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Chinese control Conference (CCC)

作者： Ruichi Ren Kaiyu Qin Wantao Deng Jiangfeng Yue Mengji Shi Boxian Lin School of Aeronautics and Astronautics University of Electronic Science and Technology of China Chengdu China The Aircraft Swarm Intelligent Sensing and Cooperative Control Key Laboratory of Sichuan Province Chengdu China Southwest Institute of Technical Physics Chengdu China

This paper investigates the fixed-time bipartite tracking consensus problem for heterogeneous multi-agent systems (HMASs) in a directed signed network. The HMASs consist of a fractional-order leader and first-order followers which subject to input disturbances. Not only the different dynamic characteristics, but also the directional communication networks among heterogeneous agents, which increase the difficulty of controller design. According to the Lyapunov stability theory and graph theory, a more compact fixed-time distributed protocol is proposed, which rejects bounded disturbances by simply specifying a sufficiently large gain coefficient for the nonlinear control input. Under the designed protocol, followers can achieve bipartite consensus tracking for leader agent within a preset settling time, which is independent of the initial values of agents. Finally, several simulation tests are presented to verify the effectiveness of the proposed controller.

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Cooperative guidance strategy for multiple hypersonic gliding vehicles system

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Chinese Journal of Aeronautics 2020年第3期33卷 990-1005页

作者： Jianglong YU Xiwang DONG Qingdong LI Zhang REN Jinhu LV School of Automation Science and Electrical Engineering Science and Technology on Aircraft Control LaboratoryBeihang UniversityBeijing 100083China Beijing Advanced Innovation Center for Big Data and Brain Computing Beihang UniversityBeijing 100083China Shananxi Key Laboratory of Integrated and Intelligent Navigation Xi’an 710068China

Cooperative guidance strategy for multiple hypersonic gliding vehicles system with flight constraints and cooperative constraints is *** paper mainly cares about the coordination of the entry glide flight phase and driving-down *** from the existing results,both the attack time and the attack angle constraints are considered ***, for the entry glide flight phase, a two-stage method is proposed to achieve the rapid cooperative trajectories planning, where the control signal corridors are designed based on the quasi-equilibrium gliding *** the first stage, the bank angle curve is optimized to achieve the attack angle *** the second stage, the angle of attack curve is optimized to achieve the attack time *** optimized parameters can be obtained by the secant ***, for the driving-down phase, the cooperative terminal guidance law is designed where the terminal attack time and attack angle are *** guidance law is then transformed into the bank angle and angle of attack *** cooperative guidance strategy is summarized as an ***, a numerical simulation example with three hypersonic gliding vehicles is provided for revealing the effectiveness of the acquired strategy and algorithm.

关键词： Attack angle constraints Attack time constraints Cooperative guidance Cooperative path planning Entry guidance Hypersonic vehicles

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Numerical simulation and experimental research on Taylor Couette flow characteristics in air gap of aviation motor

Numerical simulation and experimental research on Taylor Cou...

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

作者： Hui Ma Shuyue Liang Hongbo Zhan Lin Qi Weijian Chen Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration No.33 Shuige Road Nanjing People's Republic of China Key Laboratory of Aircraft Environment Control and Life Support MIIT Nanjing University of Areonautics and Astronautics No.29 Yudao Street Nanjing People's Republic of China

ISBN: (数字)9781837242108

A test bench with PIV technology was built and visualization research on Taylor vortex between concentric rotating cylinders was carried out to explore the flow morphology within the annular gap by changing the rotational speed of the inner cylinder. The numerical method and accuracy were verified by experiments. The selected turbulence model was then applied for numerical simulation of the Taylor Couette flow in a simplified air gap model of an aviation motor with smooth inner and outer walls. The Taylor Couette flow characteristics in the air gap under varying rotational speed were studied, and simulation results were given for flow with axial flow and without axial flow.

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ANALYSIS OF AERODYNAMIC COUPLING EFFECT IN CLOSE FORMATION FOR FLAPPING WINGS 32

ANALYSIS OF AERODYNAMIC COUPLING EFFECT IN CLOSE FORMATION F...

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

作者： Chen, Zhaotong Jiao, Zongxia Shang, Yaoxing Zhao, Longfei School of Automation Science and Electrical Engineering Beihang University Beijing100191 China Science and Technology on Aircraft Control Laboratory Beihang University Beijing100191 China Ningbo Institute of Technology Beihang University Ningbo315800 China Research Institute for Frontier Science Beihang University Beijing100191 China

ISBN: (纸本)9783932182914

This work explores the unsteady interaction between the streamwise vortices and the follower in a V-shaped close flapping wings formation. The advanced high fidelity LBM simulation and finite explicit dynamic solver are used to calculate the fluid structure interaction. First, the vortex effect during flapping process of flexible wing shows that the suction side adsorption effect after LEV formation will increase the lift. Due to the existence of angle of attack, the structure and aerodynamic characteristics of the LEV are different. In addition, the wing buffeting is caused by the breakdown of LEV near the median of stroke. Second, the flow structure is obviously different when the spatial phase is in phase. The spatial drift of follower's TIV, the delay of vortex shedding and the secondary vortex structure indicate that the coupling effect with incident vortex is strong. But in other temporal phases, these unsteady phenomena weaken or disappear, and are replaced by the finite time collision between the wing and the incident vortex. By comparing the aerodynamic load curves, it is found that the lift is significantly increased and the net thrust is decreased most in the same phase. However, this change is obviously weakened in other phases. The smaller the spatial phase difference is, the more obvious the aerodynamic effect is. This indicates that the coupling form of aerodynamic effect may exist between the close formation of flapping wing and the specific temporal phase when the position of two aircraft is fixed. © 2021 32nd Congress of the International Council of the Aeronautical sciences, ICAS 2021. All rights reserved.

关键词： Vortex flow

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Impact of Dead Time Effect on Common Mode Electromagnetic Interference in PMSM Drives

Impact of Dead Time Effect on Common Mode Electromagnetic In...

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Asia-Pacific Symposium on Electromagnetic Compatibility (APEMC)

作者： Yuxiang Xue Hui Li Yingzhe Wu Minghai Dong Lisheng Wang Hengbin Zhang Xi Liu 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 Beijing Research and Development Center Shanghai Gatek Automotive Electronics Company Ltd Beijing China School of Automation Engineering University of Electronic Science and Technology of China Chengdu China

ISBN: (数字)9784885523472

ISBN: (纸本)9798350349498

The pulse width modulation (PWM) technique has been widely applied in permanent magnet synchronous motor (PMSM) drives, which causes common mode (CM) electromagnetic interference (EMI) issue due to its higher frequency. And moreover, this issue will be intensified by the dead time area inserted into the control signal of the switching device (such as IGBT or MOSFET) in the power inverter. In this paper, the CM voltage/current has been analyzed with the considerations of the switching process of the MOSFET as well as the influence of the dead time effect. In order to reduce the CM voltage/current, a dead time compensation method is recommended, which can reduce the distortion of CM voltage/current and relieve the high-frequency (HF) CM EMI noise. According to experiment result, it can be figured out that the spectra of the CM current have been reduced by nearly 5.5 dB $\mu$A at the resonance frequency with an appropriate dead time compensation in PMSM drives.

关键词： MOSFET Time-frequency analysis Electromagnetic interference Noise Switches Pulse width modulation Electromagnetic compatibility

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Dual-channel Dynamical Event-Triggered Load Frequency control under Attack for Wind Power Systems with Multiple Time-varying Delay

Dual-channel Dynamical Event-Triggered Load Frequency Contro...

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IEEE International Conference on Power and Power and Renewable Energy (ICPRE)

作者： Hanmei Zhou Qishui Zhong Shaoyu Hu Jin Yang Kaibo Shi School of Aeronautics and Astronautics University of Electronic Science and Technology Aircraft Swarm Intelligent Sensing and Cooperative Control Key Laboratory of Sichuan Province Chengdu China School of Aeronautics and Astronautics University of Electronic Science and Technology Chengdu China School of Electronic Information and Electrical Engineering Chengdu University Chengdu China

In order to stabilize a multi-time-delay interconnected wind power system, a dual-channel dynamic event-triggered load frequency control scheme is proposed, considering network attacks in this paper. Firstly, this paper designs load frequency control of wind power system incorporating the effect of time-varying delay both in the states and control input. Secondly, in order to reduce the occupancy of communication bandwidth, a novel transmission scheme with two asynchronous event triggers network channels has been designed. Further, a malicious bounded time-delay deception attack model is proposed to enhance the security. By constructing a discrete-type Lyapunov-Krasovskii functional, stability criteria with H ∞ performance index are established. Finally, numerical examples are presented to demonstrate the effectiveness of the proposed control method.

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The Formation control Based on the Direction Coordination for Multiple Hypersonic Vehicles

The Formation Control Based on the Direction Coordination fo...

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Chinese control Conference (CCC)

作者： Yuqing Zhang Jianglong Yu Zhang Ren Xiwang Dong Qingdong Li Yan Zhou Kaiqiang Liang Junxiang Wang Science and Technology on Aircraft Control Laboratory School of Automation Science and Electrical Engineering Beihang University Beijing P.R. China Institute of Artificial Intelligence Beihang University Beijing P.R. China China Academy of Launch Vehicle Technology Beijing P.R. China

In this paper, a formation strategy based on the direction coordination and consistency of velocity and the optimization of the initial states is introduced for the formation of multiple hypersonic vehicles. Firstly, considering the mode of leader-follower, a two-dimensional controller is designed based on the dynamic model of hypersonic vehicle, which could realize the consistency of flight path angle and azimuth angle between followers and leader. Secondly, the initial states of the vehicles and the control parameters of the controller are taken as optimization variables, and the deformation of the formation during the whole flight is designed as the objective function. Finally, the combination of the PSACO (particle swarm ant colony optimization) algorithm and the SQP (sequential quadratic programming) algorithm is used to solve the optimization model. The simulation results show that the multiple hypersonic vehicles can achieve better formation flight based on the above methods.

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Design and Flight Test of a Compact and Rapidly-Deployable Air-Launched Inflatable-Winged aircraft

Design and Flight Test of a Compact and Rapidly-Deployable A...

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AIAA science and technology Forum and Exposition, AIAA SciTech Forum 2025

作者： Ge, Hang Xu, Yixiang Sun, Donglei Chen, Xinmin Chen, Boyang School of Aerospace Faculty of Science and Engineering University of Nottingham Ningbo China Zhejiang Ningbo315100 China Department of Mechanical Materials and Manufacturing Engineering UNNC-NFTZ Blockchain Laboratory University of Nottingham Ningbo China Zhejiang Ningbo315100 China Advanced Intelligent Manufacturing Research Group Control System Lab University of Nottingham Ningbo China Zhejiang Ningbo315100 China Zhejiang Provincial Engineering Research Center of Special Aircraft Ningbo Institute of Materials Technology & Engineering Chinese Academy of Sciences Zhejiang Ningbo315100 China

ISBN: (数字)9781624107238

ISBN: (纸本)9781624107238

In this research, a high-altitude, compact and rapidly deployable, air-launched, inflatablewinged aircraft is designed, developed, and flight-tested to investigate the flight characteristics of inflatable-winged aircraft as well as the in-flight inflation and dynamic deployment properties when launched from various carriers. To start with, two types of inflatable wings employing different materials have been designed, fabricated, and tested, the tests including structural characteristics tests, inflation properties tests, and low-Reynolds-number wind-tunnel tests. A full-scale 30-kilogram prototype unmanned aerial vehicle with inflatable wings was then designed, assembled and tested with some basic low-altitude flights to verify the feasibility of the aerodynamic layout and the trim and stability and control characteristics. Finally, low- and high-altitude in-flight launches will be conducted to study the dynamic deployment properties and high-altitude flight characteristics of this design. © 2025, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： Wind tunnels

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High-Frequency Modeling of Common-Mode and Differential-Mode Impedances in LLC Resonant Converters

High-Frequency Modeling of Common-Mode and Differential-Mode...

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IEEE International Symposium on Circuits and Systems (ISCAS)

作者： Chuang Bi Siyong Luo Yi Wu School of Astronautics and Aeronautics/Aircraft swarm intelligent sensing and cooperative control Key Laboratory of Sichuan Province University of Electronic Science and Technology of China Chengdu China State Grid Shanghai Municipal Electric Power Company Shanghai China

LLC resonant converters have been widely used in industry because of its soft switching characteristics in the full load range. However, due to the increasing switching frequency with the help of wideband-gap devices, electromagnetic interference (EMI) of LLC resonant converters has become a key problem in such systems. High dv/dt or di/dt of wideband-gap (WBG) semiconductor switches produce a large number of high-frequency harmonic components, thus common-mode (CM) and differential-mode (DM) noise signals are generated in LLC resonant converters. In order to investigate EMI issues, an improved CM and DM models are established respectively to represent the high-frequency behavior, and the equivalent circuit parameters of CM and DM impedances are extracted according to the experimental results. The calculated CM and DM impedances are in good agreement with the measured ones from the vector network analyzer (VNA), which verifies the effectiveness of the proposed high-frequency CM and DM models.

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Robust Adaptive Fixed-Time Consensus for Nonlinear High-Order Multi-Agent Systems

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IEEE Transactions on Automation science and Engineering 2025年 22卷 15832-15845页

作者： Li, Jiale Li, Guofei Guo, Zheng Zuo, Zongyu Zheng, Xiaojing Northwestern Polytechnical University School of Aeronautics Xi’an710072 China Northwestern Polytechnical University Institute of Extreme Mechanics Xi’an710072 China Northwestern Polytechnical University School of Astronautics Xi’an710072 China Beihang University School of Automation Science and Electrical Engineering Beijing100191 China Science and Technology on Aircraft Control Laboratory Beijing100191 China Xidian University School of Information Mechanics and Sensing Engineering Xi’an710071 China

This paper investigates the consensus problem of leader-follower nonlinear high-order multi-agent systems through a fully distributed approach. A distributed consensus tracking control scheme is proposed, embedding a fixed-time convergent command filter with adaptive gain to ensure that the filter error ultimately reaches the origin. To tackle the challenges posed by unknown bounds of system nonlinearities and external disturbances, a robust control protocol is developed, incorporating an adaptive mechanism to implement compensatory action instead of directly estimating the lumped uncertainty. A notable feature of the proposed approach lies in its capability to determine the settling time bound without any global information, including the number of nodes, the eigenvalue of the Laplacian matrix, and other unknown parameters. The efficacy of the developed methodology is validated through numerical simulations and physical experiment conducted on a multi-motor system. © 2004-2012 IEEE.

关键词： Robust control

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