Pub Date : 2010-06-08DOI: 10.1109/ISSCAA.2010.5632900
Dan Wang, Zhi Xiong, Fang Chen, Jian-ye Liu
The error of the inertia navigation system can be modulated critically by using the real-time SAR image through image matching and positioning. The mismatching points are inevitable in the SAR aided navigation. In the integrated navigation, the measurement outliers will affect the filter seriously. In order to eliminate the effect of the mismatching points, combining the discontinuous working characteristics of the SAR image matching navigation, the paper proposes the image mismatching points eliminating arithmetic and the integrated navigation arithmetic. We found the mathematical models of the INS/SAR integrated navigation system which has the discontinuous working characteristics. And basing on the Kalman filtering information we design the arithmetic to eliminate and displace the image mismatching points. The simulation indicates the arithmetic proposed in this paper can eliminate and displace the image mismatching points availably and consequently improves the accuracy of the integrated navigation greatly.
{"title":"Research on the image mismatching points eliminating and the integrated arithmetic in the INS/SAR integrated navigation","authors":"Dan Wang, Zhi Xiong, Fang Chen, Jian-ye Liu","doi":"10.1109/ISSCAA.2010.5632900","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632900","url":null,"abstract":"The error of the inertia navigation system can be modulated critically by using the real-time SAR image through image matching and positioning. The mismatching points are inevitable in the SAR aided navigation. In the integrated navigation, the measurement outliers will affect the filter seriously. In order to eliminate the effect of the mismatching points, combining the discontinuous working characteristics of the SAR image matching navigation, the paper proposes the image mismatching points eliminating arithmetic and the integrated navigation arithmetic. We found the mathematical models of the INS/SAR integrated navigation system which has the discontinuous working characteristics. And basing on the Kalman filtering information we design the arithmetic to eliminate and displace the image mismatching points. The simulation indicates the arithmetic proposed in this paper can eliminate and displace the image mismatching points availably and consequently improves the accuracy of the integrated navigation greatly.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"15 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124007609","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-06-08DOI: 10.1109/ISSCAA.2010.5633387
Xinxin Yang, Xiong Luo, F. Sun, Fengge Wu, Huaping Liu
In recent years, dynamics model and control of space robot system are the hot topics in the research field. In this paper, a new dynamics model and control strategy of space robotic system with a flexible manipulator and a liquid fuel tank are investigated. Based on Lagrange equation method, the dynamics model of the space robotic system coupling with liquid sloshing, flexibility vibration and base movement is derived. The elastic deflection of the flexible manipulator is described by the assumed mode method and equivalent mechanical model is adopted instead of liquid sloshing under the environment of low-gravity. The inverse dynamics control algorithm combined with PD control method is performed to solve the trajectory tracking problem. Some simulation results are given to verify the effectiveness of the proposed method.
{"title":"Dynamic modeling and tracking control of fuel filled space robotic system with flexible manipulators","authors":"Xinxin Yang, Xiong Luo, F. Sun, Fengge Wu, Huaping Liu","doi":"10.1109/ISSCAA.2010.5633387","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633387","url":null,"abstract":"In recent years, dynamics model and control of space robot system are the hot topics in the research field. In this paper, a new dynamics model and control strategy of space robotic system with a flexible manipulator and a liquid fuel tank are investigated. Based on Lagrange equation method, the dynamics model of the space robotic system coupling with liquid sloshing, flexibility vibration and base movement is derived. The elastic deflection of the flexible manipulator is described by the assumed mode method and equivalent mechanical model is adopted instead of liquid sloshing under the environment of low-gravity. The inverse dynamics control algorithm combined with PD control method is performed to solve the trajectory tracking problem. Some simulation results are given to verify the effectiveness of the proposed method.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"95 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122396011","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-06-08DOI: 10.1109/ISSCAA.2010.5633585
Kan Xie, Yu Liu
An aerodynamic study is presented for controlled canard configuration of a target unmanned air vehicle (TUAV) at cruise Mach number between 0.7 and 0.85, using a solid rocket motor as power. The analysis was focused on the longitudinal wind tunnel test data for learning complicated controlled canard-elements interactions and canard vortex behavior. The canard vortex interaction with tail wing of initial configuration concept with a NACA0012 canard and the improved configuration with a NACA0007 canard were reviewed and discussed. The experiments prove that the stability and control characteristics of whole TUAV are sensitive to the thickness of canard in transonic peed regime because of different canard vortex intensity and effect generated. The flight experiment shows that the final improved controlled canard configuration satisfies the request of the control system.
{"title":"An experimental study of controlled canard for a solid rocket motor based unmanned air vehicle","authors":"Kan Xie, Yu Liu","doi":"10.1109/ISSCAA.2010.5633585","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633585","url":null,"abstract":"An aerodynamic study is presented for controlled canard configuration of a target unmanned air vehicle (TUAV) at cruise Mach number between 0.7 and 0.85, using a solid rocket motor as power. The analysis was focused on the longitudinal wind tunnel test data for learning complicated controlled canard-elements interactions and canard vortex behavior. The canard vortex interaction with tail wing of initial configuration concept with a NACA0012 canard and the improved configuration with a NACA0007 canard were reviewed and discussed. The experiments prove that the stability and control characteristics of whole TUAV are sensitive to the thickness of canard in transonic peed regime because of different canard vortex intensity and effect generated. The flight experiment shows that the final improved controlled canard configuration satisfies the request of the control system.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"9 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128566100","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-06-08DOI: 10.1109/ISSCAA.2010.5632307
W. Liang, Zhenqing Wang, Pengcheng Lin
The existence of viscosity effect at the interface of double dissimilar materials has an important impact to the distribution of interface crack-tip field and the properties variety of the interface itself. The singular is considered in crack-tip, and the elastic-viscoplastic quasi-static propagating governing equations of double dissimilar materials at interface crack-tip field are established. The displacement potential function and boundary condition of interface crack-tip are introduced and the numerical analysis of rigid-elastic viscoplastic interface for mode III are worked out. The stress-strain fields are obtained at the crack-tip and the variations of solutions are discussed according to each parameter. The numerical results show that the viscosity effect is a main factor of interface propagating crack-tip field, and the interface crack-tip is a viscoplastic field that is governed by viscosity coefficient, Mach number and singular factor.
{"title":"The elastic-viscoplastic field near mode iii dynamic propagating crack-tip of interface in double dissimilar materials","authors":"W. Liang, Zhenqing Wang, Pengcheng Lin","doi":"10.1109/ISSCAA.2010.5632307","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632307","url":null,"abstract":"The existence of viscosity effect at the interface of double dissimilar materials has an important impact to the distribution of interface crack-tip field and the properties variety of the interface itself. The singular is considered in crack-tip, and the elastic-viscoplastic quasi-static propagating governing equations of double dissimilar materials at interface crack-tip field are established. The displacement potential function and boundary condition of interface crack-tip are introduced and the numerical analysis of rigid-elastic viscoplastic interface for mode III are worked out. The stress-strain fields are obtained at the crack-tip and the variations of solutions are discussed according to each parameter. The numerical results show that the viscosity effect is a main factor of interface propagating crack-tip field, and the interface crack-tip is a viscoplastic field that is governed by viscosity coefficient, Mach number and singular factor.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"8 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130722464","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-06-08DOI: 10.1109/ISSCAA.2010.5633417
Fuhai Zhang, Yili Fu, Shibo Yan, Shuguo Wang
In recent years, research on space robotics has attracted considerable attention. Kinematics of the free-flying or free-floating space manipulator system, including a spacecraft and a manipulator mounted on the spacecraft, is a significant problem. In free-floating work mode, the spacecraft will move freely in response to the disturbances caused by the manipulator motions. From the view of application, change of the spacecraft attitude for the space manipulator system is not desirable. Therefore, it is of significance to adopt the free-floating with zero-disturbance spacecraft attitude work mode. This paper presents an overview of the kinematics of the space manipulator system. Position and velocity kinematics solutions in three work modes are analyzed. The kinematics differences among the three work modes are formulated. The simulation results validate the effectiveness of the kinematics solutions in the three work modes.
{"title":"Kinematics and simulations of space manipulator in three work modes","authors":"Fuhai Zhang, Yili Fu, Shibo Yan, Shuguo Wang","doi":"10.1109/ISSCAA.2010.5633417","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633417","url":null,"abstract":"In recent years, research on space robotics has attracted considerable attention. Kinematics of the free-flying or free-floating space manipulator system, including a spacecraft and a manipulator mounted on the spacecraft, is a significant problem. In free-floating work mode, the spacecraft will move freely in response to the disturbances caused by the manipulator motions. From the view of application, change of the spacecraft attitude for the space manipulator system is not desirable. Therefore, it is of significance to adopt the free-floating with zero-disturbance spacecraft attitude work mode. This paper presents an overview of the kinematics of the space manipulator system. Position and velocity kinematics solutions in three work modes are analyzed. The kinematics differences among the three work modes are formulated. The simulation results validate the effectiveness of the kinematics solutions in the three work modes.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"22 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130449409","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-06-08DOI: 10.1109/ISSCAA.2010.5633386
Xin-sheng Wang, Lei Ma
The gyro and the infrared earth sensor (IES) are two kinds of important components in satellite attitude control system. A fault detection and isolation (FDI) approach based on observer and Kalman filter is presented. Firstly, the models of gyro and IES are discussed, and a virtual linear system of satellite pitch channel is constructed. Then, an observer for fault detection and a Kalman filter for fault isolation are designed. The observer could detect faults from IES and gyro, but the Kalman filter could only detect IES fault rather than sensitive to gyro fault. So, fault isolation method could be achieved via fault arbitration logic given in the paper. Lastly, computer simulations are finished on the condition of system health status (no faults), IES fault and gyro fault. The simulation results show that the proposed fault detection and isolation approach is correct and feasible.
{"title":"Fault detection and isolation for gyro and infrared earth sensor based on observer and filter","authors":"Xin-sheng Wang, Lei Ma","doi":"10.1109/ISSCAA.2010.5633386","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633386","url":null,"abstract":"The gyro and the infrared earth sensor (IES) are two kinds of important components in satellite attitude control system. A fault detection and isolation (FDI) approach based on observer and Kalman filter is presented. Firstly, the models of gyro and IES are discussed, and a virtual linear system of satellite pitch channel is constructed. Then, an observer for fault detection and a Kalman filter for fault isolation are designed. The observer could detect faults from IES and gyro, but the Kalman filter could only detect IES fault rather than sensitive to gyro fault. So, fault isolation method could be achieved via fault arbitration logic given in the paper. Lastly, computer simulations are finished on the condition of system health status (no faults), IES fault and gyro fault. The simulation results show that the proposed fault detection and isolation approach is correct and feasible.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"6 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129873644","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-06-08DOI: 10.1109/ISSCAA.2010.5633352
Hongbo Li, Y. Lu, Yun Zhang
A new method called track smooth filter(TSF), which improves the tracking quality of target track, is presented for the situation that the measuring data rate is low, the system feature and the target movement is complicated. Based on the spatial trace matching principle that the track made by the target motion is continual and smooth, simple and robust estimation models can be constructed by the regression analysis for the target kinematics process with unknown behavior. The state estimations of the target are obtained by the smooth filter so as to establish the target track. In applications on the experimental data, it is shown that the adaptability and the stability of the track filter are well.
{"title":"A method of target tracking based on spatial trace matching principle","authors":"Hongbo Li, Y. Lu, Yun Zhang","doi":"10.1109/ISSCAA.2010.5633352","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633352","url":null,"abstract":"A new method called track smooth filter(TSF), which improves the tracking quality of target track, is presented for the situation that the measuring data rate is low, the system feature and the target movement is complicated. Based on the spatial trace matching principle that the track made by the target motion is continual and smooth, simple and robust estimation models can be constructed by the regression analysis for the target kinematics process with unknown behavior. The state estimations of the target are obtained by the smooth filter so as to establish the target track. In applications on the experimental data, it is shown that the adaptability and the stability of the track filter are well.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"11 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125886138","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-06-08DOI: 10.1109/ISSCAA.2010.5633239
Xiao-fang Wang, Hai Lin
Probability of penetration of image guided missile can increase greatly if the missile does terminal maneuver, but the terminal maneuver may have effects on target searching of missile. To study the effect the centroid model of missile doing typical terminal weaving maneuver was built and the model of target movement and parallel search law were built too. Based on the models the effect of terminal weaving maneuver on search area, movement speed of image on monitor screen and the probability of target entering the IFOV of seeker were analyzed through simulation. Simulation results show the effect on target searching of terminal weaving maneuver is little when image guided missile attacks the target with low velocity, which provides important reference for overall design of missile.
{"title":"Research on effect on target searching of image guided missile's terminal maneuver","authors":"Xiao-fang Wang, Hai Lin","doi":"10.1109/ISSCAA.2010.5633239","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633239","url":null,"abstract":"Probability of penetration of image guided missile can increase greatly if the missile does terminal maneuver, but the terminal maneuver may have effects on target searching of missile. To study the effect the centroid model of missile doing typical terminal weaving maneuver was built and the model of target movement and parallel search law were built too. Based on the models the effect of terminal weaving maneuver on search area, movement speed of image on monitor screen and the probability of target entering the IFOV of seeker were analyzed through simulation. Simulation results show the effect on target searching of terminal weaving maneuver is little when image guided missile attacks the target with low velocity, which provides important reference for overall design of missile.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"136 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122454658","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-06-08DOI: 10.1109/ISSCAA.2010.5632731
Shuanghe Yu, Zhenqiang Yang, Siyuan Wang, Kai Zheng
This paper proposes a novel sensorless speed tracking control scheme for the permanent magnet synchronous motors (PMSM) with uncertain parameters. An angular speed observer is designed to achieve the purpose of sensorless speed estimation, and then a speed tracking controller is developed with the adaptive backstepping technique to deal with the parameter uncertainties and load variation in the PMSM system. The stability of the whole closed loop system is guaranteed under Lyapunov criterion. Performance of proposed controller is investigated under different dynamic operating conditions such as step changes in commands, step changes in load, and parameter variations. The results indicate the effectiveness of the scheme in terms of the speed tracking ability and robustness against parameter variations.
{"title":"Sensorless adaptive backstepping speed tracking control of uncertain permanent magnet synchronous motors","authors":"Shuanghe Yu, Zhenqiang Yang, Siyuan Wang, Kai Zheng","doi":"10.1109/ISSCAA.2010.5632731","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632731","url":null,"abstract":"This paper proposes a novel sensorless speed tracking control scheme for the permanent magnet synchronous motors (PMSM) with uncertain parameters. An angular speed observer is designed to achieve the purpose of sensorless speed estimation, and then a speed tracking controller is developed with the adaptive backstepping technique to deal with the parameter uncertainties and load variation in the PMSM system. The stability of the whole closed loop system is guaranteed under Lyapunov criterion. Performance of proposed controller is investigated under different dynamic operating conditions such as step changes in commands, step changes in load, and parameter variations. The results indicate the effectiveness of the scheme in terms of the speed tracking ability and robustness against parameter variations.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"7 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126955716","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-06-08DOI: 10.1109/ISSCAA.2010.5633299
Wanli Zhang, Changhong Wang, Baomin Feng
Using aerodynamic force to finish the orbital transfer mission can save a lot of fuels and increase the payload. In this paper, After giving the mathematical description of the Aero-assisted Orbital Transfer(AOT) problem, we discrete it through the Guess-pseudospectral method and then apply SNOPT algorithm to get the optimal state trajectory. After that we do some simplify to original dynamic equations and design a real-time closed-Loop state feedback guidance law. About the singularity issue of the control variable, we give an effective method to deal with it. Though the comparison of this closed-loop guidance law with the Matched Asymptotic Expansion(MAE) predictor-corrector method, this method can save a lot of calculation quantity and have some improvement in its guidance performance, Simulation result shows that even when the external parameter vary, guidance trajectory can still track the optimal trajectory perfectly, so it has an excellent robustness.
{"title":"Trajectory optimization and closed-Loop guidance law design of Aero-assisted Orbital Transfer problem","authors":"Wanli Zhang, Changhong Wang, Baomin Feng","doi":"10.1109/ISSCAA.2010.5633299","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633299","url":null,"abstract":"Using aerodynamic force to finish the orbital transfer mission can save a lot of fuels and increase the payload. In this paper, After giving the mathematical description of the Aero-assisted Orbital Transfer(AOT) problem, we discrete it through the Guess-pseudospectral method and then apply SNOPT algorithm to get the optimal state trajectory. After that we do some simplify to original dynamic equations and design a real-time closed-Loop state feedback guidance law. About the singularity issue of the control variable, we give an effective method to deal with it. Though the comparison of this closed-loop guidance law with the Matched Asymptotic Expansion(MAE) predictor-corrector method, this method can save a lot of calculation quantity and have some improvement in its guidance performance, Simulation result shows that even when the external parameter vary, guidance trajectory can still track the optimal trajectory perfectly, so it has an excellent robustness.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"172 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133013103","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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