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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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Open-circuit faults in power switching elements are primary failures of active magnetic bearing (AMB) system. However, the characteristics of current signals of switching elements have not been fully used in the diagnosis of open-circuit faults in magnetic bearings. This article proposes a tracking differentiator (TD) algorithm, referred as Fast-TD, to extract differential information from the current signal, which is applied to the fault diagnosis of open-circuit failures in magnetic bearings. Especially, the rigorous convergence proof of the Fast-TD algorithm is presented. First, when a switching element of the three-phase full-bridge in AMB system is open-circuited, theoretical analysis demonstrates the feasibility of diagnosing the open-circuit faults in power switching elements in real time by analyzing the differential signals from the current sensor. Then, the Fast-TD algorithm for extracting the differential information of current sensor is proposed and its convergence is proven by demonstrating the convergence trajectories of the states within different regions. Next, the current differential extraction method via Fast-TD is applied to the fault diagnosis and fault-tolerant control (FTC) of a magnetic system. The case studies, which include comparison simulations with two other differentiators, verify the effectiveness of the proposed Fast-TD algorithm.
Keyword ：
Circuit faults Circuit faults Circuits Circuits Coils Coils Convergence Convergence Fast-tracking differentiator (TD) Fast-tracking differentiator (TD) fault-diagnosis fault-diagnosis Fault diagnosis Fault diagnosis magnetic bearing magnetic bearing Magnetic levitation Magnetic levitation open-circuit fault open-circuit fault Power amplifiers Power amplifiers Rotors Rotors Switches Switches Switching circuits Switching circuits switching element switching element
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| GB/T 7714 | Zhang, Zhizhou , Pan, Yueliang , Zi, Zheng et al. Current Differential Signal Extraction Algorithm via Fast-TD and Its Application in Open-Circuit Fault Diagnosis of Magnetic Bearings [J]. | IEEE TRANSACTIONS ON INSTRUMENTATION AND MEASUREMENT , 2025 , 74 . |
| MLA | Zhang, Zhizhou et al. "Current Differential Signal Extraction Algorithm via Fast-TD and Its Application in Open-Circuit Fault Diagnosis of Magnetic Bearings" . | IEEE TRANSACTIONS ON INSTRUMENTATION AND MEASUREMENT 74 (2025) . |
| APA | Zhang, Zhizhou , Pan, Yueliang , Zi, Zheng , Xie, Yuan , Zhao, Weilong , Zhang, Jinchu et al. Current Differential Signal Extraction Algorithm via Fast-TD and Its Application in Open-Circuit Fault Diagnosis of Magnetic Bearings . | IEEE TRANSACTIONS ON INSTRUMENTATION AND MEASUREMENT , 2025 , 74 . |
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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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Abstract ：
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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To address the strong decoupling between pressure and temperature variables in the intake environment simulation system （IESS） of altitude test facility， as well as the significant total disturbance caused by rapid transient tests， a novel fixed time sliding mode controller （FxTSMC） with a fixed time extended state observer （FxTESO） was designed， and thus， a fixed time active disturbance rejection compound decoupling control method （FxT-ADRCDC） was proposed. Specifically， a static decoupling method was adopted to decouple the IESS into two single-input， single-output systems， achieving independent control of intake temperature and pressure. In terms of total disturbance estimation and suppression， the FxTESO was utilized to rapidly and accurately estimate the states and total disturbances including dynamic coupling to deal with the strong disturbance， and then， a novel FxTSMC that can avoid singular problems and converge rapidly was proposed， the total disturbance was then compensated into the FxTSMC， obtaining the FxT-ADRCDC method. The Lyapunov function was designed to prove the fixed time stability of the closed-loop control system， obtaining the upper bound of the settling time， which does not depend on the initial conditions. Finally， the transient flight mission experiments on a high-confidence IESS platform were launched and the comparisons between the FxT-ADRCDC method and the linear active disturbance rejection decoupling control （LADRDC） method were carried out. The results show that the absolute integral error of intake pressure and temperature under the FxT-ADRCDC is， on average， reduced by approximately 70.3% and 70.7%， respectively， compared to the LADRDC method. Moreover， the valve swing satisfies the requirements for practical engineering. The proposed method effectively achieves high-quality decoupling control of intake pressure and temperature， and provides strong technical support for improving the system’s rapid and accurate dynamic modelling capabilities. © 2025 China Aerospace Science and Industry Corp. All rights reserved.
Keyword ：
Closed loop control systems Closed loop control systems Disturbance rejection Disturbance rejection Linear control systems Linear control systems State estimation State estimation
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| GB/T 7714 | Xu, Zhouzhe , Zhang, Hehong , Zhai, Chao et al. Fixed time active disturbance rejection compound decoupling control method for intake environment simulation system of altitude test facility [J]. | Journal of Propulsion Technology , 2025 , 46 (2) . |
| MLA | Xu, Zhouzhe et al. "Fixed time active disturbance rejection compound decoupling control method for intake environment simulation system of altitude test facility" . | Journal of Propulsion Technology 46 . 2 (2025) . |
| APA | Xu, Zhouzhe , Zhang, Hehong , Zhai, Chao , Qian, Qiumeng , Wu, Linfeng . Fixed time active disturbance rejection compound decoupling control method for intake environment simulation system of altitude test facility . | Journal of Propulsion Technology , 2025 , 46 (2) . |
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随着微电网和虚拟电厂等分布式能源管理方式的变革,大量的分布式能源给电力系统的运营商带来了技术挑战并且增大了管理复杂度.一个可控分布式能源的聚合运行模型,可以方便高效地管理大量的分布式能源.本质上,聚合运行模型的可行域是所有分布式能源的多面体可行域的Minkowski和.然而,两个任意多面体的Minkowski和的计算是一个不确定的多项式时间难题.为了精确地刻画并提高大量分布式能源的聚合灵活性,首先,本文提出一种通用的凸约束空间中的Minkowski和计算方法.采用离散点集的凸包逼近真实约束空间,再使用Minkowski和对离散点集进行叠加,并提出离散点集优化算法,使其尽可能地逼近真实约束空间.这种点集是高维度、抽象的,但却表征了分布式能源的运行特征,我们将其定义为特征点集.然后,提出了一种特征点集的选取规则,能够提高调度灵活性,增加调峰能力并减少Minkowski和的运算复杂度.此外,提出一种简化特征点集的算法并且保证了不损失约束空间.最后,从理论上阐释了特征点集法在电网调度中的合理性.数值仿真结果表明,该方法在提高系统聚合灵活性和计算效率方面具有很大潜力.
Keyword ：
Minkowski和 Minkowski和 内近似 内近似 凸包 凸包 分布式能源 分布式能源 特征点集 特征点集 聚合和分解 聚合和分解
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| GB/T 7714 | 樊鹏阳 , 翟超 , 何宇俊 et al. 基于特征点集的分布式能源调度灵活性聚合方法 [J]. | 中国科学（信息科学） , 2025 , 55 (2) : 372-387 . |
| MLA | 樊鹏阳 et al. "基于特征点集的分布式能源调度灵活性聚合方法" . | 中国科学（信息科学） 55 . 2 (2025) : 372-387 . |
| APA | 樊鹏阳 , 翟超 , 何宇俊 , 刘沅昆 , 张和洪 . 基于特征点集的分布式能源调度灵活性聚合方法 . | 中国科学（信息科学） , 2025 , 55 (2) , 372-387 . |
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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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This paper presents an interactive motion control method based on reinforcement learning, designed to assist children with autism who have social motor impairments through a mirror game intervention. The virtual teacher uses the Deep Deterministic Policy Gradient (DDPG) algorithm to optimize its actions, guiding the participant to follow a Lissajous trajectory. To ensure safety, a motion-correction mechanism was developed, which automatically adjusts actions when the predicted trajectory surpasses predefined safety boundaries. The reward function considers both the distance between the virtual teacher and the target trajectory, as well as the distance between the virtual teacher and the participant, with dynamic adjustments applied by the motion-correction mechanism. Experimental results demonstrate that the virtual teacher effectively guides the participant towards the target trajectory while adhering to safety constraints. © 2025 IEEE.
Keyword ：
Engineering education Engineering education Reinforcement learning Reinforcement learning Teaching Teaching
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| GB/T 7714 | Yang, Fan , Huang, Yuening , Zhai, Chao et al. Safe Reinforcement Learning for Social Motor Coordination in Two Dimensional Space [C] . 2025 . |
| MLA | Yang, Fan et al. "Safe Reinforcement Learning for Social Motor Coordination in Two Dimensional Space" . (2025) . |
| APA | Yang, Fan , Huang, Yuening , Zhai, Chao , Zhang, Hehong . Safe Reinforcement Learning for Social Motor Coordination in Two Dimensional Space . (2025) . |
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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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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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