Pub Date : 2006-05-08DOI: 10.1109/ISSCAA.2006.1627621
Hamid Reza Shaker, M. Samavat
This paper presents a parameter preserving controller order reduction method applied to HiMAT aircraft. The reduction method, is based on frequency balancing within operational bandwidth of the system. This method is of interest for practical controller reduction for HiMAT because in this context it is important to keep the accuracy of approximation as high as possible without sacrificing the important system properties, like stability and passivity. Numerical results show that the approximation error is reduced
{"title":"Accuracy enhancement in HiMAT aircraft controller reduction","authors":"Hamid Reza Shaker, M. Samavat","doi":"10.1109/ISSCAA.2006.1627621","DOIUrl":"https://doi.org/10.1109/ISSCAA.2006.1627621","url":null,"abstract":"This paper presents a parameter preserving controller order reduction method applied to HiMAT aircraft. The reduction method, is based on frequency balancing within operational bandwidth of the system. This method is of interest for practical controller reduction for HiMAT because in this context it is important to keep the accuracy of approximation as high as possible without sacrificing the important system properties, like stability and passivity. Numerical results show that the approximation error is reduced","PeriodicalId":275436,"journal":{"name":"2006 1st International Symposium on Systems and Control in Aerospace and Astronautics","volume":"31 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2006-05-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131333489","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 : 2006-05-08DOI: 10.1109/ISSCAA.2006.1627639
D. Xue, Xibin Cao, Yunhua Wu
Autonomous formation flying is an important technology for the future space missions involving multiple satellites, and one of the key requirements of formation flying is accurate relative navigation. This paper develops an efficient approach of autonomous relative orbit determination for formation flying satellite. In view of that some formation flying satellites work at the orbits which are beyond the range of a GPS signal, inter-satellite measurements by the devices onboard the satellite instead of GPS measurements are chosen to perform this relative navigation. Several estimator architectures and associated algorithms are presented, among which the decentralized architecture is chosen because it can reduce the computational load as well as the communication requirements among the satellites, accordingly the orbit states estimation is achieved through a decentralized Schmidt-Kalman filter design. The simulation results verify the validity of this navigation method
{"title":"Decentralized determination of relative orbit for formation flying satellite","authors":"D. Xue, Xibin Cao, Yunhua Wu","doi":"10.1109/ISSCAA.2006.1627639","DOIUrl":"https://doi.org/10.1109/ISSCAA.2006.1627639","url":null,"abstract":"Autonomous formation flying is an important technology for the future space missions involving multiple satellites, and one of the key requirements of formation flying is accurate relative navigation. This paper develops an efficient approach of autonomous relative orbit determination for formation flying satellite. In view of that some formation flying satellites work at the orbits which are beyond the range of a GPS signal, inter-satellite measurements by the devices onboard the satellite instead of GPS measurements are chosen to perform this relative navigation. Several estimator architectures and associated algorithms are presented, among which the decentralized architecture is chosen because it can reduce the computational load as well as the communication requirements among the satellites, accordingly the orbit states estimation is achieved through a decentralized Schmidt-Kalman filter design. The simulation results verify the validity of this navigation method","PeriodicalId":275436,"journal":{"name":"2006 1st International Symposium on Systems and Control in Aerospace and Astronautics","volume":"2 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2006-05-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128867986","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 : 2006-05-08DOI: 10.1109/ISSCAA.2006.1627500
Fengxia Xu, Zhongda Lu, Ming Zeng, B. Su
The velocity system and position system have a kind of nonlinear disturbance; it is correlated with some positions and changes periodically with the position. The paper presents the model of velocity system and position system with position dependent periodic disturbance, deduces the condition of position dependent periodic disturbance translating into time dependent periodic error, proposes the condition and method of reject nonlinear disturbance with multi-period finite-dimensional repetitive control, and proves this method can improve the velocity precision and position precision of system
{"title":"Rejection of nonlinear disturbance with multi-period finite-dimensional repetitive control","authors":"Fengxia Xu, Zhongda Lu, Ming Zeng, B. Su","doi":"10.1109/ISSCAA.2006.1627500","DOIUrl":"https://doi.org/10.1109/ISSCAA.2006.1627500","url":null,"abstract":"The velocity system and position system have a kind of nonlinear disturbance; it is correlated with some positions and changes periodically with the position. The paper presents the model of velocity system and position system with position dependent periodic disturbance, deduces the condition of position dependent periodic disturbance translating into time dependent periodic error, proposes the condition and method of reject nonlinear disturbance with multi-period finite-dimensional repetitive control, and proves this method can improve the velocity precision and position precision of system","PeriodicalId":275436,"journal":{"name":"2006 1st International Symposium on Systems and Control in Aerospace and Astronautics","volume":"6 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2006-05-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125521868","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 : 2006-05-08DOI: 10.1109/ISSCAA.2006.1627617
Li Li, Qing-shuang Zeng, Yonglin Jiang, Hongwei Xia
Tracking technique is one of the most active research topics in the domain of computer vision currently, and motion analysis presents the essence of moving object tracking in video. This paper proposed a novel method for tracking based on spatio-temporal motion segmentation. First, successively layered moving object silhouettes encode system time termed the timed motion history image for motion trajectory representation. Then, a spatio-temporal segmentation procedure is used to labeling motion regions by estimating density gradient in spatial-temporal domain. Several examples are shown to illustrate that this solution has high effectiveness and robust nature, providing practical tools for moving object tracking in real time surveillance system
{"title":"Spatio-temporal motion segmentation and tracking under realistic condition","authors":"Li Li, Qing-shuang Zeng, Yonglin Jiang, Hongwei Xia","doi":"10.1109/ISSCAA.2006.1627617","DOIUrl":"https://doi.org/10.1109/ISSCAA.2006.1627617","url":null,"abstract":"Tracking technique is one of the most active research topics in the domain of computer vision currently, and motion analysis presents the essence of moving object tracking in video. This paper proposed a novel method for tracking based on spatio-temporal motion segmentation. First, successively layered moving object silhouettes encode system time termed the timed motion history image for motion trajectory representation. Then, a spatio-temporal segmentation procedure is used to labeling motion regions by estimating density gradient in spatial-temporal domain. Several examples are shown to illustrate that this solution has high effectiveness and robust nature, providing practical tools for moving object tracking in real time surveillance system","PeriodicalId":275436,"journal":{"name":"2006 1st International Symposium on Systems and Control in Aerospace and Astronautics","volume":"29 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2006-05-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126547029","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 : 2006-05-08DOI: 10.1109/ISSCAA.2006.1627456
J. Shang
The evolution of digital modulation signals is reviewed in this article firstly, including PSK, FSK, QPSK, OQPSK, MSK etc. Secondly the modulation and demodulation of MSK are taken as a focal point and a new efficient demodulation method based on instantaneous phase information is put forward. Thirdly simulation validates the new method
{"title":"A new software demodulation method for MSK signal based on phase information","authors":"J. Shang","doi":"10.1109/ISSCAA.2006.1627456","DOIUrl":"https://doi.org/10.1109/ISSCAA.2006.1627456","url":null,"abstract":"The evolution of digital modulation signals is reviewed in this article firstly, including PSK, FSK, QPSK, OQPSK, MSK etc. Secondly the modulation and demodulation of MSK are taken as a focal point and a new efficient demodulation method based on instantaneous phase information is put forward. Thirdly simulation validates the new method","PeriodicalId":275436,"journal":{"name":"2006 1st International Symposium on Systems and Control in Aerospace and Astronautics","volume":"25 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2006-05-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122307942","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 : 2006-05-08DOI: 10.1109/ISSCAA.2006.1627415
Lin Huang, W. Jing
The stability problems of two magnetic control systems are discussed. One uses a three-axis magnetic actuator only; the other includes an additional momentum-biased wheel. The so-called orbit-averaged magnetic controllers, derived from the orbit-averaged magnetic field, show an ability to ensure the global attitude stabilization. This is supported theoretically by the averaging method and Lyapunov theories, and also illustrated by the simulations executed for orbits of different inclinations. The results show that the second system can achieve considerably high steady-state control accuracy in all cases
{"title":"Attitude stabilization of averaging magnetic torque","authors":"Lin Huang, W. Jing","doi":"10.1109/ISSCAA.2006.1627415","DOIUrl":"https://doi.org/10.1109/ISSCAA.2006.1627415","url":null,"abstract":"The stability problems of two magnetic control systems are discussed. One uses a three-axis magnetic actuator only; the other includes an additional momentum-biased wheel. The so-called orbit-averaged magnetic controllers, derived from the orbit-averaged magnetic field, show an ability to ensure the global attitude stabilization. This is supported theoretically by the averaging method and Lyapunov theories, and also illustrated by the simulations executed for orbits of different inclinations. The results show that the second system can achieve considerably high steady-state control accuracy in all cases","PeriodicalId":275436,"journal":{"name":"2006 1st International Symposium on Systems and Control in Aerospace and Astronautics","volume":"7 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2006-05-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126605187","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 : 2006-05-08DOI: 10.1109/ISSCAA.2006.1627709
Songchen Han, Liyuan Cheng, Huiyan Tong
In order to avoid collision, aircraft can not get closer to each other than a predefined safety distance in free flight. With noncooperative facts and unexpected conditions, the problem of air traffic conflict resolution becomes very complex. In this paper, based on the famous pursue-evade qualitative differential game barrier theory, considering the vehicle attempting to avoid collision as an "evader", and the noncooperative adjacent vehicle as a "pursuer", we firstly extend the two aircraft conflict resolution problem to three-dimensional space. Based on a simulation example, the three-dimensional barrier, which representing the two vehicles' optimal trajectory is obtained. The feasibility of studying the problem of conflict resolution in three-dimensional space with differential game theory is proved by this result
{"title":"Noncooperative conflict resolution using differential game","authors":"Songchen Han, Liyuan Cheng, Huiyan Tong","doi":"10.1109/ISSCAA.2006.1627709","DOIUrl":"https://doi.org/10.1109/ISSCAA.2006.1627709","url":null,"abstract":"In order to avoid collision, aircraft can not get closer to each other than a predefined safety distance in free flight. With noncooperative facts and unexpected conditions, the problem of air traffic conflict resolution becomes very complex. In this paper, based on the famous pursue-evade qualitative differential game barrier theory, considering the vehicle attempting to avoid collision as an \"evader\", and the noncooperative adjacent vehicle as a \"pursuer\", we firstly extend the two aircraft conflict resolution problem to three-dimensional space. Based on a simulation example, the three-dimensional barrier, which representing the two vehicles' optimal trajectory is obtained. The feasibility of studying the problem of conflict resolution in three-dimensional space with differential game theory is proved by this result","PeriodicalId":275436,"journal":{"name":"2006 1st International Symposium on Systems and Control in Aerospace and Astronautics","volume":"46 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2006-05-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114194814","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 : 2006-05-08DOI: 10.1109/ISSCAA.2006.1627447
Wei Jiang, G. Yi, Qingshuang Zeng, Lixian Zhang
In this paper, the applicability and advantage of tracking differentiator (TD) filter in dynamically tuned gyro (DTG) north seeking system is presented. According to the working principle of north seeking system, the system structure is first designed based on DSP. Then TD filter with discrete form, which is easily realized in DSP, is adopted to eliminate both the noise and disturbance in the output signal of gyro. Practical measurement data are given to show that the north-seeking accuracy is improved effectively, and the seeking time is shortened by TD filter
{"title":"Application of TD filter in DTG north seeking system","authors":"Wei Jiang, G. Yi, Qingshuang Zeng, Lixian Zhang","doi":"10.1109/ISSCAA.2006.1627447","DOIUrl":"https://doi.org/10.1109/ISSCAA.2006.1627447","url":null,"abstract":"In this paper, the applicability and advantage of tracking differentiator (TD) filter in dynamically tuned gyro (DTG) north seeking system is presented. According to the working principle of north seeking system, the system structure is first designed based on DSP. Then TD filter with discrete form, which is easily realized in DSP, is adopted to eliminate both the noise and disturbance in the output signal of gyro. Practical measurement data are given to show that the north-seeking accuracy is improved effectively, and the seeking time is shortened by TD filter","PeriodicalId":275436,"journal":{"name":"2006 1st International Symposium on Systems and Control in Aerospace and Astronautics","volume":"23 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2006-05-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116220282","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 : 2006-05-08DOI: 10.1109/ISSCAA.2006.1627409
Rongjun Mu, Siyuan Rong, Naigang Cui
A specific integrated navigation system, INS/GPS/Doppler/CNS was analyzed. The characteristic, model and principle of federated filtering algorithm with FDIR (fault detect/isolate/rescale) capability were researched to satisfy requests of high reliability and fault-tolerant ability which were put forward by multiple sensor navigation system. Moreover, application model and FDIR model were proposed for fusion system which are built-up by local systems and supervised by federated filter. Based on these two models, local multiple fading fault-tolerant filter and FDIR strategy for general system are presented. Effectiveness and practicability rise after the validation by simulations for this two-stage (local(s)+general) fault-tolerant multiple sensor fusion system
{"title":"Federated filter with strengthened FDIR capability for multiple sensor navigation system","authors":"Rongjun Mu, Siyuan Rong, Naigang Cui","doi":"10.1109/ISSCAA.2006.1627409","DOIUrl":"https://doi.org/10.1109/ISSCAA.2006.1627409","url":null,"abstract":"A specific integrated navigation system, INS/GPS/Doppler/CNS was analyzed. The characteristic, model and principle of federated filtering algorithm with FDIR (fault detect/isolate/rescale) capability were researched to satisfy requests of high reliability and fault-tolerant ability which were put forward by multiple sensor navigation system. Moreover, application model and FDIR model were proposed for fusion system which are built-up by local systems and supervised by federated filter. Based on these two models, local multiple fading fault-tolerant filter and FDIR strategy for general system are presented. Effectiveness and practicability rise after the validation by simulations for this two-stage (local(s)+general) fault-tolerant multiple sensor fusion system","PeriodicalId":275436,"journal":{"name":"2006 1st International Symposium on Systems and Control in Aerospace and Astronautics","volume":"218 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2006-05-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116629651","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 : 2006-05-08DOI: 10.1109/ISSCAA.2006.1627596
Qiyu Wang, Jianping Yuan, Zhanxia Zhu
Because of its payload's work characteristic, it requires much higher precision in Earth observation satellite's attitude control systems than others. Most Earth observation satellites use zero-momentum three-axis stabilization control method. This paper investigates this control method in satellite control system, deducing the dynamics and kinematics of satellite attitude's model expressed by attitude error quaternion, applying PID control method in this model, and then simulating and evaluating the method preliminarily. The results show that the method can achieve the require precision quickly
{"title":"The application of error quaternion and PID control method in Earth observation satellite's attitude control system","authors":"Qiyu Wang, Jianping Yuan, Zhanxia Zhu","doi":"10.1109/ISSCAA.2006.1627596","DOIUrl":"https://doi.org/10.1109/ISSCAA.2006.1627596","url":null,"abstract":"Because of its payload's work characteristic, it requires much higher precision in Earth observation satellite's attitude control systems than others. Most Earth observation satellites use zero-momentum three-axis stabilization control method. This paper investigates this control method in satellite control system, deducing the dynamics and kinematics of satellite attitude's model expressed by attitude error quaternion, applying PID control method in this model, and then simulating and evaluating the method preliminarily. The results show that the method can achieve the require precision quickly","PeriodicalId":275436,"journal":{"name":"2006 1st International Symposium on Systems and Control in Aerospace and Astronautics","volume":"17 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2006-05-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121705196","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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