligence algorithm with the modeling and simulation for variable pitch systems of wind turbine, and proposes a fault prediction using the artificial neural network technique of multi-layer perceptron. The operating principle of the variable pitch system is analyzed by building the dynamic model, and the fault detection data of the system is obtained. Then, the artificial neural network of multi-layer perceptron is trained with limited data set. The estimated value of pitch angle can be accurately predicted. The residual error can be obtained by comparing the pitch angle predicted by the artificial neural network and the actual pitch angle output of the system model. The system fault detection results can be obtained according to the fault decision-making index. The proposed method can detect and isolate the fault of complex pitch system accurately with uncertain factors, such as disturbance, and predict the change of fault amplitude effectively. © 2023, The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.

关键词： Wind turbines

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A Joint Longitudinal and Lateral Guidance Scheme for Reentry Gliding Phase of Hypersonic Vehicles

A Joint Longitudinal and Lateral Guidance Scheme for Reentry...

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International Conference on Guidance, Navigation and control, ICGNC 2022

作者： Wang, Ziyu Wu, Yunjie Duan, Jingqi State Key Laboratory of Virtual Reality Technology and System Beihang University Beijing100191 China School of Automation Science and Electrical Engineering Beihang University Beijing100191 China Science and Technology on Aircraft Control Laboratory Beijing100191 China Large Aircraft Advanced Training Center Beihang University Beijing100191 China

ISBN: (纸本)9789811966125

A joint longitudinal and lateral guidance law design scheme is proposed for the reference trajectory tracking problem of the reentry gliding phase of hypersonic vehicles. With respect to the longitudinal and lateral motion model of the hypersonic vehicle, a longitudinal guidance law based on the Global Fast Terminal Sliding Mode (GFTSM) algorithm and a lateral guidance law based on the Extended State Observer (ESO) is designed respectively, which are combined to get the bank angle for the hypersonic vehicle and obtain the final guidance scheme. From theoretical analysis, it shows that the guidance scheme has the characteristics of global rapidity and finite-time convergence, and both longitudinal and lateral guidance law are robust to system uncertainties which are caused by certain parameter perturbation and external interference. The effectiveness and superiority of this joint guidance scheme compared to traditional guidance method are verified by simulation experiments using the specific gliding reentry model and reference trajectory of a hypersonic vehicle. © 2023, The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.

关键词： Hypersonic vehicles

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THE DISPERSION CHARACTERISTICS OF INFECTIOUS DROPLETS IN A CIVIL aircraft CABIN WITH DIFFERENT AIR SUPPLY RATES

THE DISPERSION CHARACTERISTICS OF INFECTIOUS DROPLETS IN A C...

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

作者： Li, Pei Sun, Jianhong Zheng, Daren Xu, Changyue Key Laboratory of Aircraft Environment Control and Life Support MIIT Nanjing University of Aeronautics and Astronautics Nanjing210016 China Key Laboratory of Civil Aviation Emergency Science and Technology CAAC Nanjing University of Aeronautics and Astronautics Nanjing211106 China

This work presents a simulation of infectious droplet dispersion in a civil aircraft cabin with the Euler-Lagrangian method. The influence of different rates of air supply on the airflow field, droplet dispersion, and concentration distribution of infectious droplets are analysed. The results show the rates of air supply have a significant impact on airflow filed. The area of vortex circulation region in the cabin is reduced. Total mass of infectious droplets in the cabin basically reaches stability after the infector exhales the infectious droplets for 120 seconds. The total mass in the civil cabin is 3.56×10-12 kg with the 6.9 L per second per person and respectively decreased by 4.21% and 22.75% with increasing the air supply rate to 10 L per second per person and 16 L per second per person. The concentration of infectious droplets in each passenger's respiratory zone is examined. The infector located at the middle of the cabin or sitting near the aisle could affect more passengers and thus, the infector is recommended to sit by the window during the epidemic. © The Institution of Engineering & technology 2024.

关键词： Vortex flow

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Privacy - Preserving Event - Triggered Predefined Time Containment control for Networked Agent Systems 14

Privacy - Preserving Event - Triggered Predefined Time Conta...

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14th International Conference on Information science and technology, ICIST 2024

作者： Li, Weihao Yue, Jiangfeng Shi, Mengji Lin, Boxian Qin, Kaiyu School of Aeronautics and Astronautics University of Electronic Science and Technology of China Chengdu China Aircraft Swarm Intelligent Sensing and Cooperative Control Key Laboratory of Sichuan Province Chengdu611731 China National Laboratory on Adaptive Optics Chengdu610209 China

ISBN: (纸本)9798350353334

This paper addresses the privacy-preserving event-triggered predefined time containment control problem for net-worked agent systems. A novel containment control scheme is developed that integrates privacy protection with event-triggered mechanisms, optimizing network efficiency b y minimizing un-necessary data transmission while ensuring robust containment within a specified time frame. T he proposed control scheme ensures the confidentiality of agents' information through output masking, thereby maintaining both privacy and control accuracy. Furthermore, it provides a distinct advantage over traditional finite-time and fi xed-time co ntrol me thods by gu aranteeing con-vergence to the desired state within a predefined time, regardless of initial conditions. Finally, some simulation results are given to verify the effectiveness of the proposed containment control scheme. © 2024 IEEE.

关键词： Differential privacy

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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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A Fault-Tolerant control Scheme for Civil aircraft Based on Prescribed Performance control

A Fault-Tolerant Control Scheme for Civil Aircraft Based on ...

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International Conference on Guidance, Navigation and control, ICGNC 2022

作者： Duan, Jingqi Wu, Yunjie Wang, Ziyu State Key Laboratory of Virtual Reality Technology and System Beihang University Beijing100191 China School of Automation Science and Electrical Engineering Beihang University Beijing100191 China Science and Technology on Aircraft Control Laboratory Beijing100191 China Large Aircraft Advanced Training Center Beihang University Beijing100191 China

ISBN: (纸本)9789811966125

In this paper, a fault-tolerant control scheme based on prescribed performance control is proposed to solve the pitch angle attitude control problem of large civil aircraft when actuator faults and external disturbances exist simultaneously. Firstly, the longitudinal motion model of civil aircraft with actuator fault is established. Among them, actuator faults and external disturbances are regarded as lumped disturbances. Then, a performance envelope is constructed based on the hyperbolic cosecant function which can adjust the transient convergence rate and the steady convergence rate respectively. In order to achieve fast online estimation of lumped disturbances, an RBF neural network observer is constructed. The introduction of tracking differentiator solves the problems of initial state constraint of prescribed performance control and "differential-explosion" in back-stepping control. After proving the stability of the system from the perspective of theoretical analysis, the simulation of pitch angle control under the condition of abrupt actuator faults and external disturbance is completed based on Boeing 747 longitudinal motion model. © 2023, The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.

关键词： Attitude control

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RESEARCH OF THE CHARACTERISTICS OF THE ACTIVE LOAD-SENSITIVE DRIVE SYSTEM

RESEARCH OF THE CHARACTERISTICS OF THE ACTIVE LOAD-SENSITIVE...

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

作者： Mou, Quanrun Liu, Xiaochao Wang, Zhenyu Qiu, Zhongyi Li, Juefei Jiao, Zongxia School of Aeronautic Science and Engineering Beihang University Beijing China School of Automation Science and Electrical Engineering Beihang University Beijing China Ningbo Institute of Technology Beihang University Ningbo China Science and Technology on Aircraft Control Laboratory Beihang University Beijing China Tianmushan Laboratory Xixi Octagon City Yuhang District Hangzhou310023 China

In this paper, an active load-sensitive valve-controlled variable displacement motor drive system is introduced, aiming at solving the problem of large energy waste in valve-controlled fixed-displacement system. The fixed-displacement system is unable to match the variable load conditions promptly due to the fixed displacement, resulting in serious throttling losses under small load conditions. This study analyses the energy consumption characteristics by establishing a mathematical model of the active load-sensitive drive system. In addition, the nonlinear mapping of displacement and load pressure difference is designed, and simulation verification of comparing active load-sensitive drive system with the valve-controlled fixed-displacement motor drive system is completed. By analysing the simulation results, it can be seen that the active load-sensitive drive system can reduce the average flow rate by 68% and the peak flow rate by nearly 66% under the small load condition, which effectively solves the problem of heavy throttling loss in the valve-controlled hydraulic system. © The Institution of Engineering & technology 2024.

关键词： Energy utilization

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A Review of aircraft Ground Taxi control Techniques

A Review of Aircraft Ground Taxi Control Techniques

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

作者： Li, Bingyu Liu, Xiaochao School of Automation Science and Electrical Engineering Beihang University Beijing100191 China National Key Laboratory of Aircraft Integrated Flight Control Beihang University Beijing100191 China Key Laboratory of Advanced Aircraft Systems Beihang University Ministry of Industry and Information Technology Beijing100191 China Ningbo Institute of Technology Beihang University Ningbo315800 China Tianmushan Laboratory Hangzhou310023 China

The extensive utilization of aircraft as a mode of transportation and the accelerated expansion of the aviation market have imposed heightened expectations on airport scheduling capabilities. To enhance the efficacy of aircraft ground operations and diminish the duration of runway occupation, the analysis of aircraft motion characteristics and the management of their ground taxiing trajectories assume greater significance. This paper provides an overview of aircraft ground taxiing control technology. This paper provides a brief overview of the key parameters and trajectory prediction methods involved in the aircraft landing process. The nonlinear analysis theory is employed to introduce the aircraft brake system stability and heading stability. Subsequently, the results of significant research on ground skidding control laws are presented. The fourth section presents a summary of the issues and technological developments in aircraft ground skid run control and outlines future research priorities in anti-skid brake control. © The Institution of Engineering & technology 2024.

关键词： aircraft GROUND TAXI NONLINEAR control STABILITY ANALYSIS TRAJECTORY PREDICTION

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Multi-parameter load sensing pump model simulation and flow rate characteristics research

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Chinese Journal of Aeronautics 2022年第12期35卷 296-308页

作者： ZongXia JIAO Zhenyu WANG Xiaochao LIU HuJiang WANG Pengyuan QI Weizhi QIAO School of Automation Science and Electrical Engineering Beihang UniversityBeijing 100083China State Key Laboratory of Fluid Power and Mechatronic Systems Zhejiang UniversityHangzhou 310027China Research Institute for Frontier Science Beihang UniversityBeijing100083China Science and Technology on Aircraft Control Laboratory Beihang UniversityBeijing 100083China Science and Technology on Vehicle Transmission Laboratory China North Vehicle Research InstituteBeijing 100072China Ningbo Institute of Technology Beihang UniversityNingbo 315800China

Load sensing pumps have been widely used in diverse hydraulic *** show that structural parameters have undeniable impacts on the characteristics and efficiency of the load sensing *** main purpose of this article is to study the influence of load sensing pump structure parameters on flow *** the present study,a nonlinear multi-parameter model is proposed for this type of *** this model,different parameters,including spool clearance,spool covering amount,internal leakage are considered to reflect the displacement adjustment process of the load sensing ***,a frequency sweep method is proposed to analyze the frequency domain of the nonlinear mathematical *** experiment rig was built to study the influence of key structural parameters on the dynamic follow-up characteristics of the pump *** obtained results show that the diameter of the orifice d can significantly affect the working characteristics of the *** is found that a large diameter of the orifice d can improve the phase following ability of the system,while a small diameter of the orifice d can reduce the bypass flow rate and increase the amplitude following *** paper provides a new consideration to study the dynamic follow-up characteristics of the load sensing pump.

关键词： Flow rate characteristics Frequency analysis Hydraulic Load sensing pump Nonlinear

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THE PARAMETER SENSITIVITY ANALYSIS ON THE DYNAMIC STIFFNESS OF THE ELECTRO-HYDROSTATIC ACTUATOR

THE PARAMETER SENSITIVITY ANALYSIS ON THE DYNAMIC STIFFNESS ...

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

作者： Renlei, Wei Shuai, Wu Bing, Chu Yuliang, Yang Jianing, Luo School of Automation Science and Electrical Engineering Beihang University Beijing100191 China National Key Laboratory of Aircraft Integrated Flight Control Beihang University Beijing100191 China Key Laboratory of Advanced Aircraft Systems Beihang University Ministry of Industry and Information Technology Beijing100191 China Ningbo Institute of Technology Beihang University Ningbo315800 China Tianmushan Laboratory Hangzhou310023 China AVIC Shenyang Aircraft Design and Research Institute Shenyang110035 China

The electro-hydrostatic actuator (EHA) has the advantage of high power weight ratio, less leakage and the absence of throttle loss. It's used on the multi-electric aircraft and the all-electric aircraft. However, it will be affected by the aerodynamic load and the rudder flutter will occur if the dynamic stiffness of the EHA is low. As a result, it's significant to analyse the sensitivity of the EHA's parameters on the dynamic stiffness. The article builds a linear model of the EHA considering the leakage in the system. What's more, the local parameter sensitivity for the dynamic stiffness is calculated when the frequency is between 0.01 Hz and 1000 Hz. © The Institution of Engineering & technology 2024.

关键词： Sensitivity analysis

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