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学者姓名：张和洪
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Abstract ：
The levitation control system is a critical subsystem in maglev trains, ensuring stable levitation of the train on the guideway. Achieving stable levitation requires providing the system with accurate levitation gap and corresponding velocity data while minimizing phase lag. This work proposes an enhanced tracking differentiator (TD) to reduce phase lag in both filtering and differentiation of input signals with varying noise levels. The improved performance is achieved by incorporating system damping and an amplitude factor into the control algorithm used to design the differentiator. Theoretical analysis guarantees the convergence of the proposed algorithm. Simulations and experiments conducted on the levitation gap data demonstrate the superior performance of the proposed TD in reducing phase lag for both filtered and differentiated signals. Furthermore, experimental results highlight the improved performance of the feedback controller when employing the proposed TD.
Keyword ：
control nonlinearities control nonlinearities damping damping differentiation differentiation magnetic levitation magnetic levitation tracking tracking
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| GB/T 7714 | Zhang, Louyue , Xiao, Gaoxi , Zhai, Chao et al. Maglev train levitation control via tracking differentiator with small phase lag [J]. | IET CONTROL THEORY AND APPLICATIONS , 2025 , 19 (1) . |
| MLA | Zhang, Louyue et al. "Maglev train levitation control via tracking differentiator with small phase lag" . | IET CONTROL THEORY AND APPLICATIONS 19 . 1 (2025) . |
| APA | Zhang, Louyue , Xiao, Gaoxi , Zhai, Chao , Zhang, Hehong . Maglev train levitation control via tracking differentiator with small phase lag . | IET CONTROL THEORY AND APPLICATIONS , 2025 , 19 (1) . |
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针对高空台进气环境模拟系统(IESS)存在压力与温度双变量强耦合及发动机快速过渡态试验带来的强总和扰动问题,设计一种新型固定时间滑模控制器(FxTSMC)并结合固定时间扩张状态观测器(FxTESO),提出一种固定时间自抗扰复合解耦控制(FxT-ADRCDC)方法.具体地,采用静态解耦方法将IESS解耦为两个单输入、单输出系统,实现IESS温度和压力的独立控制.在总扰动估计与抑制方面,利用固定时间扩张状态观测器快速准确估计系统状态与包含系统动态耦合在内的总扰动,并提出一种能够避免奇异问题且快速收敛的新型FxTSMC,将总扰动补偿到FxTSMC中,得到FxT-ADRCDC方法.设计Lyapunov函数证明了闭环控制系统的固定时间稳定性,得到不依赖于初始条件的稳定时间上限.搭建高置信度IESS仿真平台开展发动机过渡态飞行任务试验,对比了本文所提出方法与线性自抗扰解耦控制(LADRDC)方法.结果显示,FxT-ADRCDC方法控制下的进气压力、温度的绝对积分误差比LADRDC方法平均减少约70.3%和70.7%,且阀门摆动量符合实际工程要求,有效实现了进气压力、温度的高品质解耦控制,为提升IESS的快速、精确的动态模拟能力提供有力的技术支撑.
Keyword ：
固定时间 固定时间 快速过渡态试验 快速过渡态试验 滑模控制器 滑模控制器 线性自抗扰解耦控制 线性自抗扰解耦控制 自抗扰复合解耦控制 自抗扰复合解耦控制 进气环境模拟系统 进气环境模拟系统 高空台 高空台
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| GB/T 7714 | 徐周浙 , 张和洪 , 翟超 et al. 高空台进气环境模拟系统固定时间自抗扰复合解耦控制 [J]. | 推进技术 , 2025 , 46 (2) : 234-247 . |
| MLA | 徐周浙 et al. "高空台进气环境模拟系统固定时间自抗扰复合解耦控制" . | 推进技术 46 . 2 (2025) : 234-247 . |
| APA | 徐周浙 , 张和洪 , 翟超 , 钱秋朦 , 吴林峰 . 高空台进气环境模拟系统固定时间自抗扰复合解耦控制 . | 推进技术 , 2025 , 46 (2) , 234-247 . |
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针对航空发动机高空模拟试验对进气环境压力模拟控制系统所提出的高精度、强抗扰性、强鲁棒性的迫切需求,提出一种线性/非线性自抗扰控制切换控制策略.首先,分析了高空舱进气环境压力模拟控制系统的技术难点并基于高空舱环境模拟进气系统的基本结构,推导出其数学模型以及建立仿真试验平台;随后,分析了线性自抗扰控制和非线性自抗扰控制各自的优缺点,进而设计了线性/非线性自抗扰切换控制策略;最后,在仿真平台上验证了线性/非线性自抗扰切换控制策略,并与单独采用线性自抗扰控制或非线性自抗扰控制进行了对比分析.结果表明,线性/非线性自抗扰切换控制器兼具线性与非线性自抗扰的优势,能够根据任务工况实时切换合适的自抗扰控制器,进一步提升进气环境模拟控制系统的抗扰能力、调节时间与控制精度,具有较高的工程应用价值和前景.
Keyword ：
切换控制 切换控制 压力跟踪控制 压力跟踪控制 稳态试验 稳态试验 自抗扰控制 自抗扰控制 过渡态试验 过渡态试验 高空舱 高空舱
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| GB/T 7714 | 傅随金 , 黄志贤 , 李超洋 et al. 基于SADRC的进气压力控制技术仿真研究 [J]. | 燃气涡轮试验与研究 , 2025 , 38 (1) : 56-65 . |
| MLA | 傅随金 et al. "基于SADRC的进气压力控制技术仿真研究" . | 燃气涡轮试验与研究 38 . 1 (2025) : 56-65 . |
| APA | 傅随金 , 黄志贤 , 李超洋 , 但志宏 , 张和洪 . 基于SADRC的进气压力控制技术仿真研究 . | 燃气涡轮试验与研究 , 2025 , 38 (1) , 56-65 . |
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航空发动机性能测试的准确性直接影响其研发和优化效果,对国防科技和航空工业发展至关重要.本文提出了一种结合干扰观测器和非奇异终端滑模(NTSM)的复合分层抗干扰控制(CHADC)方法.将干扰分为内部扰动(包括未建模动态、参数和结构的不确定性)和外部扰动.采用干扰观测器对内部扰动进行估计并通过前馈加以抵消,使用非奇异终端滑模控制方法抑制外部扰动,同时设计了一种新型趋近律,解决了控制量抖动过大的问题.仿真结果表明,通过采用干扰观测器与非奇异终端滑模结合的复合分层抗干扰控制方法,能将被控压力的压力最大瞬时波动量降到0.5%以内,动态调节时间减少2s以上,大幅提高了发动机过渡态试验中的动态响应速度、控制精度和抗扰动能力.这一研究成果能够为航空发动机的研发和测试提供更加精确的环境模拟,从而加速航空发动机的性能优化.
Keyword ：
复合分层抗干扰 复合分层抗干扰 干扰观测器 干扰观测器 趋近律 趋近律 非奇异终端滑模 非奇异终端滑模 高空舱 高空舱
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| GB/T 7714 | 李鑫 , 齐熙溥 , 王信 et al. 高空舱进气压力环境模拟系统的复合分层抗干扰控制 [J]. | 航空科学技术 , 2025 , 36 (3) : 95-104 . |
| MLA | 李鑫 et al. "高空舱进气压力环境模拟系统的复合分层抗干扰控制" . | 航空科学技术 36 . 3 (2025) : 95-104 . |
| APA | 李鑫 , 齐熙溥 , 王信 , 翟超 , 张和洪 . 高空舱进气压力环境模拟系统的复合分层抗干扰控制 . | 航空科学技术 , 2025 , 36 (3) , 95-104 . |
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To address significant disturbances, including sudden air flow variation, model uncertainty, and unavoidable measurement noises during aeroengine transient tests in the intake environmental pressure simulation system (IEPSS), a sliding mode active disturbance rejection controller (SMADRC) is designed. The sliding mode control in SMADRC can deal with unmatched disturbances that are beyond the capabilities of the extended state observer (ESO) in ADRC. And the particle swarm optimization (PSO) algorithm is introduced to tune and optimize the controller parameters to further enhance the performance. To validate the effectiveness of the proposed method, simulations are conducted on the IEPSS software platform. The simulation results clearly demonstrate PSO-SMADRC can reduce the mean squared error by 60.9%, the input oscillation by 68.7%, and the maximum deviation by 53.9%, compared with LADRC originally applied in the IEPSS.
Keyword ：
active disturbance rejection control active disturbance rejection control non-linear control systems non-linear control systems particle swarm optimisation particle swarm optimisation pressure control pressure control
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| GB/T 7714 | Chuanjian, Li , Chao, Zhai , Hehong, Zhang et al. PSO-SMADRC for altitude test facility intake pressure environmental simulation system [J]. | ELECTRONICS LETTERS , 2024 , 60 (3) . |
| MLA | Chuanjian, Li et al. "PSO-SMADRC for altitude test facility intake pressure environmental simulation system" . | ELECTRONICS LETTERS 60 . 3 (2024) . |
| APA | Chuanjian, Li , Chao, Zhai , Hehong, Zhang , Shiqi, Zheng . PSO-SMADRC for altitude test facility intake pressure environmental simulation system . | ELECTRONICS LETTERS , 2024 , 60 (3) . |
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With strong nonlinearity， high uncertainty and strong external disturbance for flight altitude simulation of altitude test facility， a robust cascade linear active disturbance rejection control (LADRC) algorithm via the reduced order linear extended state observer (RLESO) was proposed. In particular， the main characteristics and control issues of the controlled plant were analyzed， and the generalized controlled plant can be included by the butterfly valve position loop and flight altitude loop. The RLESO and corresponding controller were designed for the two loops respectively， meanwhile the cascade control system was constructed. The robust cascade LADRC was realized in the simulation environment and compared with the classical PID control scheme. When the engine was subject to the thrust transient test，the maximum fluctuation value of the controlled pressure was reduced from 3.5 kPa to 0.8 kPa. This indicated that the robust cascade LADRC technology via RLESO can significantly improve the dynamic control quality. The ideal robust control performance and anti-disturbance ability for flight altitude simulation were obtained. © 2024 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.
Keyword ：
Altitude control Altitude control Cascade control systems Cascade control systems Disturbance rejection Disturbance rejection Flight control systems Flight control systems Flight simulators Flight simulators Quality control Quality control Robust control Robust control State estimation State estimation Three term control systems Three term control systems
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| GB/T 7714 | Dan, Zhihong , Zhang, Song , Zhang, Hehong et al. Robust cascade LADRC technology for flight altitude simulation of high altitude cell [J]. | Journal of Aerospace Power , 2024 , 39 (4) . |
| MLA | Dan, Zhihong et al. "Robust cascade LADRC technology for flight altitude simulation of high altitude cell" . | Journal of Aerospace Power 39 . 4 (2024) . |
| APA | Dan, Zhihong , Zhang, Song , Zhang, Hehong , Qian, Qiumeng , Wang, Xin , Zhao, Wei . Robust cascade LADRC technology for flight altitude simulation of high altitude cell . | Journal of Aerospace Power , 2024 , 39 (4) . |
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The flight environment simulation system plays a crucial role in aeroengine testing, replicating real mission pressure and temperature conditions. However, existing systems face challenges in handling strong measurement noises and total disturbances during transient tests, leading to inaccurate simulations and potential actuator damage. To address these gaps, an enhanced tracking differentiator based active disturbance rejection control scheme is proposed and implemented. Our method introduces two key innovations: a discrete-time optimal control law that dynamically adjusts control inputs based on state transition and sampling times, and a phase-advancing method that mitigates filtering phase delays by incorporating derivative signals to predict input trends. These components are integrated into a novel tracking differentiator, enhancing the estimation capability of the extended state observer in active disturbance rejection control. Frequency-domain analysis demonstrates the proposed tracking differentiator's superior filtering performance and phase quality. Simulations of intake environment pressure during aeroengine transient tests reveal that, compared to traditional tracking differentiator-based active disturbance rejection control, the proposed approach significantly reduces both control signal oscillations and setpoint deviations by 75.44% and 53.9%, respectively. These improvements effectively address environment simulation deviations and unnecessary actuator wear, thereby enhancing the accuracy and reliability of aeroengine testing. © 2024 Elsevier Masson SAS
Keyword ：
Active disturbance rejection control Active disturbance rejection control Aeroengine transient tests Aeroengine transient tests Filtering Filtering Flight environment simulation system Flight environment simulation system Intake pressure simulation Intake pressure simulation Phase delay Phase delay Time criterion Time criterion Tracking differentiator Tracking differentiator
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| GB/T 7714 | Li, C. , Zhang, H. , Xiao, G. et al. An efficient tracking differentiator based active disturbance rejection control for flight environment simulation system [J]. | Aerospace Science and Technology , 2024 , 155 . |
| MLA | Li, C. et al. "An efficient tracking differentiator based active disturbance rejection control for flight environment simulation system" . | Aerospace Science and Technology 155 (2024) . |
| APA | Li, C. , Zhang, H. , Xiao, G. , Zhai, C. , Dan, Z. , Wang, X. . An efficient tracking differentiator based active disturbance rejection control for flight environment simulation system . | Aerospace Science and Technology , 2024 , 155 . |
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Multi-view learning has received increasing attention in recent years due to its ability to leverage valuable patterns hidden in heterogeneous data sources. While existing studies have achieved encouraging results, especially those based on graph convolutional networks, they are still limited in their ability to fully exploit the connectivity relationships between samples and are susceptible to noise. To address the aforementioned limitations, we propose a framework called geometric localized graph convolutional network for multi-view semi-supervised classification. This framework utilizes a diffusion map to obtain the geometric structure of the feature space of multiple views and constructs a stable distance matrix that considers the local connectivity of nodes on the geometric structure. Additionally, we propose a truncated diffusion correlation function that maps the distance matrix of each view into correlations between samples to obtain a reliable sparse graph. To fuse the features, we use learnable weights to concatenate the coordinates of the geometric structure. Finally, we obtain a graph embedding of the fused feature and topology by using graph convolutional networks. Comprehensive experiments demonstrate the superiority of the proposed method over other state-of-the-art methods. © 2024 Elsevier Inc.
Keyword ：
Convolution Convolution Diffusion Diffusion Geometry Geometry Supervised learning Supervised learning Topology Topology
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| GB/T 7714 | Huang, Aiping , Lu, Jielong , Wu, Zhihao et al. Geometric localized graph convolutional network for multi-view semi-supervised classification [J]. | Information Sciences , 2024 , 677 . |
| MLA | Huang, Aiping et al. "Geometric localized graph convolutional network for multi-view semi-supervised classification" . | Information Sciences 677 (2024) . |
| APA | Huang, Aiping , Lu, Jielong , Wu, Zhihao , Chen, Zhaoliang , Chen, Yuhong , Wang, Shiping et al. Geometric localized graph convolutional network for multi-view semi-supervised classification . | Information Sciences , 2024 , 677 . |
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This work is concerned with the L-1 bumpless transfer control issue for switched positive delayed systems on finite horizons. A bumpless transfer input scheme and a state-dependent limited frequency switching scheme, induced by the transient control input discontinuities during controller switching and by the frequent switching for multiple subsystems, respectively, are jointly introduced. The main advantages of the presented schemes are that the amplitude of the control input discontinuities and the frequent switches are all reduced by the dual design of bumpless transfer controllers for subsystems and a state-dependent limited frequency switching scheme. By utilizing the multiple linear copositive Lyapunov functionals, sufficient conditions are also offered so as to achieve the desirable closed-loop performances, including positivity, finite-time boundedness, bumpless transfer property and a prescribed L-1-gain property. Finally, a practical example is borrowed which validates the proposed schemes.
Keyword ：
bumpless transfer bumpless transfer finite-time L-1-gain performance finite-time L-1-gain performance state-dependent switching state-dependent switching switched positive delayed systems switched positive delayed systems
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| GB/T 7714 | Wang, Peng , Lin, Pin , Zhang, Hehong et al. Finite-time L1 bumpless transfer control for switched positive delayed systems: A state-dependent limited frequency switching scheme [J]. | INTERNATIONAL JOURNAL OF ROBUST AND NONLINEAR CONTROL , 2024 , 34 (13) : 9166-9181 . |
| MLA | Wang, Peng et al. "Finite-time L1 bumpless transfer control for switched positive delayed systems: A state-dependent limited frequency switching scheme" . | INTERNATIONAL JOURNAL OF ROBUST AND NONLINEAR CONTROL 34 . 13 (2024) : 9166-9181 . |
| APA | Wang, Peng , Lin, Pin , Zhang, Hehong , Zhao, Ying , Sang, Hong , Dimirovski, Georgi M. . Finite-time L1 bumpless transfer control for switched positive delayed systems: A state-dependent limited frequency switching scheme . | INTERNATIONAL JOURNAL OF ROBUST AND NONLINEAR CONTROL , 2024 , 34 (13) , 9166-9181 . |
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The ability of a high-altitude test bench flight environment simulation system to accurately simulate high-altitude environmental parameters plays a crucial role in the performance testing and evaluation of aviation engines. However, the strong coupling between controlled pressure and temperature variables in the core air intake environment simulation subsystem, along with sensor measurement noise, limits the overall control quality of environmental parameters. For this purpose, this paper proposes an adaptive active disturbance rejection control based on coupling degree identification, abbreviated as AADRC, which efficiently matches the system control channels while solving the flight environment simulation control problems caused by variable coupling and measurement noise. Based on the relative gain array method, the coupling degree of the control variables of the linearized system is identified, providing a matched control loop for the high-temperature gas control valve and the low-temperature gas control valve. Considering the impact of sensor measurement noise on the performance of active disturbance rejection control, an adaptive extended state observer with adaptive bandwidth adjustment method based on relative gain array method, referred to as AESO, is proposed.
Keyword ：
active disturbance rejection control active disturbance rejection control coupling analysis coupling analysis decoupled control algorithms decoupled control algorithms extended state observer extended state observer flight environment simulation platform flight environment simulation platform relative gain array relative gain array
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| GB/T 7714 | Wu, Linfeng , Qian, Qiumeng , Zhai, Chao et al. Adaptive Active Disturbance Rejection Control based on Coupling Coefficient with Applications to Flight Environment Simulation System [J]. | 2024 43RD CHINESE CONTROL CONFERENCE, CCC 2024 , 2024 : 2721-2726 . |
| MLA | Wu, Linfeng et al. "Adaptive Active Disturbance Rejection Control based on Coupling Coefficient with Applications to Flight Environment Simulation System" . | 2024 43RD CHINESE CONTROL CONFERENCE, CCC 2024 (2024) : 2721-2726 . |
| APA | Wu, Linfeng , Qian, Qiumeng , Zhai, Chao , Zhang, Hehong . Adaptive Active Disturbance Rejection Control based on Coupling Coefficient with Applications to Flight Environment Simulation System . | 2024 43RD CHINESE CONTROL CONFERENCE, CCC 2024 , 2024 , 2721-2726 . |
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