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学者姓名：张和洪
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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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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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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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高空舱进气环境压力模拟控制系统在发动机开展过渡态试验中存在强气流扰动及大量随机噪声干扰,为此,提出新型非线性状态误差反馈函数xal及在结构上引入总扰动状态变量反馈环节来设计扩张状态观测器算法(记作xal-ESO),并以此提出基于xal-ESO的高空舱进气环境压力模拟新型自抗扰控制方法.借助数值仿真对比所提出的xal-ESO与常见ESO在状态与总扰动方面的估计能力,结果表明xal-ESO能有效抑制系统输出噪声并取得较好的估计品质.基于系统核心设备模型搭建高空舱进气环境压力模拟仿真平台并进行工程试验,对比了基于xal-ESO的自抗扰控制与当前工程中使用的线性自抗扰控制的进气环境压力控制效果,试验结果显示线性自抗扰控制方法受噪声影响明显,而所提出的新型自抗扰控制方法在发动机过渡态试验中跟踪进气压力时超调量降低了58.70%,稳态误差降低了95.71%,表明该方法能够有效提升高空舱进气环境压力模拟效果,提升发动机过渡态性能评价的准确性.
Keyword ：
压力模拟 压力模拟 扩张状态观测器 扩张状态观测器 自抗扰控制 自抗扰控制 过渡态试验 过渡态试验 非线性状态误差反馈 非线性状态误差反馈 高空舱 高空舱
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| GB/T 7714 | 李婉如 , 张和洪 , 王鹏 et al. 高空舱进气环境压力模拟新型自抗扰控制 [J]. | 推进技术 , 2024 , 45 (8) : 246-256 . |
| MLA | 李婉如 et al. "高空舱进气环境压力模拟新型自抗扰控制" . | 推进技术 45 . 8 (2024) : 246-256 . |
| APA | 李婉如 , 张和洪 , 王鹏 , 翟超 , 张松 , 但志宏 et al. 高空舱进气环境压力模拟新型自抗扰控制 . | 推进技术 , 2024 , 45 (8) , 246-256 . |
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针对航空发动机高空环境模拟过渡态试验对高空舱进气环境压力模拟系统提出的强抗扰性、强鲁棒性等控制综合品质要求,设计了一种基于鲁棒模型预测控制(Robust Model Predictive Control,RMPC)的高空舱进气环境压力控制方法.RMPC采用滚动时域优化和扰动反馈补偿的方法,在预测控制框架内处理模型的不确定性.通过建立进气环境压力模拟系统设备特性模型,设计了基于RMPC的进气环境压力控制 策略,搭建了仿真平台,与线性自抗扰控制(Linear Active Disturbance Rejection Control,LADRC)方法进行了对比分析.仿真结果表明,应用RMPC技术后,动态调节时间由7.68 s缩短至3.91 s,最大瞬时波动量由0.94％减小至0.25％,该技术能够大幅提高发动机高空环境模拟过渡态试验中进气环境压力模拟的动态响应速度、控制精度和抗扰能力.
Keyword ：
压力模拟 压力模拟 最优控制 最优控制 过渡态试验 过渡态试验 高空舱 高空舱 鲁棒模型预测控制 鲁棒模型预测控制
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| GB/T 7714 | 林珏 , 张和洪 , 但志宏 et al. 高空舱进气环境压力模拟鲁棒模型预测控制 [J]. | 测控技术 , 2024 , 43 (8) : 64-71 . |
| MLA | 林珏 et al. "高空舱进气环境压力模拟鲁棒模型预测控制" . | 测控技术 43 . 8 (2024) : 64-71 . |
| APA | 林珏 , 张和洪 , 但志宏 , 吴珊珊 , 徐莹莹 , 翟超 . 高空舱进气环境压力模拟鲁棒模型预测控制 . | 测控技术 , 2024 , 43 (8) , 64-71 . |
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针对航空发动机高空舱飞行高度模拟控制系统存在的强非线性、高度不确定性、强外部扰动等实际工程问题，对抑制系统不确定性影响的主要控制方法进行了分析和讨论，设计了一种基于降阶线性扩张状态观测器（RLESO）的串级线性自抗扰（LADRC）鲁棒控制方法。分析了被控对象的主要特性和控制难点，并将广义受控对象分为蝶阀位置回路和飞行高度回路。对两个回路分别设计降阶扩张状态观测器和控制器并组建串级控制系统。通过控制仿真并与经典PID控制方法进行了对比分析，结果显示在推力瞬变试验控制仿真中，被控压力的最大波动值从3.5 kPa减小至0.8 kPa，表明了基于RLESO的串级LADRC技术能够显著提升高空台飞行高度模拟的控制品质，获得了较为理想的鲁棒控制性能和抗扰性能。
Keyword ：
线性自抗扰控制器 线性自抗扰控制器 降阶线性扩张状态观测器 降阶线性扩张状态观测器 飞行高度模拟 飞行高度模拟 高空舱 高空舱 鲁棒性 鲁棒性
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| GB/T 7714 | 但志宏 , 张松 , 张和洪 et al. 高空舱飞行高度模拟串级LADRC鲁棒控制技术 [J]. | 航空动力学报 , 2024 , 39 (04) : 284-293 . |
| MLA | 但志宏 et al. "高空舱飞行高度模拟串级LADRC鲁棒控制技术" . | 航空动力学报 39 . 04 (2024) : 284-293 . |
| APA | 但志宏 , 张松 , 张和洪 , 钱秋朦 , 王信 , 赵伟 . 高空舱飞行高度模拟串级LADRC鲁棒控制技术 . | 航空动力学报 , 2024 , 39 (04) , 284-293 . |
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针对机载惯性稳定平台电磁轴承的体积、质量较大，电磁场和温度场同时运算的双向耦合法研究较少的问题，提出一种轻量化、大承载磁悬浮机载惯性稳定平台电磁轴承的总体方案，设计了三点式单导磁环电磁轴承支承方式，采用有限元法完成该系统电磁性能的仿真分析，并对结构强度进行校核，完成电磁场和温度场单向、双向耦合的温度场分析。结果表明，电磁轴承性能满足设计要求，磁热双向耦合分析得到的温度分布更符合实际情况，自然空冷的方式能保证系统安全运行。
Keyword ：
有限元分析 有限元分析 温度场 温度场 滑动轴承 滑动轴承 磁力轴承 磁力轴承 稳定平台 稳定平台
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| GB/T 7714 | 赵巍龙 , 张志洲 , 李优 et al. 轻量型机载惯性稳定平台电磁轴承性能与温度场仿真分析 [J]. | 轴承 , 2024 , PageCount-页数: 8 (07) : 115-121,137 . |
| MLA | 赵巍龙 et al. "轻量型机载惯性稳定平台电磁轴承性能与温度场仿真分析" . | 轴承 PageCount-页数: 8 . 07 (2024) : 115-121,137 . |
| APA | 赵巍龙 , 张志洲 , 李优 , 潘月亮 , 张和洪 . 轻量型机载惯性稳定平台电磁轴承性能与温度场仿真分析 . | 轴承 , 2024 , PageCount-页数: 8 (07) , 115-121,137 . |
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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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