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Aeroengine thrust estimation and embedded verification based on improved temporal convolutional network

Chinese Journal of Aeronautics 2024年第1期37卷 106-117页

作者： Wanzhi MENG Zhuorui PAN Sixin WEN Pan QIN Ximing SUN Key Laboratory of Intelligent Control and Optimization for Industrial Equipment of Ministry of Education Dalian University of TechnologyDalian 116024China School of Control Science and Engineering Dalian University of TechnologyDalian 116024China

thrust estimation is a significant part of aeroengine thrust control *** traditional estimation methods are either low in accuracy or large in *** further improve the estimation effect,a thrust estimator based on Multi-layer Residual Temporal Convolutional Network(M-RTCN)is *** solve the problem of dead Rectified Linear Unit(ReLU),the proposed method uses the Gaussian Error Linear Unit(GELU)activation function instead of ReLU in residual *** the overall architecture of the multi-layer convolutional network is adjusted by using residual connections,so that the network thrust estimation effect and memory consumption are further ***,the comparison with seven other methods shows that the proposed method has the advantages of higher estimation accuracy and faster convergence ***,six neural network models are deployed in the embedded controller of the micro-turbojet *** Hardware-in-the-Loop(HIL)testing results demonstrate the superiority of M-RTCN in terms of estimation accuracy,memory occupation and running ***,an ignition verification is conducted to confirm the expected thrust estimation and real-time performance.

关键词： thrust estimation Temporal convolutional network Embedded deployment Hardware-in-the-loop testing Ignition verification

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thrust estimate method of an on-orbit Hall thruster using Hall drift current

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Plasma Science and Technology 2024年第12期26卷 150-159页

作者： Ziying REN Liqiu WEI Zexin LIU Yanlin HU Liang HAN Hong LI Yongjie DING Xiufeng ZHONG School of Energy Science and Engineering Harbin Institute of TechnologyHarbin 150001People’s Republic of China Chang Guang Satellite Technology Co. Ltd.Changchun 130000People’s Republic of China Beijing Institute of Control Engineering Beijing 100190People’s Republic of China Beijing SunWise Space Technology Ltd. Beijing 101300People’s Republic of China

In order to realize the thrust estimation of the Hall thruster during its flight mission,this study establishes an estimation method based on measurement of the Hall drift *** this method,the Hall drift current is calculated from an inverse magnetostatic problem,which is formulated according to its induced magnetic flux density detected by sensors,and then the thrust is estimated by multiplying the Hall drift current with the characteristic magnetic flux density of the thruster *** addition,a three-wire torsion pendulum micro-thrust measurement system is utilized to verify the estimate values obtained from the proposed *** errors were found to be less than 8%when the discharge voltage ranged from 250 V to 350 V and the anode flow rate ranged from 30 sccm to 50 sccm,indicating the possibility that the proposed thrust estimate method could be practically ***,the measurement accuracy of the magnetic flux density is suggested to be lower than 0.015 mT and improvement on the inverse problem solution is required in the future.

关键词： thrust estimation Hall effect thruster Hall drift current inverse problem Tikhonov regularization

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