Pub Date : 2010-06-08DOI: 10.1109/ISSCAA.2010.5633205
Xu Mingliang, Li Luhua, Tang Guojian, Chen Kejun
Hypersonic glide-cruise vehicle is a new concept craft which glides with hypersonic velocity, and can cruise at a constant height apart from the ground recur to the engine. In the paper two guidance approaches of this craft are studied during cruise and attack phases respectively. Based on the established dynamics model, a novel guidance approach for cruise state holding and bank-to-turn control when passing through the waypoints is proposed. The optimal transformative proportion guidance law is adopted during the attack phase. The approaches studied are validated with a three-dimension simulation programme, and all war indexes requirements are meet.
{"title":"Study on guidance approaches of hypersonic glide-cruise vehicle during cruise and attack phases","authors":"Xu Mingliang, Li Luhua, Tang Guojian, Chen Kejun","doi":"10.1109/ISSCAA.2010.5633205","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633205","url":null,"abstract":"Hypersonic glide-cruise vehicle is a new concept craft which glides with hypersonic velocity, and can cruise at a constant height apart from the ground recur to the engine. In the paper two guidance approaches of this craft are studied during cruise and attack phases respectively. Based on the established dynamics model, a novel guidance approach for cruise state holding and bank-to-turn control when passing through the waypoints is proposed. The optimal transformative proportion guidance law is adopted during the attack phase. The approaches studied are validated with a three-dimension simulation programme, and all war indexes requirements are meet.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"75 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":"116594529","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.2010.5633349
Zhang Yan, Wu Wenqi, Cao Ju-liang
Rated biased RLG is used in the north-finder based on a continuous rotation platform. Along with the rotating platform, the input axis of RLG relative to the earth rotation rate vector periodically changes. In this way, the measurement error of RLG is modulated in every direction. The cross-correlation analysis method is used for getting the azimuth angle. Considering the periodicity of gyro outputs, a digital filter is designed to decrease the influence of quantization error of RLG and some other wideband error sources. Experiment results show that the “cross-correlation analysis + filter” method can markedly increase the precision of the north-finder.
{"title":"The study of north-finder based on rate biased RLG","authors":"Zhang Yan, Wu Wenqi, Cao Ju-liang","doi":"10.1109/ISSCAA.2010.5633349","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633349","url":null,"abstract":"Rated biased RLG is used in the north-finder based on a continuous rotation platform. Along with the rotating platform, the input axis of RLG relative to the earth rotation rate vector periodically changes. In this way, the measurement error of RLG is modulated in every direction. The cross-correlation analysis method is used for getting the azimuth angle. Considering the periodicity of gyro outputs, a digital filter is designed to decrease the influence of quantization error of RLG and some other wideband error sources. Experiment results show that the “cross-correlation analysis + filter” method can markedly increase the precision of the north-finder.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"116 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":"116624165","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.2010.5632541
Wu Wei, Huang Ye
The computational complexity of multi-dimension assignment algorithm, which can be used to solve multi-sensor multi-target location and tracking problem based on time difference of arrival (TDOA) measurements, will increase exponentially with the scale of assignment problem. By the fact that multiple emitters usually exist separately in the surveillance space, the clustering technique is used to partition the global multiple dimension assignment problem into some local sub problem for reducing the computational complexity. Its efficiency has been confirmed by computer simulations.
{"title":"Algorithm of multiple emitters tracking based on TDOA measurements and clustering technique","authors":"Wu Wei, Huang Ye","doi":"10.1109/ISSCAA.2010.5632541","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632541","url":null,"abstract":"The computational complexity of multi-dimension assignment algorithm, which can be used to solve multi-sensor multi-target location and tracking problem based on time difference of arrival (TDOA) measurements, will increase exponentially with the scale of assignment problem. By the fact that multiple emitters usually exist separately in the surveillance space, the clustering technique is used to partition the global multiple dimension assignment problem into some local sub problem for reducing the computational complexity. Its efficiency has been confirmed by computer simulations.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"177 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":"116872028","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.2010.5632899
Tao Yang, G. Radice, Weihua Zhang
A strategy for trajectory design, motion camouflage, is introduced within the context of orbital relative motion. At first the equations of orbital motion for this approach are developed. The control strategy is then implemented using both an impulsive and continuous approach. A number of parameters are then optimized to minimize the fuel mass. The simulation results reveal that the predator successfully reaches the target and thus proving the validity of this approach.
{"title":"Motion camouflage for in-orbit maneuvers","authors":"Tao Yang, G. Radice, Weihua Zhang","doi":"10.1109/ISSCAA.2010.5632899","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632899","url":null,"abstract":"A strategy for trajectory design, motion camouflage, is introduced within the context of orbital relative motion. At first the equations of orbital motion for this approach are developed. The control strategy is then implemented using both an impulsive and continuous approach. A number of parameters are then optimized to minimize the fuel mass. The simulation results reveal that the predator successfully reaches the target and thus proving the validity of this approach.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"32 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":"129764382","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.2010.5632401
Yan Yan, Shuanghe Yu, Jia-lu Du, Kai Zheng
In this work, a switched control law is proposed to make the desired set point of an underactuated surface vessel finite-time stabilization. The control law is separated into three actions. Each action makes the system have a double integrator subsystem and we use a finite-time controller to achieve a certain objective. In order to overcome the difficulties of measuring the linear and angular velocities of underactuated surface vessels, in the condition that only the position and orientation are measurable, we present second-order sliding-mode observers of the velocity u, v, and r for the vessels. Simulation results show that the control law is effective.
{"title":"Observer based finite-time switched controller of an underactuated surface vessel","authors":"Yan Yan, Shuanghe Yu, Jia-lu Du, Kai Zheng","doi":"10.1109/ISSCAA.2010.5632401","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632401","url":null,"abstract":"In this work, a switched control law is proposed to make the desired set point of an underactuated surface vessel finite-time stabilization. The control law is separated into three actions. Each action makes the system have a double integrator subsystem and we use a finite-time controller to achieve a certain objective. In order to overcome the difficulties of measuring the linear and angular velocities of underactuated surface vessels, in the condition that only the position and orientation are measurable, we present second-order sliding-mode observers of the velocity u, v, and r for the vessels. Simulation results show that the control law is effective.","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":"124577336","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.2010.5632358
Liu Hao, Shen Yi
A robust controller design method for high-maneuverable kinetic kill vehicle (KKV) whose attitude is controlled by combining aerodynamic tail fins and direct force is presented in this paper, which is a new algorithm based on adaptive approximation variable structure control (AAVSC) theory. Using this approach chatting problem which is due to the presence of infinite frequency switching function can be solved basically. In addition, the boundaries of uncertainties and disturbances, whose deterministic structures are known exactly, can be obtained easily by using the technology of the on-line identification, which will make the compound control systems remain stable. Theoretical analysis and numerical simulation results show that adaptive approximation variable structure control law is robust against parameter perturbations and disturbances. Due to the effect of direct force, the response time can be dramatically shortened; therefore, the rapid response requirements for KKV can be met.
{"title":"Compound control systems design for KKV based on the theory of adaptive approximate variable structure","authors":"Liu Hao, Shen Yi","doi":"10.1109/ISSCAA.2010.5632358","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632358","url":null,"abstract":"A robust controller design method for high-maneuverable kinetic kill vehicle (KKV) whose attitude is controlled by combining aerodynamic tail fins and direct force is presented in this paper, which is a new algorithm based on adaptive approximation variable structure control (AAVSC) theory. Using this approach chatting problem which is due to the presence of infinite frequency switching function can be solved basically. In addition, the boundaries of uncertainties and disturbances, whose deterministic structures are known exactly, can be obtained easily by using the technology of the on-line identification, which will make the compound control systems remain stable. Theoretical analysis and numerical simulation results show that adaptive approximation variable structure control law is robust against parameter perturbations and disturbances. Due to the effect of direct force, the response time can be dramatically shortened; therefore, the rapid response requirements for KKV can be met.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"36 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":"127006853","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.2010.5633022
Haibin Sun, Shihua Li, S. Fei
In this paper, a composite control method, consisting of a feedforward compensation part based on disturbance observer (DOB) and a feedback regulation part based on finite time controller, is proposed for 6DOF spacecraft formation control. The design of the composite controller can be divided into two steps: firstly, a continuous finite time controller is designed to stabilize the closed-loop spacecraft formation control system to a set of two equilibria in finite time in the absence of disturbances; secondly, considering the presence of external disturbances, a DOB is introduced to estimate unknown disturbances. The dynamic and disturbance rejection performances of the closed-loop spacecraft formation control system can be improved. A numerical example is provided to demonstrate the effectiveness of the proposed approach.
{"title":"Spacecraft formation control in 6DOF based on finite-time control and disturbance observer","authors":"Haibin Sun, Shihua Li, S. Fei","doi":"10.1109/ISSCAA.2010.5633022","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633022","url":null,"abstract":"In this paper, a composite control method, consisting of a feedforward compensation part based on disturbance observer (DOB) and a feedback regulation part based on finite time controller, is proposed for 6DOF spacecraft formation control. The design of the composite controller can be divided into two steps: firstly, a continuous finite time controller is designed to stabilize the closed-loop spacecraft formation control system to a set of two equilibria in finite time in the absence of disturbances; secondly, considering the presence of external disturbances, a DOB is introduced to estimate unknown disturbances. The dynamic and disturbance rejection performances of the closed-loop spacecraft formation control system can be improved. A numerical example is provided to demonstrate the effectiveness of the proposed approach.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"54 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":"123843724","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.2010.5633374
Wang Guo-hua, Jiang Qin-bo, Xu Jian-feng
Wideband spectrum estimation is very important for wideband wireless communication systems, especially for military communication system. The concept and the design method of the adaptive wideband spectrum estimation are put forward in this paper. Firstly, the wideband spectrum is estimated by using the wavelet packet decomposition. Then the characteristic noise of the independent signals exist in the wideband spectrum is produced by using the wavelet packet synthesis. Lastly the filters or trap filters, which are used to extract or trap signals, are designed based on LMS adaptive algorithm. The adaptive wideband spectrum estimation will be widely used in the wideband systems because of its real-time estimation ability and its good adaptability.
{"title":"Adaptive wideband spectrum estimation based on wavelet packet","authors":"Wang Guo-hua, Jiang Qin-bo, Xu Jian-feng","doi":"10.1109/ISSCAA.2010.5633374","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633374","url":null,"abstract":"Wideband spectrum estimation is very important for wideband wireless communication systems, especially for military communication system. The concept and the design method of the adaptive wideband spectrum estimation are put forward in this paper. Firstly, the wideband spectrum is estimated by using the wavelet packet decomposition. Then the characteristic noise of the independent signals exist in the wideband spectrum is produced by using the wavelet packet synthesis. Lastly the filters or trap filters, which are used to extract or trap signals, are designed based on LMS adaptive algorithm. The adaptive wideband spectrum estimation will be widely used in the wideband systems because of its real-time estimation ability and its good adaptability.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"39 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":"116492488","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.2010.5633951
Yong Feng, Hongyu Shi, Xinghuo Yu
This paper proposes an observer based on the nonsingular terminal sliding mode (NTSM) method and the high-order sliding mode (HOSM) method for estimating the rotor speed and the rotor flux in the induction motor control system. A terminal sliding mode observer is designed to estimate the rotor speed and the rotor flux of the motor system with fast convergence and better tracking precision. A high-order sliding mode control law is utilized to guarantee the stability of the observer and eliminate the chattering. The simulation results show that the proposed method can converge to actual value quickly with high precision.
{"title":"A sliding mode observer design method for induction motor control system","authors":"Yong Feng, Hongyu Shi, Xinghuo Yu","doi":"10.1109/ISSCAA.2010.5633951","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633951","url":null,"abstract":"This paper proposes an observer based on the nonsingular terminal sliding mode (NTSM) method and the high-order sliding mode (HOSM) method for estimating the rotor speed and the rotor flux in the induction motor control system. A terminal sliding mode observer is designed to estimate the rotor speed and the rotor flux of the motor system with fast convergence and better tracking precision. A high-order sliding mode control law is utilized to guarantee the stability of the observer and eliminate the chattering. The simulation results show that the proposed method can converge to actual value quickly with high precision.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"69 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":"121453870","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.2010.5633312
Rong Chen, Yaowen Feng, Xutao Li
Three Gorges Project Management System (TGPMS) is a large scale, integrated project management system which is designed for construction management in Three Gorges Project, and it has already been developed to support cross-area, multi-organization applications with the progress of project, and the extending of enterprise business. It is valuable for optimizing the high availability of information system by reviewing the migration road of TGPMS architecture and discussing system high availability design and implementation.
{"title":"High availability design and implementation of TGPMS system","authors":"Rong Chen, Yaowen Feng, Xutao Li","doi":"10.1109/ISSCAA.2010.5633312","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633312","url":null,"abstract":"Three Gorges Project Management System (TGPMS) is a large scale, integrated project management system which is designed for construction management in Three Gorges Project, and it has already been developed to support cross-area, multi-organization applications with the progress of project, and the extending of enterprise business. It is valuable for optimizing the high availability of information system by reviewing the migration road of TGPMS architecture and discussing system high availability design and implementation.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"70 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":"124381412","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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