Pub Date : 2019-08-01DOI: 10.1109/ICCSSE.2019.00030
Wang Min, Li Qiang, Liang Xingang, An Ran
More and more GEO Satellites adopts electric thrusters to execute station-keeping and momentum dumping. Profiting from the high specific impulse of electric propulsion, there is substantially decrease in fuel consumption and improvement in payload capacity. Quantity and configuration of electric thrusters have a large influence in station-keeping efficiency and momentum dumping capacity. Considering the necessary of system backup, the station-keeping and momentum dumping must be performed correctly while at least one thruster breaks down. In this paper, a method of station-keeping and momentum dumping capacity analysis is introduced, from which the minimum configuration of electric thrusters is induced. In addition, the minimum configuration of electric thrusters for GEO satellite station-keeping and momentum dumping with backup is discussed. At last, the relationship between thrusters' installation parameters and capacity of station-keeping and momentum dumping is analyzed. In view of the above, the designing method of electric thrusters' installation parameters is obtained.
{"title":"Electric Thrusters Configuration Strategy Study on Station-Keeping and Momentum Dumping of GEO Satellite","authors":"Wang Min, Li Qiang, Liang Xingang, An Ran","doi":"10.1109/ICCSSE.2019.00030","DOIUrl":"https://doi.org/10.1109/ICCSSE.2019.00030","url":null,"abstract":"More and more GEO Satellites adopts electric thrusters to execute station-keeping and momentum dumping. Profiting from the high specific impulse of electric propulsion, there is substantially decrease in fuel consumption and improvement in payload capacity. Quantity and configuration of electric thrusters have a large influence in station-keeping efficiency and momentum dumping capacity. Considering the necessary of system backup, the station-keeping and momentum dumping must be performed correctly while at least one thruster breaks down. In this paper, a method of station-keeping and momentum dumping capacity analysis is introduced, from which the minimum configuration of electric thrusters is induced. In addition, the minimum configuration of electric thrusters for GEO satellite station-keeping and momentum dumping with backup is discussed. At last, the relationship between thrusters' installation parameters and capacity of station-keeping and momentum dumping is analyzed. In view of the above, the designing method of electric thrusters' installation parameters is obtained.","PeriodicalId":443482,"journal":{"name":"2019 5th International Conference on Control Science and Systems Engineering (ICCSSE)","volume":"11 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-08-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131933713","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 : 2019-08-01DOI: 10.1109/ICCSSE.2019.00020
Yulong Zhao, Xin Tengda, Hu Min, Pan Shengdong
Aiming at the new gyro structure of fan shaped superfluid interference grating gyro, the noise suppression of gyro based on software filtering algorithm is studied in this paper. Firstly, the phase noise model of gyro is constructed, and the amplitude range and characteristics of the phase noise are quantitatively analyzed. Secondly, considering the working principle of gyro and the additive noise characteristics of the phase noise, the mixed angular velocity information of gyro output is used as the expected input of the noise suppression system, and the phase noise is used as the reference input, the gyro noise suppression system is designed based on the normalized least mean square (NLMS). Finally, the influence of filter parameters on gyro noise suppression system is analyzed and the effectiveness of the design system is verified.
{"title":"Noise Suppression Research of Fan Shaped Superfluid Interference Grating Gyroscope","authors":"Yulong Zhao, Xin Tengda, Hu Min, Pan Shengdong","doi":"10.1109/ICCSSE.2019.00020","DOIUrl":"https://doi.org/10.1109/ICCSSE.2019.00020","url":null,"abstract":"Aiming at the new gyro structure of fan shaped superfluid interference grating gyro, the noise suppression of gyro based on software filtering algorithm is studied in this paper. Firstly, the phase noise model of gyro is constructed, and the amplitude range and characteristics of the phase noise are quantitatively analyzed. Secondly, considering the working principle of gyro and the additive noise characteristics of the phase noise, the mixed angular velocity information of gyro output is used as the expected input of the noise suppression system, and the phase noise is used as the reference input, the gyro noise suppression system is designed based on the normalized least mean square (NLMS). Finally, the influence of filter parameters on gyro noise suppression system is analyzed and the effectiveness of the design system is verified.","PeriodicalId":443482,"journal":{"name":"2019 5th International Conference on Control Science and Systems Engineering (ICCSSE)","volume":"104 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-08-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132761876","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 : 2019-08-01DOI: 10.1109/iccsse.2019.00003
{"title":"[Copyright notice]","authors":"","doi":"10.1109/iccsse.2019.00003","DOIUrl":"https://doi.org/10.1109/iccsse.2019.00003","url":null,"abstract":"","PeriodicalId":443482,"journal":{"name":"2019 5th International Conference on Control Science and Systems Engineering (ICCSSE)","volume":"58 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-08-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127119024","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 : 2019-08-01DOI: 10.1109/ICCSSE.2019.00026
Ming Wang, T. Zhang
This paper investigates the finite-time trajectory tracking control problem for rigid robotic manipulators. The objective is to control all the links of rigid manipulators to converge into the desired form of motion in a finite time respectively. Based on the finite-time control technique, a new motion tracking control law, which is suitable for a class of rigid manipulators with model uncertainties and external disturbances, is proposed using the fast terminal sliding mode control (FTSMC) scheme. The proposed method can drive the system states reach zero without requiring the explicit dynamic model. Rigorous proof is given by using Lyapunov and matrix theory. Simulation results are presented to validate the effectiveness of our theoretical analysis.
{"title":"A New Finite-Time Control of Rigid Manipulator with FTSMC Approach","authors":"Ming Wang, T. Zhang","doi":"10.1109/ICCSSE.2019.00026","DOIUrl":"https://doi.org/10.1109/ICCSSE.2019.00026","url":null,"abstract":"This paper investigates the finite-time trajectory tracking control problem for rigid robotic manipulators. The objective is to control all the links of rigid manipulators to converge into the desired form of motion in a finite time respectively. Based on the finite-time control technique, a new motion tracking control law, which is suitable for a class of rigid manipulators with model uncertainties and external disturbances, is proposed using the fast terminal sliding mode control (FTSMC) scheme. The proposed method can drive the system states reach zero without requiring the explicit dynamic model. Rigorous proof is given by using Lyapunov and matrix theory. Simulation results are presented to validate the effectiveness of our theoretical analysis.","PeriodicalId":443482,"journal":{"name":"2019 5th International Conference on Control Science and Systems Engineering (ICCSSE)","volume":"112 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-08-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133148056","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 : 2019-08-01DOI: 10.1109/ICCSSE.2019.00018
Jun Wang, Miaomiao Ling
In this paper, the linear networked control system (NCS) with any actuator failures is discussed. The offline design of the fault-tolerant controller under the discrete event triggering communication mechanism (DETCS) and the control problem of online scheduling and compensation are studied. Firstly, according to certain rules, the actuator fault is divided into four sections. By constructing Lyapunov-Krasovskii functional and improved Jesson inequalities, a set of controllers with less conservativeness is designed based on common faults in the interval. Secondly, when the fault detection observer detects the fault, the corresponding interval controller is dispatched through the scheduling mechanism. In case of sudden and rare failure within the interval, the controller in which the fault occurs should be compensated to meet the fault-tolerant control requirements. Finally, a simulation example is given to verify the correctness and effectiveness of the proposed method.
{"title":"Research on an Improved Hybrid Fault-Tolerant Control Method for NCS Based on DETCS","authors":"Jun Wang, Miaomiao Ling","doi":"10.1109/ICCSSE.2019.00018","DOIUrl":"https://doi.org/10.1109/ICCSSE.2019.00018","url":null,"abstract":"In this paper, the linear networked control system (NCS) with any actuator failures is discussed. The offline design of the fault-tolerant controller under the discrete event triggering communication mechanism (DETCS) and the control problem of online scheduling and compensation are studied. Firstly, according to certain rules, the actuator fault is divided into four sections. By constructing Lyapunov-Krasovskii functional and improved Jesson inequalities, a set of controllers with less conservativeness is designed based on common faults in the interval. Secondly, when the fault detection observer detects the fault, the corresponding interval controller is dispatched through the scheduling mechanism. In case of sudden and rare failure within the interval, the controller in which the fault occurs should be compensated to meet the fault-tolerant control requirements. Finally, a simulation example is given to verify the correctness and effectiveness of the proposed method.","PeriodicalId":443482,"journal":{"name":"2019 5th International Conference on Control Science and Systems Engineering (ICCSSE)","volume":"42 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-08-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124762610","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 : 2019-08-01DOI: 10.1109/ICCSSE.2019.00040
Chen Zhao, Jie Liu, Hao Zhang, Zhenfei Song, Yajie Chang
The level of intelligent autonomy of satellites determines the ability and efficiency of human beings in exploring and utilizing space in the future. As the central nervous system of satellites, the intelligent control system of satellites is one of the decisive factors in the development of software-defined satellites. In order to alleviate the pressure of orbit control on ground operation and control system, an intelligent orbit control strategy for geostationary orbit satellites is designed based on the open software architecture of software-defined satellites, which enables satellites to complete orbit control independently of human intervention. The simulation results verify that the orbit control strategy can use less propellant than traditional orbit maintenance to keep the position error of satellite track within (+10km) autonomously, which effectively improves the intelligent level of satellite orbit control.
{"title":"Precise Intelligent Orbit Control Strategy on Geostationary Orbit Satellite","authors":"Chen Zhao, Jie Liu, Hao Zhang, Zhenfei Song, Yajie Chang","doi":"10.1109/ICCSSE.2019.00040","DOIUrl":"https://doi.org/10.1109/ICCSSE.2019.00040","url":null,"abstract":"The level of intelligent autonomy of satellites determines the ability and efficiency of human beings in exploring and utilizing space in the future. As the central nervous system of satellites, the intelligent control system of satellites is one of the decisive factors in the development of software-defined satellites. In order to alleviate the pressure of orbit control on ground operation and control system, an intelligent orbit control strategy for geostationary orbit satellites is designed based on the open software architecture of software-defined satellites, which enables satellites to complete orbit control independently of human intervention. The simulation results verify that the orbit control strategy can use less propellant than traditional orbit maintenance to keep the position error of satellite track within (+10km) autonomously, which effectively improves the intelligent level of satellite orbit control.","PeriodicalId":443482,"journal":{"name":"2019 5th International Conference on Control Science and Systems Engineering (ICCSSE)","volume":"21 3","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-08-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132194157","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 : 2019-08-01DOI: 10.1109/ICCSSE.2019.00013
Juan Tan, Xin Chen, Dong Cao
Airborne sensors play an important role in flight control system acquisition of flight status, internal and external loop control law solution and so on. In addition to increasing the hardware redundancy to improve the system reliability, it can also increase the analytical redundancy of the model to improve the system fault tolerance. In this paper, based on the aerodynamic parameters of UAV, fault modeling and analysis of sensor system are carried out, and a state estimator is designed using Kalman-Bussy filter principle. According to the system residual, the improved residual detection algorithm is used to estimate and evaluate the system fault state. Under the condition of joint voting based on cycle time and residual value, an adaptive reference model is designed to compare and modify the analytical model in real time, so as to improve the fault tolerance ability of the system. The simulation results show proposed method is feasible and effective. The process of adding iterative residuals detection can respond quickly to sudden fault and detect the slow-changing characteristics of soft fault obviously, so it is suitable for typical fault diagnosis of airborne sensor system. The process of adaptive model adjustment plays a key role in reducing the influence of noise and correcting the uncertainty error of the system, which makes the identification process of aerodynamic parameter model more efficient.
{"title":"An Airborne Sensor Fault Diagnosis Method Based on Analytic Model Parameter Identification","authors":"Juan Tan, Xin Chen, Dong Cao","doi":"10.1109/ICCSSE.2019.00013","DOIUrl":"https://doi.org/10.1109/ICCSSE.2019.00013","url":null,"abstract":"Airborne sensors play an important role in flight control system acquisition of flight status, internal and external loop control law solution and so on. In addition to increasing the hardware redundancy to improve the system reliability, it can also increase the analytical redundancy of the model to improve the system fault tolerance. In this paper, based on the aerodynamic parameters of UAV, fault modeling and analysis of sensor system are carried out, and a state estimator is designed using Kalman-Bussy filter principle. According to the system residual, the improved residual detection algorithm is used to estimate and evaluate the system fault state. Under the condition of joint voting based on cycle time and residual value, an adaptive reference model is designed to compare and modify the analytical model in real time, so as to improve the fault tolerance ability of the system. The simulation results show proposed method is feasible and effective. The process of adding iterative residuals detection can respond quickly to sudden fault and detect the slow-changing characteristics of soft fault obviously, so it is suitable for typical fault diagnosis of airborne sensor system. The process of adaptive model adjustment plays a key role in reducing the influence of noise and correcting the uncertainty error of the system, which makes the identification process of aerodynamic parameter model more efficient.","PeriodicalId":443482,"journal":{"name":"2019 5th International Conference on Control Science and Systems Engineering (ICCSSE)","volume":"107 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-08-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131989005","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 : 2019-08-01DOI: 10.1109/ICCSSE.2019.00014
Bin Hu, Zhaihe Zhou, Chuntao Li
This paper introduces the composition of the UAV simulation system, uses MATLAB/Simulink to build the model of UAV system, and then generates an executable program from model through rapid prototyping technology, and loads the executable program onto the xPC target. And Simulation console based on xPC Target API was built to control and monitor the simulation. Finally, after the UAV semi-physical simulation system is completed, the real-time and semi-physical simulation tests of the system are carried out. Test results show that the simulation system is reliable and stable, and the overall development time is short.
{"title":"Design of Semi-Physical Real-Time Simulation System for UAV Based on xPC","authors":"Bin Hu, Zhaihe Zhou, Chuntao Li","doi":"10.1109/ICCSSE.2019.00014","DOIUrl":"https://doi.org/10.1109/ICCSSE.2019.00014","url":null,"abstract":"This paper introduces the composition of the UAV simulation system, uses MATLAB/Simulink to build the model of UAV system, and then generates an executable program from model through rapid prototyping technology, and loads the executable program onto the xPC target. And Simulation console based on xPC Target API was built to control and monitor the simulation. Finally, after the UAV semi-physical simulation system is completed, the real-time and semi-physical simulation tests of the system are carried out. Test results show that the simulation system is reliable and stable, and the overall development time is short.","PeriodicalId":443482,"journal":{"name":"2019 5th International Conference on Control Science and Systems Engineering (ICCSSE)","volume":"8 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-08-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116323804","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 : 2019-08-01DOI: 10.1109/ICCSSE.2019.00011
Sinuo Pan
This paper considers the optimized schedule for UAV fleets in the scenario of delivery. The target is constructing a plan including the mission allocation for each drone, the routing schedule and the number of drones. Additional factors been considered are the change of the unit energy consumption with the payload of the drone. To realize the goal, K-means++ clustering are applied to designate the mission area for each drone and genetic algorithm are adopted to make the flight path. Moreover, the number of drones are determined by two considerations respectively which are the minimum number of drones and the minimum energy consumption.
{"title":"UAV Delivery Planning Based on K-Means++ Clustering and Genetic Algorithm","authors":"Sinuo Pan","doi":"10.1109/ICCSSE.2019.00011","DOIUrl":"https://doi.org/10.1109/ICCSSE.2019.00011","url":null,"abstract":"This paper considers the optimized schedule for UAV fleets in the scenario of delivery. The target is constructing a plan including the mission allocation for each drone, the routing schedule and the number of drones. Additional factors been considered are the change of the unit energy consumption with the payload of the drone. To realize the goal, K-means++ clustering are applied to designate the mission area for each drone and genetic algorithm are adopted to make the flight path. Moreover, the number of drones are determined by two considerations respectively which are the minimum number of drones and the minimum energy consumption.","PeriodicalId":443482,"journal":{"name":"2019 5th International Conference on Control Science and Systems Engineering (ICCSSE)","volume":"27 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-08-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121752597","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}
The paper constructed a flexible, low-cost, compact and safe induction motor simulator for microprocessors, DSP lectures and researches, targeting motor-drive control. The system is composed of two parts: (1) the control theory realization design based on a TI DSP chip, TMS320F28335 (2) the Xilinx Spartan-3E FPGA development board, used to simulate the induction motor drive system. It is capable of simulating components, e.g. controller, inverter, induction motor, sensor and load. This experiment simulation system creates responses that are identical to physical motor responses. Thus, the induction motor simulator can replace the expensive motor drive experiment equipment and achieve the theoretical verification and measurements.
{"title":"Development of Teaching Aid for Induction Motor Drive Control System","authors":"Shyh-Shing Perng, Ter-Feng Wu, Maoh-Chin Jiang, Yi-Ru Jiang","doi":"10.1109/ICCSSE.2019.00023","DOIUrl":"https://doi.org/10.1109/ICCSSE.2019.00023","url":null,"abstract":"The paper constructed a flexible, low-cost, compact and safe induction motor simulator for microprocessors, DSP lectures and researches, targeting motor-drive control. The system is composed of two parts: (1) the control theory realization design based on a TI DSP chip, TMS320F28335 (2) the Xilinx Spartan-3E FPGA development board, used to simulate the induction motor drive system. It is capable of simulating components, e.g. controller, inverter, induction motor, sensor and load. This experiment simulation system creates responses that are identical to physical motor responses. Thus, the induction motor simulator can replace the expensive motor drive experiment equipment and achieve the theoretical verification and measurements.","PeriodicalId":443482,"journal":{"name":"2019 5th International Conference on Control Science and Systems Engineering (ICCSSE)","volume":"29 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-08-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115290869","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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