Marine diesel engines are widely used in the domain of ship. Uncertain environment coupled with external disturbance affects the stability of the engine speed, hence, keeping engine speed steady is a crucial task. Fuzzy logic control based PID controller for diesel engine with variable sampling is proposed in this paper. The fuzzy logic employed in this study is different from previous works. The input parameter engine speed is divided into three parts and three PID controllers are used to adjust speed in each divided part. Couple of controllers are compared by simulations on Matlab/Simulink environment with a mean value engine model. The results demonstrate that the fuzzy logic controller with variable integral PID can retain the speed well both in speed tracking and load variation conditions. On the basis of the mentioned controller above, we propose a new controller where the coefficient k_p is variable and depends on the speed error (e). The simulations prove that the new controller has better adaptation in the condition of the load change.
{"title":"Fuzzy Logic Control Based PID Controller for Diesel Engine with Variable Sampling Rate Control Theory","authors":"Xuemin Li, Chunyue Feng, Runzhi Wang, Yufei Liu, Yunlong Yang, Yutun Yang","doi":"10.1109/ICCSSE.2019.00024","DOIUrl":"https://doi.org/10.1109/ICCSSE.2019.00024","url":null,"abstract":"Marine diesel engines are widely used in the domain of ship. Uncertain environment coupled with external disturbance affects the stability of the engine speed, hence, keeping engine speed steady is a crucial task. Fuzzy logic control based PID controller for diesel engine with variable sampling is proposed in this paper. The fuzzy logic employed in this study is different from previous works. The input parameter engine speed is divided into three parts and three PID controllers are used to adjust speed in each divided part. Couple of controllers are compared by simulations on Matlab/Simulink environment with a mean value engine model. The results demonstrate that the fuzzy logic controller with variable integral PID can retain the speed well both in speed tracking and load variation conditions. On the basis of the mentioned controller above, we propose a new controller where the coefficient k_p is variable and depends on the speed error (e). The simulations prove that the new controller has better adaptation in the condition of the load change.","PeriodicalId":443482,"journal":{"name":"2019 5th International Conference on Control Science and Systems Engineering (ICCSSE)","volume":"416 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":"133581143","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.2019.00031
Wang Min, Li Qiang, An Ran, Liang Xingang
GEO satellite station-keeping consuming minimal propellant, to maintain the satellite longitude and latitude in a limitative area, is a constrained optimization problem. The station-keeping problem contains complex firing position constraint such as forbidden firing position during eclipse. Aiming at All-electric propulsion satellite station-keeping problem, the control model between firing parameters and orbit elements is built. A special method is put forward to solve the station-keeping strategy to avoid forbidden position. The geostationary orbit is divided into several firing segments and thruster firing is described as a series of binary codes. To calculate the firing parameters, genetic algorithm is adopted. By choosing appropriate firing segments the forbidden firing area ca be avoided. The simulation results reveal that this method can efficiently avoid forbidden firing positions and the satellite longitude and latitude can be controlled in high precision.
{"title":"Station-Keeping Method for GEO All-Electric Propulsion Satellite to Avoid Forbidden Firing Position","authors":"Wang Min, Li Qiang, An Ran, Liang Xingang","doi":"10.1109/ICCSSE.2019.00031","DOIUrl":"https://doi.org/10.1109/ICCSSE.2019.00031","url":null,"abstract":"GEO satellite station-keeping consuming minimal propellant, to maintain the satellite longitude and latitude in a limitative area, is a constrained optimization problem. The station-keeping problem contains complex firing position constraint such as forbidden firing position during eclipse. Aiming at All-electric propulsion satellite station-keeping problem, the control model between firing parameters and orbit elements is built. A special method is put forward to solve the station-keeping strategy to avoid forbidden position. The geostationary orbit is divided into several firing segments and thruster firing is described as a series of binary codes. To calculate the firing parameters, genetic algorithm is adopted. By choosing appropriate firing segments the forbidden firing area ca be avoided. The simulation results reveal that this method can efficiently avoid forbidden firing positions and the satellite longitude and latitude can be controlled in high precision.","PeriodicalId":443482,"journal":{"name":"2019 5th International Conference on Control Science and Systems Engineering (ICCSSE)","volume":"95 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":"114540326","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.2019.00032
Yanting Che, Dongze Lv, Jia Luo, Guangming Huang, Lei-Hua Ge
In this paper, a dimensionality reduction Gauss-Hermite quadrature filter (DRGHQF) is proposed. Compared with the conventional GHQF algorithm and with the Rao-Blackwellised particle filter (RBPF), the proposed DRGHQF performs better in terms of computational cost and accuracy. The simulation results indicate that the DRGHQF can significantly reduce the computational cost without incurring a loss in accuracy.
{"title":"Dimensionality Reduction Gauss-Hermite Quadrature Filter Algorithm","authors":"Yanting Che, Dongze Lv, Jia Luo, Guangming Huang, Lei-Hua Ge","doi":"10.1109/ICCSSE.2019.00032","DOIUrl":"https://doi.org/10.1109/ICCSSE.2019.00032","url":null,"abstract":"In this paper, a dimensionality reduction Gauss-Hermite quadrature filter (DRGHQF) is proposed. Compared with the conventional GHQF algorithm and with the Rao-Blackwellised particle filter (RBPF), the proposed DRGHQF performs better in terms of computational cost and accuracy. The simulation results indicate that the DRGHQF can significantly reduce the computational cost without incurring a loss in accuracy.","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":"131812607","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.2019.00012
Yujia Wang, Muyuan Wang, Jiae Yang, Xiaolei Liu, Xuebo Yang
This paper presents an optimal guaranteed cost controller for aircraft lateral dynamics. A linear model with parametric uncertainties and time delay is first used to establish the proposed control scheme. The Lyapunov stability theorem and linear matrix inequality are then used to design an optimal state feedback control law for application to the lateral aircraft dynamics which resolves the instability caused by said uncertainties and time delay. The effectiveness and robustness of the model are demonstrated via simulation.
{"title":"Optimal Guaranteed Cost Control Design for Lateral Aircraft Dynamics with Uncertainties and Time Delay","authors":"Yujia Wang, Muyuan Wang, Jiae Yang, Xiaolei Liu, Xuebo Yang","doi":"10.1109/ICCSSE.2019.00012","DOIUrl":"https://doi.org/10.1109/ICCSSE.2019.00012","url":null,"abstract":"This paper presents an optimal guaranteed cost controller for aircraft lateral dynamics. A linear model with parametric uncertainties and time delay is first used to establish the proposed control scheme. The Lyapunov stability theorem and linear matrix inequality are then used to design an optimal state feedback control law for application to the lateral aircraft dynamics which resolves the instability caused by said uncertainties and time delay. The effectiveness and robustness of the model are demonstrated via simulation.","PeriodicalId":443482,"journal":{"name":"2019 5th International Conference on Control Science and Systems Engineering (ICCSSE)","volume":"217 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":"134207747","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.2019.00010
Wang Jun, Yuyang Tian
Aiming at the problem of partial failure of Quadrotor uav actuator, a collaborative design method of optimizing PID parameters of controller, fault diagnosis and fault-tolerant control is proposed. Firstly, the off-line optimization of PID parameters of four-rotor uav controller is carried out by using ant colony algorithm. According to the severity of actuator fault, the fault is partitioned and the corresponding fault tolerant controller is designed. In the case of actuator failure, support vector machine (SVM) is used to diagnose the fault, and then the fault of the fault tolerant controller is compensated by online scheduling. Finally, the feasibility and effectiveness of the proposed method are verified on the matlab experimental platform.
{"title":"Fault Tolerant Control of Quadrotor UAV Based on Support Vector Machine","authors":"Wang Jun, Yuyang Tian","doi":"10.1109/ICCSSE.2019.00010","DOIUrl":"https://doi.org/10.1109/ICCSSE.2019.00010","url":null,"abstract":"Aiming at the problem of partial failure of Quadrotor uav actuator, a collaborative design method of optimizing PID parameters of controller, fault diagnosis and fault-tolerant control is proposed. Firstly, the off-line optimization of PID parameters of four-rotor uav controller is carried out by using ant colony algorithm. According to the severity of actuator fault, the fault is partitioned and the corresponding fault tolerant controller is designed. In the case of actuator failure, support vector machine (SVM) is used to diagnose the fault, and then the fault of the fault tolerant controller is compensated by online scheduling. Finally, the feasibility and effectiveness of the proposed method are verified on the matlab experimental platform.","PeriodicalId":443482,"journal":{"name":"2019 5th International Conference on Control Science and Systems Engineering (ICCSSE)","volume":"15 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":"125013684","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.2019.00001
{"title":"[Title page i]","authors":"","doi":"10.1109/iccsse.2019.00001","DOIUrl":"https://doi.org/10.1109/iccsse.2019.00001","url":null,"abstract":"","PeriodicalId":443482,"journal":{"name":"2019 5th International Conference on Control Science and Systems Engineering (ICCSSE)","volume":"36 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":"121728932","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.2019.00016
Waqas Ahmed, Zhongjian Li, Muhammad Istan, M. Anwar
Autopilots maintain the flight balance of aircraft using aerodynamics forces autonomously. Autopilot system design is divided into two section, inner and outer loop. Inner loop act as a stabilizer while outer loop provide motion control such as altitude, speed and path angle. The aim of this study is to utilize eigenstructure assignment (EA) and Proportional -Integral-Derivative (PID) in multi-loop configuration for altitude and pitch angle control. Aircraft non-linear model is obtained using Euler formulism and trimmed at certain flight conditions to achieve the linear state space model of aircraft which is used in this study. Aircraft longitudinal motion is highly coupled and unstable, EA is implemented in inner loop for stability augmentation and decoupling of system. Two different outer loop controllers are designed for altitude and pitch control of aircraft using PID controller. Designing controllers in such a configuration not only reduced the coupling between different state variables but also accurately control and tracked the altitude and pitch angle. Effectiveness of multi-loop control configuration will be illustrated with the help Matlab/Simulink model and results.
{"title":"Multi-objective Eigenstructure Assignment-PID Based Controller Design for Longitudinal Motion of Aircraft","authors":"Waqas Ahmed, Zhongjian Li, Muhammad Istan, M. Anwar","doi":"10.1109/ICCSSE.2019.00016","DOIUrl":"https://doi.org/10.1109/ICCSSE.2019.00016","url":null,"abstract":"Autopilots maintain the flight balance of aircraft using aerodynamics forces autonomously. Autopilot system design is divided into two section, inner and outer loop. Inner loop act as a stabilizer while outer loop provide motion control such as altitude, speed and path angle. The aim of this study is to utilize eigenstructure assignment (EA) and Proportional -Integral-Derivative (PID) in multi-loop configuration for altitude and pitch angle control. Aircraft non-linear model is obtained using Euler formulism and trimmed at certain flight conditions to achieve the linear state space model of aircraft which is used in this study. Aircraft longitudinal motion is highly coupled and unstable, EA is implemented in inner loop for stability augmentation and decoupling of system. Two different outer loop controllers are designed for altitude and pitch control of aircraft using PID controller. Designing controllers in such a configuration not only reduced the coupling between different state variables but also accurately control and tracked the altitude and pitch angle. Effectiveness of multi-loop control configuration will be illustrated with the help Matlab/Simulink model and results.","PeriodicalId":443482,"journal":{"name":"2019 5th International Conference on Control Science and Systems Engineering (ICCSSE)","volume":"4 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":"122753986","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.2019.00008
Liyao Wu, Wei Han
This paper discusses the design of a cooperative control system for a carrier-based aircraft/unmanned aerial vehicles (UAVs) formation. Firstly, this paper is based on the background of open sea combat in the future, and combined with the characteristics and combat process of the carrier-based aircraft/UAVs formation, then a three-layer hierarchical coordination control system of the carrier-based aircraft/UAVs formation is designed, and the control system is described in terms of hardware and software functions. It provides a reference for the future research on the cooperative command control system of carrier-based aircraft/UAVs formation.
{"title":"Design of Cooperative Control System for a Carrier-Based Aircraft/ Unmanned Aerial Vehicles Formation","authors":"Liyao Wu, Wei Han","doi":"10.1109/ICCSSE.2019.00008","DOIUrl":"https://doi.org/10.1109/ICCSSE.2019.00008","url":null,"abstract":"This paper discusses the design of a cooperative control system for a carrier-based aircraft/unmanned aerial vehicles (UAVs) formation. Firstly, this paper is based on the background of open sea combat in the future, and combined with the characteristics and combat process of the carrier-based aircraft/UAVs formation, then a three-layer hierarchical coordination control system of the carrier-based aircraft/UAVs formation is designed, and the control system is described in terms of hardware and software functions. It provides a reference for the future research on the cooperative command control system of carrier-based aircraft/UAVs formation.","PeriodicalId":443482,"journal":{"name":"2019 5th International Conference on Control Science and Systems Engineering (ICCSSE)","volume":"1 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":"130943872","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.2019.00015
P. Artitthang, Mingpei Lin, Ming Xu
The properties of coulomb force (CF) that nearly propellantless and exhaust plume contaminatless compared to the conventional chemical liquid propulsion thrusters (e.g., micro PPT, FEEP…etc.), make it attractive use for the close formation flying of the spacecraft at high Earth orbit (HEO). This paper presents the charged feedback controller using the optimal control based on the Linear Quadratic Regulator (LQR) method. The interaction between the CF that generated from charged sphere devices on the Target and Chase crafts are exploited to deploy the Chaser from the Target. Finally, the simulation results showed the effectiveness coulomb feedback-based LQR controller can be efforted the initial position of the Chaser entry to the design orbit as expected. The command force expenditure is on the order of -9 to 48 milli-Newton, in which the magnitude of coulomb charged has bounded.
{"title":"Optimal Control for Deployment of Charged Spacecraft Formation Flying Based LQR","authors":"P. Artitthang, Mingpei Lin, Ming Xu","doi":"10.1109/ICCSSE.2019.00015","DOIUrl":"https://doi.org/10.1109/ICCSSE.2019.00015","url":null,"abstract":"The properties of coulomb force (CF) that nearly propellantless and exhaust plume contaminatless compared to the conventional chemical liquid propulsion thrusters (e.g., micro PPT, FEEP…etc.), make it attractive use for the close formation flying of the spacecraft at high Earth orbit (HEO). This paper presents the charged feedback controller using the optimal control based on the Linear Quadratic Regulator (LQR) method. The interaction between the CF that generated from charged sphere devices on the Target and Chase crafts are exploited to deploy the Chaser from the Target. Finally, the simulation results showed the effectiveness coulomb feedback-based LQR controller can be efforted the initial position of the Chaser entry to the design orbit as expected. The command force expenditure is on the order of -9 to 48 milli-Newton, in which the magnitude of coulomb charged has bounded.","PeriodicalId":443482,"journal":{"name":"2019 5th International Conference on Control Science and Systems Engineering (ICCSSE)","volume":"36 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":"128950426","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.2019.00025
Hongguang Zhang
The problem of persistent bounded disturbance rejection for switched linear systems is considered in this paper. First, the concept of internal stability with performance of bounded disturbance rejection for switched linear systems under arbitrary switching sequences is introduced. Then, an equivalent condition is obtained. By this, a necessary and sufficient condition for the existence of a subsystem-dependent linear state-feedback controller such that the closed-loop system is internally stable with the desired performance is established. A numerical example are worked out to illustrate the efficiency of the proposed approach.
{"title":"Persistent Bounded Disturbance Rejection for Switched Linear Systems","authors":"Hongguang Zhang","doi":"10.1109/ICCSSE.2019.00025","DOIUrl":"https://doi.org/10.1109/ICCSSE.2019.00025","url":null,"abstract":"The problem of persistent bounded disturbance rejection for switched linear systems is considered in this paper. First, the concept of internal stability with performance of bounded disturbance rejection for switched linear systems under arbitrary switching sequences is introduced. Then, an equivalent condition is obtained. By this, a necessary and sufficient condition for the existence of a subsystem-dependent linear state-feedback controller such that the closed-loop system is internally stable with the desired performance is established. A numerical example are worked out to illustrate the efficiency of the proposed approach.","PeriodicalId":443482,"journal":{"name":"2019 5th International Conference on Control Science and Systems Engineering (ICCSSE)","volume":"76 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":"133226815","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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