Pub Date : 2016-08-01DOI: 10.1109/CGNCC.2016.7829010
Xianchao Ma, Xiong Zheng-hu, Wang Jie, She Cai-yun, Wang Jia
Due to the defects of the long time accumulation method often used now, a new parallel PSO tracking algorithm based on Multi-core Digital Signal Processing (DSP) parallel system was proposed which greatly reduced the calculation cost and complexity, compensated the target accurately and enhanced the real-time processing. A total of three flights experiment was carried out. Every time both the conventional 10ms accumulation method and parallel PSO tracking method were adopted to track the target at the same time. The experiment results showed that the parallel PSO tracking algorithm was tracking the target with less computable complexity and more effective real-time performance.
{"title":"Design and implementation of long-time coherent integration algorithm based on Multi-Core DSP","authors":"Xianchao Ma, Xiong Zheng-hu, Wang Jie, She Cai-yun, Wang Jia","doi":"10.1109/CGNCC.2016.7829010","DOIUrl":"https://doi.org/10.1109/CGNCC.2016.7829010","url":null,"abstract":"Due to the defects of the long time accumulation method often used now, a new parallel PSO tracking algorithm based on Multi-core Digital Signal Processing (DSP) parallel system was proposed which greatly reduced the calculation cost and complexity, compensated the target accurately and enhanced the real-time processing. A total of three flights experiment was carried out. Every time both the conventional 10ms accumulation method and parallel PSO tracking method were adopted to track the target at the same time. The experiment results showed that the parallel PSO tracking algorithm was tracking the target with less computable complexity and more effective real-time performance.","PeriodicalId":426650,"journal":{"name":"2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC)","volume":"176 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-08-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134253540","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 : 2016-08-01DOI: 10.1109/CGNCC.2016.7828866
Zhao Saifeng, Li Xiujuan, Lin Chuntao
In this paper, a partition method for envelope based on fuzzy clustering is designed to obtain the typical operating points as well as the interpolation mechanism of gain scheduling according to the comparability of the dynamic characteristics and the maneuverability in some partial flight regions. In order to get the most reasonable partition result, the index of clustering evaluation is chosen which divides the flight envelope into several sub envelope with similar characteristics. This approach provides the basis for gain scheduling and reduces the difficulty of the design of the flight control law at the same time.
{"title":"A partition method for UAV's envelope based on fuzzy clustering","authors":"Zhao Saifeng, Li Xiujuan, Lin Chuntao","doi":"10.1109/CGNCC.2016.7828866","DOIUrl":"https://doi.org/10.1109/CGNCC.2016.7828866","url":null,"abstract":"In this paper, a partition method for envelope based on fuzzy clustering is designed to obtain the typical operating points as well as the interpolation mechanism of gain scheduling according to the comparability of the dynamic characteristics and the maneuverability in some partial flight regions. In order to get the most reasonable partition result, the index of clustering evaluation is chosen which divides the flight envelope into several sub envelope with similar characteristics. This approach provides the basis for gain scheduling and reduces the difficulty of the design of the flight control law at the same time.","PeriodicalId":426650,"journal":{"name":"2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC)","volume":"160 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-08-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134348902","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 : 2016-08-01DOI: 10.1109/CGNCC.2016.7829138
B. Khouane, Chao Han, Yukai Zhu
In this paper, a disturbance-observer-based composite attitude controller is proposed for attitude control and stabilization of flexible spacecraft. This approach is composed of two parts. First, a disturbance observer is designed to estimate the disturbance from the flexible appendages. Solving Linear Matrix Inequality (LMI) helps to determine the design parameters of disturbance observer based control (DOBC). Subsequently, an integral sliding mode controller (ISMC) is used to address other kinds of disturbances, such as space environmental disturbance torques, unmolded uncertainties, and noises from actuators and sensors. Simulation results are provided to verify the effectiveness of the proposed control scheme.
{"title":"Disturbance observer based composite attitude stabilization of flexible spacecraft","authors":"B. Khouane, Chao Han, Yukai Zhu","doi":"10.1109/CGNCC.2016.7829138","DOIUrl":"https://doi.org/10.1109/CGNCC.2016.7829138","url":null,"abstract":"In this paper, a disturbance-observer-based composite attitude controller is proposed for attitude control and stabilization of flexible spacecraft. This approach is composed of two parts. First, a disturbance observer is designed to estimate the disturbance from the flexible appendages. Solving Linear Matrix Inequality (LMI) helps to determine the design parameters of disturbance observer based control (DOBC). Subsequently, an integral sliding mode controller (ISMC) is used to address other kinds of disturbances, such as space environmental disturbance torques, unmolded uncertainties, and noises from actuators and sensors. Simulation results are provided to verify the effectiveness of the proposed control scheme.","PeriodicalId":426650,"journal":{"name":"2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC)","volume":"41 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-08-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130848636","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 : 2016-08-01DOI: 10.1109/CGNCC.2016.7828865
Tai-shan Lou, Jie Liu, P. Jin
An innovative integrated navigation scheme based on norm-constrained Unscented Kalman filter (NCUKF) for the spacecraft attitude quaternion estimation during Mars powered descent is proposed. The norm equality constraints are introduced into the Joseph formula to reconstruct a new constraint cost function of the Unscented Kalman filter. Based on the Miniature Coherent Altimeter and Velocimeter and radio communications between the vehicle and beacons, new measurements are introduced into the navigation systems during Mars powered descent. A numerical simulation has been carried out to estimate the positions, velocities and attitudes of the vehicle, and the performance of the proposed NCUKF is demonstrated.
{"title":"An innovative integrated navigation based on norm-constrained UKF during Mars powered descent","authors":"Tai-shan Lou, Jie Liu, P. Jin","doi":"10.1109/CGNCC.2016.7828865","DOIUrl":"https://doi.org/10.1109/CGNCC.2016.7828865","url":null,"abstract":"An innovative integrated navigation scheme based on norm-constrained Unscented Kalman filter (NCUKF) for the spacecraft attitude quaternion estimation during Mars powered descent is proposed. The norm equality constraints are introduced into the Joseph formula to reconstruct a new constraint cost function of the Unscented Kalman filter. Based on the Miniature Coherent Altimeter and Velocimeter and radio communications between the vehicle and beacons, new measurements are introduced into the navigation systems during Mars powered descent. A numerical simulation has been carried out to estimate the positions, velocities and attitudes of the vehicle, and the performance of the proposed NCUKF is demonstrated.","PeriodicalId":426650,"journal":{"name":"2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC)","volume":"153 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-08-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131039079","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 : 2016-08-01DOI: 10.1109/CGNCC.2016.7828770
Changhao Chen, Ze Chen, Xianfei Pan, Xiaoping Hu
a design of pedestrian navigation system based on EKF+ZUPT+SINS is proposed in this study. Three different zero-velocity detectors are assessed by the position accuracy which is calculated through PNS with different choices of detectors and parameters. In order to show the algorithm performance and the influence of zero-velocity detectors on the whole system, the generated pedestrian trajectories fusing the information of MIMU are illustrated. The final results show that a position accuracy of 0.39% in 10 minutes can be achieved and the detectors using the information of gyroscope signals such as SHOE Detector prove to be more reliable to detect the time epochs when MIMU is stationary. Through the experiments conducted in outdoor and indoor environments, the proposed algorithm proves to be efficient.
{"title":"Assessment of zero-velocity detectors for pedestrian navigation system using MIMU","authors":"Changhao Chen, Ze Chen, Xianfei Pan, Xiaoping Hu","doi":"10.1109/CGNCC.2016.7828770","DOIUrl":"https://doi.org/10.1109/CGNCC.2016.7828770","url":null,"abstract":"a design of pedestrian navigation system based on EKF+ZUPT+SINS is proposed in this study. Three different zero-velocity detectors are assessed by the position accuracy which is calculated through PNS with different choices of detectors and parameters. In order to show the algorithm performance and the influence of zero-velocity detectors on the whole system, the generated pedestrian trajectories fusing the information of MIMU are illustrated. The final results show that a position accuracy of 0.39% in 10 minutes can be achieved and the detectors using the information of gyroscope signals such as SHOE Detector prove to be more reliable to detect the time epochs when MIMU is stationary. Through the experiments conducted in outdoor and indoor environments, the proposed algorithm proves to be efficient.","PeriodicalId":426650,"journal":{"name":"2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC)","volume":"25 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-08-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132889153","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 : 2016-08-01DOI: 10.1109/CGNCC.2016.7828969
Shugui Kang, Xia Zhao, Fu Chen
The problems of stability analysis and controller design for discrete-time periodic nonlinear quadratic systems are investigated. Firstly, by using Lyapunov function and the concept of periodic invariant set, a sufficient condition for guaranteeing that the assigned polytope belongs to the domain of attraction of the zero equilibrium point. Secondly, it is also show that this problem is related to the problem of finding a state feedback law and an admissible initial condition domain such that the resulting closed-loop system is asymptotic stability for every initial condition from the admissible domain. The proposed algorithm requires the solution of a suitable feasibility problem involving linear matrix inequalities constraints. Finally, two simulation examples are presented to show the effectiveness of the proposed approach.
{"title":"Stability analysis and controller design for discrete-time periodic nonlinear quadratic systems","authors":"Shugui Kang, Xia Zhao, Fu Chen","doi":"10.1109/CGNCC.2016.7828969","DOIUrl":"https://doi.org/10.1109/CGNCC.2016.7828969","url":null,"abstract":"The problems of stability analysis and controller design for discrete-time periodic nonlinear quadratic systems are investigated. Firstly, by using Lyapunov function and the concept of periodic invariant set, a sufficient condition for guaranteeing that the assigned polytope belongs to the domain of attraction of the zero equilibrium point. Secondly, it is also show that this problem is related to the problem of finding a state feedback law and an admissible initial condition domain such that the resulting closed-loop system is asymptotic stability for every initial condition from the admissible domain. The proposed algorithm requires the solution of a suitable feasibility problem involving linear matrix inequalities constraints. Finally, two simulation examples are presented to show the effectiveness of the proposed approach.","PeriodicalId":426650,"journal":{"name":"2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC)","volume":"6 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-08-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133608100","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 : 2016-08-01DOI: 10.1109/CGNCC.2016.7829057
Guanfeng Yu, Guofeng Zhang
The work presented in this paper focuses on real-time simulation of the airborne forward looking infrared (FLIR) sensor typically configured by modern helicopter. Based on infrared radiation theoretic model, the infrared transmittance model of “target-background-atmosphere-imaging system” is established. Furthermore, using modern computer graphics hardware, the detection signal is output in real time through the interacting of the virtual environment, which is the working process of sensors in actual infrared system. Simulation results shows that the platform can dynamically and efficiently generate realistic infrared images of helicopter varying with different simulation parameters. The dynamic simulation of large scale infrared scene can enhance the situational awareness for pilot.
{"title":"Real-time simulation of airborne FLIR sensor","authors":"Guanfeng Yu, Guofeng Zhang","doi":"10.1109/CGNCC.2016.7829057","DOIUrl":"https://doi.org/10.1109/CGNCC.2016.7829057","url":null,"abstract":"The work presented in this paper focuses on real-time simulation of the airborne forward looking infrared (FLIR) sensor typically configured by modern helicopter. Based on infrared radiation theoretic model, the infrared transmittance model of “target-background-atmosphere-imaging system” is established. Furthermore, using modern computer graphics hardware, the detection signal is output in real time through the interacting of the virtual environment, which is the working process of sensors in actual infrared system. Simulation results shows that the platform can dynamically and efficiently generate realistic infrared images of helicopter varying with different simulation parameters. The dynamic simulation of large scale infrared scene can enhance the situational awareness for pilot.","PeriodicalId":426650,"journal":{"name":"2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC)","volume":"263 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-08-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115204921","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 : 2016-08-01DOI: 10.1109/CGNCC.2016.7828791
Bingbo Cui, Haoqian Huang, Xiyuan Chen
An iterated filtering method is presented to improve the update stage of nonlinear filtering. First, we develop a generalized iterative framework for sigma point kalman filter by utilizing Gauss-Newton algorithm. A simplified iterated square root cubature kalman filter (SCKF) is proposed with application to tightly coupled GNSS/INS, where the linear combination of innovations is used in measurement update. Numerical experiment and field test results indicate that SCKF has similar performance with extended kalman filter. Compared with the non-iterated methods, iterated SCKF improves the heading by 23.6% with two iterations, and get a faster convergence rate regarding heading and velocity.
{"title":"Iterated square root cubature kalman filter with application to tightly coupled GNSS/INS","authors":"Bingbo Cui, Haoqian Huang, Xiyuan Chen","doi":"10.1109/CGNCC.2016.7828791","DOIUrl":"https://doi.org/10.1109/CGNCC.2016.7828791","url":null,"abstract":"An iterated filtering method is presented to improve the update stage of nonlinear filtering. First, we develop a generalized iterative framework for sigma point kalman filter by utilizing Gauss-Newton algorithm. A simplified iterated square root cubature kalman filter (SCKF) is proposed with application to tightly coupled GNSS/INS, where the linear combination of innovations is used in measurement update. Numerical experiment and field test results indicate that SCKF has similar performance with extended kalman filter. Compared with the non-iterated methods, iterated SCKF improves the heading by 23.6% with two iterations, and get a faster convergence rate regarding heading and velocity.","PeriodicalId":426650,"journal":{"name":"2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC)","volume":"3 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-08-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115688177","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 : 2016-08-01DOI: 10.1109/CGNCC.2016.7829127
Zhihan Zhou, Shaoping Wang, Xingjian Wang, Jun Wang
This paper presents an active fault tolerant control (AFTC) strategy for the more-electric aircraft suffering from total hydraulic loss. Based on linear quadratic regulator (LQR) and model reference control (MRC) method, the fault tolerant control law is reconfigured. A new model is adopted by regarding the control surfaces as independent ones. Without hydraulic power, the dissimilar redundant actuation system (DRAS) switches hydraulic actuators (HA) into electro-hydraulic actuator (EHA) to drive the control surfaces. Furthermore, by comparing different response performance of HA and EHA, the performance degradation is represented through the damaged aircraft model. Numerical simulation results validate the effectiveness of proposed AFTC strategy towards total hydraulic loss finally.
{"title":"LQR-MRC active fault tolerant control for more-electric aircraft without hydraulic power","authors":"Zhihan Zhou, Shaoping Wang, Xingjian Wang, Jun Wang","doi":"10.1109/CGNCC.2016.7829127","DOIUrl":"https://doi.org/10.1109/CGNCC.2016.7829127","url":null,"abstract":"This paper presents an active fault tolerant control (AFTC) strategy for the more-electric aircraft suffering from total hydraulic loss. Based on linear quadratic regulator (LQR) and model reference control (MRC) method, the fault tolerant control law is reconfigured. A new model is adopted by regarding the control surfaces as independent ones. Without hydraulic power, the dissimilar redundant actuation system (DRAS) switches hydraulic actuators (HA) into electro-hydraulic actuator (EHA) to drive the control surfaces. Furthermore, by comparing different response performance of HA and EHA, the performance degradation is represented through the damaged aircraft model. Numerical simulation results validate the effectiveness of proposed AFTC strategy towards total hydraulic loss finally.","PeriodicalId":426650,"journal":{"name":"2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC)","volume":"67 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-08-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115735645","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 : 2016-08-01DOI: 10.1109/CGNCC.2016.7828957
Yongxi Lyu, Weiguo Zhang, Jingping Shi, Xiaobo Qu, Jun Che
This paper focuses on the problems of unsteady aerodynamic modeling and flight control during post stall maneuver. Firstly, considering serious nonlinearity, coupling and hysteresis of aerodynamic force when advanced fighter aircraft doing post stall maneuver, we propose the strategy of using the extreme learning machine (ELM) method to model the unsteady aerodynamics and using dynamic inversion method to design the control law. Secondly, the angle of attack and sideslip angle and other states variables are obtained and selected as input variables based on wind tunnel test data. And coefficients of aerodynamics force are chosen as output variables. The wind tunnel data is divided into two groups: training samples and testing samples. Then ELM method is used to establish accurate unsteady aerodynamic model. The model accuracy is tested by the determination coefficient based on testing samples, which determines parameters of ELM. Thus problem of ignoring the unsteady aerodynamic in traditional control is avoided. After that, dynamic inversion method and daisy chain distribution method based the control law of advanced fighter are designed, and the alternative formula of reduced frequency is derived. Finally, compared with result of steady aerodynamic modeling, simulations of typical cobra maneuver by unsteady aerodynamics show significance of taking consideration of unsteady aerodynamic effect during the post stall maneuver.
{"title":"Post stall maneuver control of advanced fighter considering the unsteady aerodynamics","authors":"Yongxi Lyu, Weiguo Zhang, Jingping Shi, Xiaobo Qu, Jun Che","doi":"10.1109/CGNCC.2016.7828957","DOIUrl":"https://doi.org/10.1109/CGNCC.2016.7828957","url":null,"abstract":"This paper focuses on the problems of unsteady aerodynamic modeling and flight control during post stall maneuver. Firstly, considering serious nonlinearity, coupling and hysteresis of aerodynamic force when advanced fighter aircraft doing post stall maneuver, we propose the strategy of using the extreme learning machine (ELM) method to model the unsteady aerodynamics and using dynamic inversion method to design the control law. Secondly, the angle of attack and sideslip angle and other states variables are obtained and selected as input variables based on wind tunnel test data. And coefficients of aerodynamics force are chosen as output variables. The wind tunnel data is divided into two groups: training samples and testing samples. Then ELM method is used to establish accurate unsteady aerodynamic model. The model accuracy is tested by the determination coefficient based on testing samples, which determines parameters of ELM. Thus problem of ignoring the unsteady aerodynamic in traditional control is avoided. After that, dynamic inversion method and daisy chain distribution method based the control law of advanced fighter are designed, and the alternative formula of reduced frequency is derived. Finally, compared with result of steady aerodynamic modeling, simulations of typical cobra maneuver by unsteady aerodynamics show significance of taking consideration of unsteady aerodynamic effect during the post stall maneuver.","PeriodicalId":426650,"journal":{"name":"2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC)","volume":"8 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-08-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124230266","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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