Pub Date : 2016-08-01DOI: 10.1109/CGNCC.2016.7829034
L. Yongguang, Hu Hui, Zhang Hengzhen
In ultra-low temperature environment, the mechanical properties of bearing rotating in high speed change a lot, which has a great influence on the operation of machinery. To test the fatigue properties of air bearing, a hydraulic servo loading system for high-speed bearing in ultra-low temperature is designed and analyzed. According to the requirements of loading environment, this paper first designs a hydraulic servo loading system which could overcome the influence of high frequency disturbance. Then the components are selected with the related parameters in the hydraulic system calculated. Finally the simulation and analysis of the hydraulic system are carried out to verify the feasibility of the design by the AMESim software. All the research results above could provide reference for tests of aerospace high-speed bearing and designs of some other relevant hydraulic systems.
{"title":"Analysis of hydraulic servo loading system for high-speed bearing in ultra-low temperature environment","authors":"L. Yongguang, Hu Hui, Zhang Hengzhen","doi":"10.1109/CGNCC.2016.7829034","DOIUrl":"https://doi.org/10.1109/CGNCC.2016.7829034","url":null,"abstract":"In ultra-low temperature environment, the mechanical properties of bearing rotating in high speed change a lot, which has a great influence on the operation of machinery. To test the fatigue properties of air bearing, a hydraulic servo loading system for high-speed bearing in ultra-low temperature is designed and analyzed. According to the requirements of loading environment, this paper first designs a hydraulic servo loading system which could overcome the influence of high frequency disturbance. Then the components are selected with the related parameters in the hydraulic system calculated. Finally the simulation and analysis of the hydraulic system are carried out to verify the feasibility of the design by the AMESim software. All the research results above could provide reference for tests of aerospace high-speed bearing and designs of some other relevant hydraulic systems.","PeriodicalId":426650,"journal":{"name":"2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC)","volume":"28 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":"131542303","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.2016.7828785
Xudong Liu, Lin Cheng, Qingzhen Zhang, Lingtong Jiang
This paper focuses on the hypersonic vehicle in consideration of oscillation and aerodynamic heating problems during reentry process, for trajectory optimization, penalty function method and ε level comparison are introduced for transforming the unconstrained waterweeds algorithm into constrained algorithm to solve multi-objective optimization problems, in which a novel and more precise criterion based on time-scales separation guidance for oscillation optimization is put forward indicating waterweeds algorithm to get a better optimal result. The algorithm transformed is successfully applied to trajectory design.
{"title":"Entry trajectory optimization for hypersonic vehicle based on time-scales separation guidance with waterweeds algorithm","authors":"Xudong Liu, Lin Cheng, Qingzhen Zhang, Lingtong Jiang","doi":"10.1109/CGNCC.2016.7828785","DOIUrl":"https://doi.org/10.1109/CGNCC.2016.7828785","url":null,"abstract":"This paper focuses on the hypersonic vehicle in consideration of oscillation and aerodynamic heating problems during reentry process, for trajectory optimization, penalty function method and ε level comparison are introduced for transforming the unconstrained waterweeds algorithm into constrained algorithm to solve multi-objective optimization problems, in which a novel and more precise criterion based on time-scales separation guidance for oscillation optimization is put forward indicating waterweeds algorithm to get a better optimal result. The algorithm transformed is successfully applied to trajectory design.","PeriodicalId":426650,"journal":{"name":"2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC)","volume":"5 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":"127702501","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.2016.7828781
Wu Qi, Wang Changqing, Li Aijun, Huang Bin
Near space vehicle (NSV) is a nonlinear, multivariable and strongly coupled system. During the arbitrary trajectory tracking of NSV, the employment of conventional sliding mode variable structure control often results in steady-state errors, if there is some certain external disturbance. In this paper, an integral sliding mode variable structure controller is designed to eliminate the steady state error. Since the inputs of most actuators are restricted, the control performance will deteriorate or fail when the control signals are input directly into the controlled object. Therefore, the saturation limit is introduced to the controller design process to limit the input. Finally the proposed control scheme is applied to the attitude motion mode of the NSV and the simulation results confirmed its effect.
{"title":"Integral sliding mode controller design for near space vehicle with input constraints","authors":"Wu Qi, Wang Changqing, Li Aijun, Huang Bin","doi":"10.1109/CGNCC.2016.7828781","DOIUrl":"https://doi.org/10.1109/CGNCC.2016.7828781","url":null,"abstract":"Near space vehicle (NSV) is a nonlinear, multivariable and strongly coupled system. During the arbitrary trajectory tracking of NSV, the employment of conventional sliding mode variable structure control often results in steady-state errors, if there is some certain external disturbance. In this paper, an integral sliding mode variable structure controller is designed to eliminate the steady state error. Since the inputs of most actuators are restricted, the control performance will deteriorate or fail when the control signals are input directly into the controlled object. Therefore, the saturation limit is introduced to the controller design process to limit the input. Finally the proposed control scheme is applied to the attitude motion mode of the NSV and the simulation results confirmed its effect.","PeriodicalId":426650,"journal":{"name":"2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC)","volume":"34 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":"127741693","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.2016.7828801
Xiaoqian Cheng, Ran Xin, Guoning Bao, D. Luo, Zhiming Guo, Liaoni Wu
This paper presents the linear modelling of the gyroplane by the parameters identificaton method using the flight test data of a gyroplane. In recent years, unique advantages of gyroplanes have just been discovered, making it valuable in military or civilian fields. The research about unmanned gyroplanes has been initiated recently. The difficulty, which greatly impedes the research of unmanned gyroplanes, is the nonexistence of dynamic model. To solve this problem, the aerodynamic parameters indentification, based on actual flight test data in the manned gyroplane, is required. In order to get aerodynamic parameters of the linear dynamic model of the gyroplane, flight synchronous acquisition system was designed and established. Repeated flight tests based on excitation signal 211, was conducted. Through operation excitation, sufficient information was obtained to estimate parameters. Equation error method in frequency-domain was used to identify gyroplane aerodynamic parameters. The fitting degree between the flight test data and the responses of identified model proves the reliability of the the identified model. The degree of dispersion of multiple identification results characterizes recognition accuracy. Finally, based on the analysis of object properties, control law design was then carried out and the transformation from manned to unmanned control of gyroplane was therefore completed.
{"title":"Parameters identification of gyroplane longitudinal/lateral model from flight test","authors":"Xiaoqian Cheng, Ran Xin, Guoning Bao, D. Luo, Zhiming Guo, Liaoni Wu","doi":"10.1109/CGNCC.2016.7828801","DOIUrl":"https://doi.org/10.1109/CGNCC.2016.7828801","url":null,"abstract":"This paper presents the linear modelling of the gyroplane by the parameters identificaton method using the flight test data of a gyroplane. In recent years, unique advantages of gyroplanes have just been discovered, making it valuable in military or civilian fields. The research about unmanned gyroplanes has been initiated recently. The difficulty, which greatly impedes the research of unmanned gyroplanes, is the nonexistence of dynamic model. To solve this problem, the aerodynamic parameters indentification, based on actual flight test data in the manned gyroplane, is required. In order to get aerodynamic parameters of the linear dynamic model of the gyroplane, flight synchronous acquisition system was designed and established. Repeated flight tests based on excitation signal 211, was conducted. Through operation excitation, sufficient information was obtained to estimate parameters. Equation error method in frequency-domain was used to identify gyroplane aerodynamic parameters. The fitting degree between the flight test data and the responses of identified model proves the reliability of the the identified model. The degree of dispersion of multiple identification results characterizes recognition accuracy. Finally, based on the analysis of object properties, control law design was then carried out and the transformation from manned to unmanned control of gyroplane was therefore completed.","PeriodicalId":426650,"journal":{"name":"2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC)","volume":"46 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":"133293558","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.2016.7829072
Mingjun Li, Jianguo Yan, Yuan Liu
Using parachute to recycle the air-mid load is widely adopted by medium-sized unmanned air vehicles to landing, however the uncontrolled landing location results in lower recovery efficiency. By using Parafoil-UAV recovery system, UAV can land at a smaller scope around the target location accurately. The theoretical research foundation of control block and digital validation platform of Parafoil-UAV system are based on the digital model of the system. This paper presents an improved method to build the digital model: the method to calculating the apparent mass and rotational inertial of the parafoil; Based on the CFD method, aerodynamic coefficients of specified parafoil can be obtained by aerodynamic performance tests; Using infinitesimal method to calculate the aerodynamic forces and moment of the canopy accurately. For Parafoil-UAV system, forces analysis is conducted to the overall system first and then to the single block, and according to kinematic equations, the 9-DOF digital model is established in Matlab/Simulink platform. Through the digital model, the major forms of motions such as gliding, turning and flared landing can be simulated successfully, and the trajectory of the system under the control inputs can also be obtained.
{"title":"Improved digital model of parafoil-unmanned aerial vehicle accurate recycling system","authors":"Mingjun Li, Jianguo Yan, Yuan Liu","doi":"10.1109/CGNCC.2016.7829072","DOIUrl":"https://doi.org/10.1109/CGNCC.2016.7829072","url":null,"abstract":"Using parachute to recycle the air-mid load is widely adopted by medium-sized unmanned air vehicles to landing, however the uncontrolled landing location results in lower recovery efficiency. By using Parafoil-UAV recovery system, UAV can land at a smaller scope around the target location accurately. The theoretical research foundation of control block and digital validation platform of Parafoil-UAV system are based on the digital model of the system. This paper presents an improved method to build the digital model: the method to calculating the apparent mass and rotational inertial of the parafoil; Based on the CFD method, aerodynamic coefficients of specified parafoil can be obtained by aerodynamic performance tests; Using infinitesimal method to calculate the aerodynamic forces and moment of the canopy accurately. For Parafoil-UAV system, forces analysis is conducted to the overall system first and then to the single block, and according to kinematic equations, the 9-DOF digital model is established in Matlab/Simulink platform. Through the digital model, the major forms of motions such as gliding, turning and flared landing can be simulated successfully, and the trajectory of the system under the control inputs can also be obtained.","PeriodicalId":426650,"journal":{"name":"2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC)","volume":"94 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":"133626970","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}
Design of a real-time measurement system based on information fusion of Vision Measurement Unit (VMU) and Inertial Measurement Unit (IMU) is proposed for a semi-physical simulation system. Main contributions of the paper are the design and application of VMU-IMU integration to the real-time simulation of close-range rendezvous and docking (RVD) in lunar orbit. Structure and each component of the system are presented. The pose (position and attitude) filters utilized for information fusion within Kalman filter (KF) framework are designed, which regard Hill equations and quaternion differential equations as process models respectively and choose relative pose of two spacecraft as measure variables. Capabilities of the real-time measurement system are demonstrated by semi-physical closed-loop simulations, which show the proposed system yields more precise navigation result and more effective preservation of energy than an independent VMU.
{"title":"Design of real-time measurement system with Vision/IMU for close-range semi-physical rendezvous and docking simulation","authors":"Zhenshen Qu, X. Chu, Mengyu Fu, Xiaokai Liu, Weinan Xie, Changhong Wang","doi":"10.1109/CGNCC.2016.7829149","DOIUrl":"https://doi.org/10.1109/CGNCC.2016.7829149","url":null,"abstract":"Design of a real-time measurement system based on information fusion of Vision Measurement Unit (VMU) and Inertial Measurement Unit (IMU) is proposed for a semi-physical simulation system. Main contributions of the paper are the design and application of VMU-IMU integration to the real-time simulation of close-range rendezvous and docking (RVD) in lunar orbit. Structure and each component of the system are presented. The pose (position and attitude) filters utilized for information fusion within Kalman filter (KF) framework are designed, which regard Hill equations and quaternion differential equations as process models respectively and choose relative pose of two spacecraft as measure variables. Capabilities of the real-time measurement system are demonstrated by semi-physical closed-loop simulations, which show the proposed system yields more precise navigation result and more effective preservation of energy than an independent VMU.","PeriodicalId":426650,"journal":{"name":"2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC)","volume":"120 28","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-08-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131913587","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.2016.7829047
Lu Keke, Yu Jinyong, Kou Kunhu
This paper focused on the top-level design of the automatic carrier landing system. The carrier platform and carrier-based aircraft landing technology in China have been mature and stable now, in this case, to develop the automatic carrier landing system and to put it into use will greatly enhance the operational capability of the aircraft carrier. In this paper, based on the researches related on automatic carrier landing system that the United States has been proven, the needs of carrier-based aircraft automatic landing technology is analyzed, then the top-level research and design for the system functions and composition are made based on the system requirements. The contents of this paper will provide a reference for the subsequent development of the automatic landing system.
{"title":"The top-level design study for the automatic carrier landing system","authors":"Lu Keke, Yu Jinyong, Kou Kunhu","doi":"10.1109/CGNCC.2016.7829047","DOIUrl":"https://doi.org/10.1109/CGNCC.2016.7829047","url":null,"abstract":"This paper focused on the top-level design of the automatic carrier landing system. The carrier platform and carrier-based aircraft landing technology in China have been mature and stable now, in this case, to develop the automatic carrier landing system and to put it into use will greatly enhance the operational capability of the aircraft carrier. In this paper, based on the researches related on automatic carrier landing system that the United States has been proven, the needs of carrier-based aircraft automatic landing technology is analyzed, then the top-level research and design for the system functions and composition are made based on the system requirements. The contents of this paper will provide a reference for the subsequent development of the automatic landing system.","PeriodicalId":426650,"journal":{"name":"2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC)","volume":"26 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":"132185981","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.2016.7828946
Yong Li, Weisheng Yan, Jian Gao, Beibei Qi
In this paper, a dipolar field-based 3-dimensional homing guidance method is presented to solve the intelligent docking problem of an autonomous underwater vehicle (AUV). The AUV obtains its coordinates in the global coordinate frame by using the measured locations of transponders fixed in the dock station. The desired yaw and pitch angles based on the dipolar field are calculated to guide the AUV to the dock station along the direction of the entrance central axis. The adaptive non-singular terminal sliding mode control is employed for the yaw control and the pitch control, which ensures the robustness and adaptability in the presence of the control system uncertainties. Simulation results are provided to validate the effectiveness of the proposed homing guidance strategy.
{"title":"Dipolar field based 3-dimensional homing guidance algorithm for autonomous underwater vehicles","authors":"Yong Li, Weisheng Yan, Jian Gao, Beibei Qi","doi":"10.1109/CGNCC.2016.7828946","DOIUrl":"https://doi.org/10.1109/CGNCC.2016.7828946","url":null,"abstract":"In this paper, a dipolar field-based 3-dimensional homing guidance method is presented to solve the intelligent docking problem of an autonomous underwater vehicle (AUV). The AUV obtains its coordinates in the global coordinate frame by using the measured locations of transponders fixed in the dock station. The desired yaw and pitch angles based on the dipolar field are calculated to guide the AUV to the dock station along the direction of the entrance central axis. The adaptive non-singular terminal sliding mode control is employed for the yaw control and the pitch control, which ensures the robustness and adaptability in the presence of the control system uncertainties. Simulation results are provided to validate the effectiveness of the proposed homing guidance strategy.","PeriodicalId":426650,"journal":{"name":"2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC)","volume":"38 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":"134634594","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.2016.7828939
Youguang Guo, Ting Yue, Lixin Wang
To avoid the singular problems in the roll axis of Nonlinear Dynamic Inversion (NDI) flight control law with common roll axis response-type, the design of a NDI flight control law with the roll axis response-type of wind-axis roll rate is discussed. Furthermore, a new slow dynamics is used inside the outer loop controller. Reference model and PI compensator are used to generate the command for outer loop controller. The control law and its performance are evaluated on a nonlinear dynamic model of an F-16 aircraft. And the new response-type is shown to yield better tacking performance by comparing with the two conventional response-types in a combined maneuver of Split-S and Cobra.
{"title":"Unconventional roll axis response-type Nonlinear Dynamic Inversion flight control law design","authors":"Youguang Guo, Ting Yue, Lixin Wang","doi":"10.1109/CGNCC.2016.7828939","DOIUrl":"https://doi.org/10.1109/CGNCC.2016.7828939","url":null,"abstract":"To avoid the singular problems in the roll axis of Nonlinear Dynamic Inversion (NDI) flight control law with common roll axis response-type, the design of a NDI flight control law with the roll axis response-type of wind-axis roll rate is discussed. Furthermore, a new slow dynamics is used inside the outer loop controller. Reference model and PI compensator are used to generate the command for outer loop controller. The control law and its performance are evaluated on a nonlinear dynamic model of an F-16 aircraft. And the new response-type is shown to yield better tacking performance by comparing with the two conventional response-types in a combined maneuver of Split-S and Cobra.","PeriodicalId":426650,"journal":{"name":"2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC)","volume":"89 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":"133106775","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.2016.7829006
Zhao Xin, Xiao Ming-qing, Xie Yi-wang-lang, Huang Han-qiao, Cao Wei
The framework of similarity-based prognostics was presented, which takes advantage of system 's training instances' degradation trajectory and run-to-failure time to predict the remaining useful life(RUL) of test instances. Degradation models are extracted from time series data of training instances. Similarity between time series data of test instance and degradation model is calculated by likelihood function. RUL value according to the degradation model is then estimated at the best matched time stamp. RUL values weighted by similarities are fused by kernel density estimation to form the final probability density of the RUL of test instance. Results of aviation equipment simulation experiments show that the similarity-based RUL prediction performs better in accuracy and convergency.
{"title":"A method for predicting aviation equipment failures based on degradation-track similarity","authors":"Zhao Xin, Xiao Ming-qing, Xie Yi-wang-lang, Huang Han-qiao, Cao Wei","doi":"10.1109/CGNCC.2016.7829006","DOIUrl":"https://doi.org/10.1109/CGNCC.2016.7829006","url":null,"abstract":"The framework of similarity-based prognostics was presented, which takes advantage of system 's training instances' degradation trajectory and run-to-failure time to predict the remaining useful life(RUL) of test instances. Degradation models are extracted from time series data of training instances. Similarity between time series data of test instance and degradation model is calculated by likelihood function. RUL value according to the degradation model is then estimated at the best matched time stamp. RUL values weighted by similarities are fused by kernel density estimation to form the final probability density of the RUL of test instance. Results of aviation equipment simulation experiments show that the similarity-based RUL prediction performs better in accuracy and convergency.","PeriodicalId":426650,"journal":{"name":"2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC)","volume":"18 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":"130309210","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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