Pub Date : 2010-06-08DOI: 10.1109/ISSCAA.2010.5633274
Zhaohui Yao, W. Bao
This paper has discussed a class of practical switched systems with multi proportional-integral controllers. And the switching control principles based on the Min(Max) switching law is described and the integral saturation limiting in proportional-integral controller to guarantee a rapid switching is discussed. A conservative dynamic performance of this class of switched systems under switching is presented, which is the possible maximum value of the system dynamic output maximum percent overshoot at any different switching points. The conservative dynamic performance is dependent just on the system parameters but not on the initial states caused by different switching points, which makes it easy to present an exact performance objective in switching control design. And finally, a general switching proportional-integral control design approach for this class of switched systems is generalized and is testified to be reasonable and reliable by simulations.
{"title":"A multiloop switching proportional-integral control design based on Min/Max law","authors":"Zhaohui Yao, W. Bao","doi":"10.1109/ISSCAA.2010.5633274","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633274","url":null,"abstract":"This paper has discussed a class of practical switched systems with multi proportional-integral controllers. And the switching control principles based on the Min(Max) switching law is described and the integral saturation limiting in proportional-integral controller to guarantee a rapid switching is discussed. A conservative dynamic performance of this class of switched systems under switching is presented, which is the possible maximum value of the system dynamic output maximum percent overshoot at any different switching points. The conservative dynamic performance is dependent just on the system parameters but not on the initial states caused by different switching points, which makes it easy to present an exact performance objective in switching control design. And finally, a general switching proportional-integral control design approach for this class of switched systems is generalized and is testified to be reasonable and reliable by simulations.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"30 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125158120","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-06-08DOI: 10.1109/ISSCAA.2010.5633352
Hongbo Li, Y. Lu, Yun Zhang
A new method called track smooth filter(TSF), which improves the tracking quality of target track, is presented for the situation that the measuring data rate is low, the system feature and the target movement is complicated. Based on the spatial trace matching principle that the track made by the target motion is continual and smooth, simple and robust estimation models can be constructed by the regression analysis for the target kinematics process with unknown behavior. The state estimations of the target are obtained by the smooth filter so as to establish the target track. In applications on the experimental data, it is shown that the adaptability and the stability of the track filter are well.
{"title":"A method of target tracking based on spatial trace matching principle","authors":"Hongbo Li, Y. Lu, Yun Zhang","doi":"10.1109/ISSCAA.2010.5633352","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633352","url":null,"abstract":"A new method called track smooth filter(TSF), which improves the tracking quality of target track, is presented for the situation that the measuring data rate is low, the system feature and the target movement is complicated. Based on the spatial trace matching principle that the track made by the target motion is continual and smooth, simple and robust estimation models can be constructed by the regression analysis for the target kinematics process with unknown behavior. The state estimations of the target are obtained by the smooth filter so as to establish the target track. In applications on the experimental data, it is shown that the adaptability and the stability of the track filter are well.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"11 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125886138","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-06-08DOI: 10.1109/ISSCAA.2010.5633386
Xin-sheng Wang, Lei Ma
The gyro and the infrared earth sensor (IES) are two kinds of important components in satellite attitude control system. A fault detection and isolation (FDI) approach based on observer and Kalman filter is presented. Firstly, the models of gyro and IES are discussed, and a virtual linear system of satellite pitch channel is constructed. Then, an observer for fault detection and a Kalman filter for fault isolation are designed. The observer could detect faults from IES and gyro, but the Kalman filter could only detect IES fault rather than sensitive to gyro fault. So, fault isolation method could be achieved via fault arbitration logic given in the paper. Lastly, computer simulations are finished on the condition of system health status (no faults), IES fault and gyro fault. The simulation results show that the proposed fault detection and isolation approach is correct and feasible.
{"title":"Fault detection and isolation for gyro and infrared earth sensor based on observer and filter","authors":"Xin-sheng Wang, Lei Ma","doi":"10.1109/ISSCAA.2010.5633386","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633386","url":null,"abstract":"The gyro and the infrared earth sensor (IES) are two kinds of important components in satellite attitude control system. A fault detection and isolation (FDI) approach based on observer and Kalman filter is presented. Firstly, the models of gyro and IES are discussed, and a virtual linear system of satellite pitch channel is constructed. Then, an observer for fault detection and a Kalman filter for fault isolation are designed. The observer could detect faults from IES and gyro, but the Kalman filter could only detect IES fault rather than sensitive to gyro fault. So, fault isolation method could be achieved via fault arbitration logic given in the paper. Lastly, computer simulations are finished on the condition of system health status (no faults), IES fault and gyro fault. The simulation results show that the proposed fault detection and isolation approach is correct and feasible.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"6 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129873644","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-06-08DOI: 10.1109/ISSCAA.2010.5633585
Kan Xie, Yu Liu
An aerodynamic study is presented for controlled canard configuration of a target unmanned air vehicle (TUAV) at cruise Mach number between 0.7 and 0.85, using a solid rocket motor as power. The analysis was focused on the longitudinal wind tunnel test data for learning complicated controlled canard-elements interactions and canard vortex behavior. The canard vortex interaction with tail wing of initial configuration concept with a NACA0012 canard and the improved configuration with a NACA0007 canard were reviewed and discussed. The experiments prove that the stability and control characteristics of whole TUAV are sensitive to the thickness of canard in transonic peed regime because of different canard vortex intensity and effect generated. The flight experiment shows that the final improved controlled canard configuration satisfies the request of the control system.
{"title":"An experimental study of controlled canard for a solid rocket motor based unmanned air vehicle","authors":"Kan Xie, Yu Liu","doi":"10.1109/ISSCAA.2010.5633585","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633585","url":null,"abstract":"An aerodynamic study is presented for controlled canard configuration of a target unmanned air vehicle (TUAV) at cruise Mach number between 0.7 and 0.85, using a solid rocket motor as power. The analysis was focused on the longitudinal wind tunnel test data for learning complicated controlled canard-elements interactions and canard vortex behavior. The canard vortex interaction with tail wing of initial configuration concept with a NACA0012 canard and the improved configuration with a NACA0007 canard were reviewed and discussed. The experiments prove that the stability and control characteristics of whole TUAV are sensitive to the thickness of canard in transonic peed regime because of different canard vortex intensity and effect generated. The flight experiment shows that the final improved controlled canard configuration satisfies the request of the control system.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"9 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128566100","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-06-08DOI: 10.1109/ISSCAA.2010.5632731
Shuanghe Yu, Zhenqiang Yang, Siyuan Wang, Kai Zheng
This paper proposes a novel sensorless speed tracking control scheme for the permanent magnet synchronous motors (PMSM) with uncertain parameters. An angular speed observer is designed to achieve the purpose of sensorless speed estimation, and then a speed tracking controller is developed with the adaptive backstepping technique to deal with the parameter uncertainties and load variation in the PMSM system. The stability of the whole closed loop system is guaranteed under Lyapunov criterion. Performance of proposed controller is investigated under different dynamic operating conditions such as step changes in commands, step changes in load, and parameter variations. The results indicate the effectiveness of the scheme in terms of the speed tracking ability and robustness against parameter variations.
{"title":"Sensorless adaptive backstepping speed tracking control of uncertain permanent magnet synchronous motors","authors":"Shuanghe Yu, Zhenqiang Yang, Siyuan Wang, Kai Zheng","doi":"10.1109/ISSCAA.2010.5632731","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632731","url":null,"abstract":"This paper proposes a novel sensorless speed tracking control scheme for the permanent magnet synchronous motors (PMSM) with uncertain parameters. An angular speed observer is designed to achieve the purpose of sensorless speed estimation, and then a speed tracking controller is developed with the adaptive backstepping technique to deal with the parameter uncertainties and load variation in the PMSM system. The stability of the whole closed loop system is guaranteed under Lyapunov criterion. Performance of proposed controller is investigated under different dynamic operating conditions such as step changes in commands, step changes in load, and parameter variations. The results indicate the effectiveness of the scheme in terms of the speed tracking ability and robustness against parameter variations.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"7 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126955716","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Gaussian Mixture probability hypothesis density (GM-PHD) filter is a closed-form solution to the probability hypothesis density filter, which could estimate states and time-varying number of targets based on theory of random finite set. Probability multiple hypotheses tracking (PMHT) is a multi-target tracking algorithm combining data association and expectation-maximization. However, GM-PHD can not give trajectories of target because of its disability of providing identity of target. Furthermore, PMHT need known number of targets and several frames trajectories of targets at first which are difficult in practical application. Firstly, we propose track oriented PMHT tracker (TO-PMHTT), then an approach of data association combining the advantage of GM-PHD with TO-PMHTT is designed in this paper. GM-PHD acts as the pre-filter of TO-PMHTT when there are no crossing targets in the scenario, while interaction between GM-PHD and TO-PMHTT is performed when targets enter crossing zone. Computer simulation results show that the method can provide association for both separated and crossing targets tracking.
{"title":"Data association for GM-PHD with track oriented PMHT","authors":"Shicang Zhang, Jian-xun Li, Binyi Fan, Liangbin Wu","doi":"10.1109/ISSCAA.2010.5633037","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633037","url":null,"abstract":"Gaussian Mixture probability hypothesis density (GM-PHD) filter is a closed-form solution to the probability hypothesis density filter, which could estimate states and time-varying number of targets based on theory of random finite set. Probability multiple hypotheses tracking (PMHT) is a multi-target tracking algorithm combining data association and expectation-maximization. However, GM-PHD can not give trajectories of target because of its disability of providing identity of target. Furthermore, PMHT need known number of targets and several frames trajectories of targets at first which are difficult in practical application. Firstly, we propose track oriented PMHT tracker (TO-PMHTT), then an approach of data association combining the advantage of GM-PHD with TO-PMHTT is designed in this paper. GM-PHD acts as the pre-filter of TO-PMHTT when there are no crossing targets in the scenario, while interaction between GM-PHD and TO-PMHTT is performed when targets enter crossing zone. Computer simulation results show that the method can provide association for both separated and crossing targets tracking.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"24 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121817069","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-06-08DOI: 10.1109/ISSCAA.2010.5633387
Xinxin Yang, Xiong Luo, F. Sun, Fengge Wu, Huaping Liu
In recent years, dynamics model and control of space robot system are the hot topics in the research field. In this paper, a new dynamics model and control strategy of space robotic system with a flexible manipulator and a liquid fuel tank are investigated. Based on Lagrange equation method, the dynamics model of the space robotic system coupling with liquid sloshing, flexibility vibration and base movement is derived. The elastic deflection of the flexible manipulator is described by the assumed mode method and equivalent mechanical model is adopted instead of liquid sloshing under the environment of low-gravity. The inverse dynamics control algorithm combined with PD control method is performed to solve the trajectory tracking problem. Some simulation results are given to verify the effectiveness of the proposed method.
{"title":"Dynamic modeling and tracking control of fuel filled space robotic system with flexible manipulators","authors":"Xinxin Yang, Xiong Luo, F. Sun, Fengge Wu, Huaping Liu","doi":"10.1109/ISSCAA.2010.5633387","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633387","url":null,"abstract":"In recent years, dynamics model and control of space robot system are the hot topics in the research field. In this paper, a new dynamics model and control strategy of space robotic system with a flexible manipulator and a liquid fuel tank are investigated. Based on Lagrange equation method, the dynamics model of the space robotic system coupling with liquid sloshing, flexibility vibration and base movement is derived. The elastic deflection of the flexible manipulator is described by the assumed mode method and equivalent mechanical model is adopted instead of liquid sloshing under the environment of low-gravity. The inverse dynamics control algorithm combined with PD control method is performed to solve the trajectory tracking problem. Some simulation results are given to verify the effectiveness of the proposed method.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"95 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122396011","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-06-08DOI: 10.1109/ISSCAA.2010.5633239
Xiao-fang Wang, Hai Lin
Probability of penetration of image guided missile can increase greatly if the missile does terminal maneuver, but the terminal maneuver may have effects on target searching of missile. To study the effect the centroid model of missile doing typical terminal weaving maneuver was built and the model of target movement and parallel search law were built too. Based on the models the effect of terminal weaving maneuver on search area, movement speed of image on monitor screen and the probability of target entering the IFOV of seeker were analyzed through simulation. Simulation results show the effect on target searching of terminal weaving maneuver is little when image guided missile attacks the target with low velocity, which provides important reference for overall design of missile.
{"title":"Research on effect on target searching of image guided missile's terminal maneuver","authors":"Xiao-fang Wang, Hai Lin","doi":"10.1109/ISSCAA.2010.5633239","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633239","url":null,"abstract":"Probability of penetration of image guided missile can increase greatly if the missile does terminal maneuver, but the terminal maneuver may have effects on target searching of missile. To study the effect the centroid model of missile doing typical terminal weaving maneuver was built and the model of target movement and parallel search law were built too. Based on the models the effect of terminal weaving maneuver on search area, movement speed of image on monitor screen and the probability of target entering the IFOV of seeker were analyzed through simulation. Simulation results show the effect on target searching of terminal weaving maneuver is little when image guided missile attacks the target with low velocity, which provides important reference for overall design of missile.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"136 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122454658","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-06-08DOI: 10.1109/ISSCAA.2010.5633300
Xiao-Liang Wang, Ye Ma, Xue-xiong Shan
The dynamics and kinematics model is very important for the analysis of stability, manipulation and control of stratosphere airship. A full modeling approach that includes the computation of aerodynamics of airship and the added mass for the nonlinear dynamics simulation of stratosphere airships is proposed in this paper. In this approach, the aerodynamics of airship is calculated based on a panel method, an engineering estimation and theory approach. A new numerical method for calculating added masses of airship is developed by using the CFD method. This model can simulate the motion of stratosphere airships quickly and accurately.
{"title":"Modeling of stratosphere airship","authors":"Xiao-Liang Wang, Ye Ma, Xue-xiong Shan","doi":"10.1109/ISSCAA.2010.5633300","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633300","url":null,"abstract":"The dynamics and kinematics model is very important for the analysis of stability, manipulation and control of stratosphere airship. A full modeling approach that includes the computation of aerodynamics of airship and the added mass for the nonlinear dynamics simulation of stratosphere airships is proposed in this paper. In this approach, the aerodynamics of airship is calculated based on a panel method, an engineering estimation and theory approach. A new numerical method for calculating added masses of airship is developed by using the CFD method. This model can simulate the motion of stratosphere airships quickly and accurately.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"57 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122912050","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-06-08DOI: 10.1109/ISSCAA.2010.5632507
Zhang Xingyuan, Li Songjing, Li Jixiao
Due to the higher saturation magnetization and magnetoviscosity of magnetic fluids when exposed to a magnetic field, magnetic fluids are filled into the working gaps of a servo-valve torque motor to improve the dynamic performance of the torque motor in this paper. After the construction and working principle of a torque motor with magnetic fluids being introduced, the mathematical models are established. Simulation and experiments on the dynamic characteristics of the torque motor are carried out. Based on the experimental data and the mathematical model of the torque motor with magnetic fluids, the estimated values of the unknown parameters are obtained by a curve-fitting parameter identification method in the least-square sense.
{"title":"Parameter identification of a hydraulic servo-valve torque motor with magnetic fluids based on dynamic characteristics","authors":"Zhang Xingyuan, Li Songjing, Li Jixiao","doi":"10.1109/ISSCAA.2010.5632507","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632507","url":null,"abstract":"Due to the higher saturation magnetization and magnetoviscosity of magnetic fluids when exposed to a magnetic field, magnetic fluids are filled into the working gaps of a servo-valve torque motor to improve the dynamic performance of the torque motor in this paper. After the construction and working principle of a torque motor with magnetic fluids being introduced, the mathematical models are established. Simulation and experiments on the dynamic characteristics of the torque motor are carried out. Based on the experimental data and the mathematical model of the torque motor with magnetic fluids, the estimated values of the unknown parameters are obtained by a curve-fitting parameter identification method in the least-square sense.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"21 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133539279","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}
京公网安备 11010802042870号
京ICP备2023020795号-1
扫码关注我们
求助内容：
应助结果提醒方式：