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34th Congress of the International Council of the Aeronautical sciences, ICAS 2024

作者： Jiang, Chaofan Shang, Yaoxing Yu, Tian Liu, Zhicheng Li, Mingyang School of Automation Science and Electrical Engineering Beihang University Beijing China National Key Laboratory of Aircraft Integrated Flight Control Beihang University Beijing China Ningbo Institute of Technology Beihang University Ningbo China Tianmushan Laboratory Yuhang District Xixi Octagon City Hangzhou China

Electro-hydrostatic Actuator (EHA) is an important part which is used to control the control surface of aircraft. EHA has the advantage of higher efficiency compared with traditional hydraulic system. Compared with the hydraulic actuator, EHA adds motor, hydraulic pump, booster tank and other components. Therefore, the calculation of EHA efficiency is also more complex than that of hydraulic actuators. After research and analysis, the efficiency of wet motor-pump is low under large load or high speed. Using a passive load-sensitive EHA configuration can improve this situation. The motor copper loss can be reduced by reducing the displacement of piston pump under large load. But the displacement cannot be reduced blindly, which will lead to dynamic decline. The influence of displacement change velocity on dynamic and energy loss was studied. The effects of load sensitive variable displacement mechanism parameters such as piston area, spring stiffness, radius of damping hole and initial pressure on the velocity of displacement change were studied. The influence of parameters on dynamics and energy loss is obtained. So in order to balance efficiency and dynamics, particle swarm optimization method is adopted. Piston area, spring stiffness, radius of damping hole and initial pressure of variable displacement are taken as optimization variables. Energy loss and step response risetime are taken as optimization objectives. The energy loss and risetime are kept at a low level by obtaining appropriate load sensing mechanism parameters. The results show that the passive load sensing mechanism parameters obtained by particle swarm optimization algorithm can reduce the energy consumption of EHA under large load conditions and improve the efficiency of EHA without reducing the dynamic of EHA. © 2024, International Council of the Aeronautical sciences. All rights reserved.

关键词： aircraft hydraulic systems

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Data-driven-based Bipartite Tracking Consensus control for Networked Agent Systems via Adaptive Policy Iteration

Data-driven-based Bipartite Tracking Consensus Control for N...

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2024 China Automation Congress, CAC 2024

作者： Zhai, Peiyu Wang, Mingbo Lin, Boxian Li, Weihao Yue, Jiangfeng Shi, Mengji 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 Chengdu China National Laboratory on Adaptive Optics Chengdu610209 China AVIC Computing Technique Research Institute Xi’an China

ISBN: (纸本)9798350368604

In this paper, the optimal bipartite tracking consensus control problem of networked agent systems is addressed. Theoretically, a data-driven control scheme based on adaptive policy iteration (API) is designed to enable all followers in a cooperative-competitive network to achieve bipartite tracking for the leader. Firstly, the Hamilton-Jacobi-Bellman (HJB) equation of this optimal tracking consensus control problem is obtained based on the Bellman optimality principle. Secondly, an API algorithm with the adaptive escape mechanism is designed to achieve the solution of the HJB equation while reducing the iteration resource consumption. Then, the optimal value function and optimal control input are solved online based on neural networks. Finally, a simulation example is given to verify the effectiveness of the proposed data-driven-based bipartite tracking consensus control scheme. © 2024 IEEE.

关键词： Networked control systems

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The future and technique challenges of high-speed ground effect vehicle enrolled in maritime transportation

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Aerospace Traffic and Safety 2024年第1期1卷 43-54页

作者： Jianhong Sun Chenlu Wang Daren Zheng Zhi Sun Hao Liu Zhuoran Sheng Shengrun Zhang Weidong Zhao Key Laboratory of Aircraft Environment Control and Life Support MIITNanjing 210016China Key Laboratory of Civil Aviation Emergency Science&Technology CAACNanjing 211106China

This paper presents a high-speed ground effect vehicle(HS-GEV)used specifically for maritime *** the limitations of current vessels,including various types of watercraft and high-speed boats,in fulfilling of needs in different maritime transportation scenarios,the HS-GEV emerges as a promising solution to address unmet *** efficiently accomplish maritime transportation missions with quickness and safety,several critical features are emphasized,including short take-off on water,flight maneuverability and flight *** key techniques required to achieve these features,as well as recent progress highlights,are *** and promoting these crucial techniques is also suggested as a future step to improve HS-GEV *** its predominant features,the HS-GEV holds immense application value in enhancing a high-speed maritime transportation system that aligns with the evolving needs of the real world.

关键词： HS-GEV Maritime Transportation Drag Reduction Combined Power Wing-in-Ground(WIG)Effect Ground Effect Vehicle(GEV)

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Multi-target Tracking with Random Finite Set in Decentralized Large-scale Sensor Networks

Multi-target Tracking with Random Finite Set in Decentralize...

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2022 IEEE International Conference on Unmanned Systems, ICUS 2022

作者： Su, Lingfei Dong, Xiwang Hua, Yongzhao Yu, Jianglong Ren, Zhang School of Automation Science and Electrical Engineering Beihang University Science and Technology On Aircraft Control Laboratory Beijing China Institute of Artificial Intelligence Beihang University Beijing China

ISBN: (数字)9781665484565

ISBN: (纸本)9781665484565

This paper presents the multi-target tracking (MTT) problem in decentralized large-scale sensor networks. A novel random finite set (RFS)-based framework is designed, including an improved Probability Hypothesis Density filter with Gaussian Mixture (GM-PHD) representation, and an improved Generalized Covariance Intersection (GCI) fusion algorithm. For the local GM-PHD filter, the intensity of new-born targets is initialized by pre-segmenting the measurement set to address the uncertainty of measurement origin and the computational burden of large-scale measurements. Then, a sensor node-dependent clutter model is established to deal with the cardinality overestimation problem brought by the decentralized structure. For the proposed fusion algorithm, i.e., fusing the posterior PHDs generated by the proposed GM-PHD filters in a distributed manner, it is based on the idea of compensating the severe missed detection problem of GCI in the case of large-scale fusing resources by arithmetic average (AA) fusion. In this way, GCI and AA can be fully utilized to guarantee the estimation accuracy for common targets and, respectively, the robustness for exclusive targets. A simulation of a decentralized large-scale network demonstrates the effectiveness of the proposed framework with respect to estimation accuracy and computational cost. © 2022 IEEE.

关键词： Sensor nodes

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High-dimensional aerodynamic data modeling using a machine learning method based on a convolutional neural network

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Advances in Aerodynamics 2022年第1期4卷 845-875页

作者： Bo-Wen Zan Zhong-Hua Han Chen-Zhou Xu Ming-Qi Liu Wen-Zheng Wang Institute of Aerodynamic and Multidisciplinary Design Optimization National Key Laboratory of Science and Technology On Aerodynamic Design and ResearchSchool of AeronauticsNorthwestern Polytechnical UniversityXi’an710072China Aircraft Swarm Intelligent Sensing and Cooperative Control Key Laboratory of Sichuan Province School of Aeronautics and AstronauticsUniversity of Electronic Science and Technology of ChinaChengdu611731China

Modeling high-dimensional aerodynamic data presents a significant challenge in aero-loads prediction, aerodynamic shape optimization, flight control, and simulation. This article develops a machine learning approach based on a convolutional neural network (CNN) to address this problem. A CNN can implicitly distill features underlying the data. The number of parameters to be trained can be significantly reduced because of its local connectivity and parameter-sharing properties, which is favorable for solving high-dimensional problems in which the training cost can be prohibitive. A hypersonic wing similar to the Sanger aerospace plane carrier wing is employed as the test case to demonstrate the CNN-based modeling method. First, the wing is parameterized by the free-form deformation method, and 109 variables incorporating flight status and aerodynamic shape variables are defined as model input. Second, more than 7000 sample points generated by the Latin hypercube sampling method are evaluated by performing computational fluid dynamics simulations using a Reynolds-averaged Navier-Stokes flow solver to obtain an aerodynamic database, and a CNN model is built based on the observed data. Finally, the well-trained CNN model considering both flight status and shape variables is applied to aerodynamic shape optimization to demonstrate its capability to achieve fast optimization at multiple flight statuses.

关键词： Aerodynamic data modeling High-dimensional problem Machine learning Convolutional neural network Computational fluid dynamics

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Neuroadaptive Bipartite Consensus control for Uncertain Networked Agent Systems Subject to Actuator Attacks

Neuroadaptive Bipartite Consensus Control for Uncertain Netw...

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2024 China Automation Congress, CAC 2024

作者： Kang, Yulin Shi, Mengji Wang, Kexiang You, Long Yue, Jiangfeng Lin, Boxian Qin, Kaiyu School of Aeronautics and Astronautics University of Electronic Science and Technology of China Chengdu611731 China Aircraft Swarm Intelligent Sensing and Cooperative Control Key Laboratory of Sichuan Province Chengdu611731 China National Laboratory on Adaptive Optics Chengdu610209 China Chinese Aeronautical Establishment Beijing100012 China

ISBN: (纸本)9798350368604

Uncertainties, such as modeling inaccuracies, external disturbances, and actuator attacks are widely spread in the control channels of the networked networked agent system, which affect the accuracy and reliability of the cooperative control to a certain extent. With this in mind, this paper focuses on the robust bipartite consensus control problem of uncertain nonlinear networked networked agent systems subject to actuator attacks. In particular, the communication topology among agents is described by a signed graph, which contains not only cooperative interactions but also competitive interactions among agents. Theoretically, the neural network-based robust consensus controller is designed. On the one hand, compound uncertainties, like modeling inaccuracies and external disturbances are approximated by interpolated fitting of Gaussian radial basis functions. The adaptive laws for approximate parameters are generated online based on the stability conditions of the closed-loop error system. On the other hand, the estimation of the unknown actuator attack factor is achieved based on the adaptive control technique, which results in the effective compensation of the attack-induced control attenuation. Finally, the effectiveness of the proposed robust consensus control scheme is validated using some simulation examples. © 2024 IEEE.

关键词： Radial basis function networks

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Effect of center-offset arc pole shoe shapes on torque ripple and eddy-current loss of consequent pole rotor

Effect of center-offset arc pole shoe shapes on torque rippl...

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CSAA/IET International Conference on aircraft Utility Systems (AUS 2024)

作者： Haien Li Liang Yan Xiaoshuai Liu Pengjie Xiang Xinghua He Nannan Du Yang Xuxu School of Automation Science and Electrical Engineering Science and Technology on Aircraft Control Laboratory Beihang University Beijing People's Republic of China

ISBN: (数字)9781837242108

Traditional consequent pole motor has the advantages of less magnetic costs, small magnetic resistance and strong inductance. It is widely studied in the design of the electrical propulsion system. However, it has the problem of uneven distribution of air gap magnetic flux density. It is locally distributed by square waves, causing the high-level harmonic problem, increasing the torque pulse and vortex loss of the motor. This paper show the design principles of the center-offset arc pole. And the limited element simulation of the motor of different eccentric spacing. The results show that compared with the consequent pole, increasing the center-offset distance can reduce the torque ripple and vortex loss.

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Design of Intentional Eye-blink Signal Acquisition and control System Based on Pressure Sensor 7

Design of Intentional Eye-blink Signal Acquisition and Contr...

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7th International Conference on Intelligent Computing and Signal Processing, ICSP 2022

作者： Shao, Xueqi Ning, Haonan Yang, Wenjun Niu, Yafeng Southeast University School of Mechanical Engineering Department of Industrial Design Nanjing China National Key Laboratory of Science and Technology on Aircraft Control Xi'an China

ISBN: (纸本)9781665478571

Eye-blink control means that users blink intentionally to realize human-computer interaction. An intentional eye-blink signal acquisition and control system based on flexible pressure sensor is designed, which aims to control the object through simple eye movements such as blinking and winking. The system uses two pressure sensors to collect the blink signals at the orbicularis oculi muscles of the left and right eyes respectively. The software part realizes the acquisition and recognition of six intentional eye-blink signals, and transmits blink-control instruction signals through Bluetooth, so as to realize the control of the remote-controlled vehicle. The advantage of this system is that it is not affected by illumination and does not need GUI interface for control. The availability of the system is qualified after system test. © 2022 IEEE.

关键词： Human computer interaction

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Longitudinal Transition Analysis and control of a Tilt-Body VTOL aircraft

Longitudinal Transition Analysis and Control of a Tilt-Bo...

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International Conference on Guidance, Navigation and control, ICGNC 2024

作者： Lou, Jinhao Zhao, Longfei Li, Ke Zhong, Xiancheng Shang, Yaoxing Jiao, Zongxia School of Automation Science and Electrical Engineering Beihang University Beijing100191 China Key Laboratory of Advanced Aircraft Systems Beijing100083 China Science and Technology on Aircraft Control Laboratory Beijing100083 China Ningbo Institute of Technology Beihang University Ningbo315800 China Tianmushan Laboratory Hangzhou310023 China State Grid Qinghai Electric Power Co. Ltd. Qinghai Xining810001 China

ISBN: (纸本)9789819622351

Vertical takeoff and landing (VTOL) aircrafts are characterized by large flight envelopes and significant variations in flight operational conditions, making the analysis of flight envelopes and the design of controllers inherent challenges. This study focused on a tilt-body VTOL aircraft, analyzing its longitudinal flight envelope, namely transition corridors. It demonstrated that the tilt-body have a broad flight envelope and designed a longitudinal flight controller based on transition corridor trimming and total energy control theory. The theoretical approach was validated through simulation, achieving full-speed range level flight control and effective longitudinal flight control for the tilt-body. Simulation results show that this method can compensate for nonlinearities in the model and exhibits robustness, allowing the tilt-body aircraft to demonstrate excellent flight performance during transition flight. This research provides valuable insights and guidance for the analysis and control of a class of VTOL aircraft, particularly significant for the design of new VTOL configurations. © The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd. 2025.

关键词： VTOL/STOL aircraft

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A RESEARCH OF THE DISCRETE DIGITAL BRAKE VALVE MATCHING DESIGN AND control FOR LARGE aircraft

A RESEARCH OF THE DISCRETE DIGITAL BRAKE VALVE MATCHING DESI...

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

作者： Wang, Yi Wu, Shuai Jin, Hongtao Li, Chuandong Gao, Xiaolong Jiao, Zongxia School of Automation Science and Electrical Engineering Beihang University Beijing100191 China National Key Laboratory of Aircraft Integrated Flight Control Beihang University Beijing100191 China Ministry of Industry and Information Technology Beijing100191 China Ningbo Institute of Technology Beihang University Ningbo315800 China Tianmushan Laboratory Hangzhou310023 China

The aircraft braking system is a vital component of the aircraft, responsible for dissipating the kinetic energy of the aircraft and slowing it down to stop. In the field of aircraft braking systems, hydraulic systems with high power-to-weight ratios are currently the preferred choice. The brake control valve is a crucial component of the braking system, regulating the pressure of the essential components. The use of a discrete digital valve, designed to be pollution-resistant and fault-tolerant, can significantly enhance the performance of the braking system. The majority of existing designs and selections for discrete digital valves are based on experience, which may result in the unnecessary increase in system redundancy, volume and weight. This paper analyses the requirements of an aircraft braking system, combining the load situation and actual working conditions to determine the matching design of discrete digital valves. The efficacy of the designed brake valve in terms of performance and braking effectiveness is validated through the construction of a discrete digital valve braking system model. © The Institution of Engineering & technology 2024.

关键词： aircraft hydraulic systems

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