Pub Date : 2010-06-08DOI: 10.1109/ISSCAA.2010.5634044
Jie Li, T. Chai, Lisheng Fan, Li Pan, Jingkuan Gong
In this paper, a k-covered wireless sensor network optimization problem is considered to improve the quality of surveillance. In order to maximize the coverage area of wireless sensor network with k-covered hotspots and connected sensor nodes, a novel stochastic optimization technique named particle filter optimization (PFO) is proposed to obtain an optimal sensor placement. Simulation results indicate that the proposed algorithm is effective and efficient. Finally, it is demonstrated that the proposed algorithm exhibits a significant performance improvement over other benchmark methods, for example, genetic algorithm (GA) and particle swarm optimization (PSO) method.
{"title":"K-covered wireless sensor network optimization","authors":"Jie Li, T. Chai, Lisheng Fan, Li Pan, Jingkuan Gong","doi":"10.1109/ISSCAA.2010.5634044","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5634044","url":null,"abstract":"In this paper, a k-covered wireless sensor network optimization problem is considered to improve the quality of surveillance. In order to maximize the coverage area of wireless sensor network with k-covered hotspots and connected sensor nodes, a novel stochastic optimization technique named particle filter optimization (PFO) is proposed to obtain an optimal sensor placement. Simulation results indicate that the proposed algorithm is effective and efficient. Finally, it is demonstrated that the proposed algorithm exhibits a significant performance improvement over other benchmark methods, for example, genetic algorithm (GA) and particle swarm optimization (PSO) method.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"18 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":"133573498","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.2010.5632723
H. Ao, Hongyuan Jiang, Hongyu Zhao
The application of porous characteristics of Metal Rubber (MR) material in sealing structure was studied in the paper. A sealing O-ring of MR was designed and tested in the sealing experimental setup. The linear expansion of MR material was studied. The sealing performance of MR O-ring was modeled and simulated considering the geometric dimension of the sealing slot and the cross section of rings. The transfer coefficient of pressure force from radial direction to axial direction was obtained and verified experimentally. The good agreement of the experimental results and the simulated results indicates the suitability of the calculated method for determining the sealing behavior with O-rings.
{"title":"Modeling and experimental study of linear expansion characteristics of metallic rubber material in sealing structure","authors":"H. Ao, Hongyuan Jiang, Hongyu Zhao","doi":"10.1109/ISSCAA.2010.5632723","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632723","url":null,"abstract":"The application of porous characteristics of Metal Rubber (MR) material in sealing structure was studied in the paper. A sealing O-ring of MR was designed and tested in the sealing experimental setup. The linear expansion of MR material was studied. The sealing performance of MR O-ring was modeled and simulated considering the geometric dimension of the sealing slot and the cross section of rings. The transfer coefficient of pressure force from radial direction to axial direction was obtained and verified experimentally. The good agreement of the experimental results and the simulated results indicates the suitability of the calculated method for determining the sealing behavior with O-rings.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"35 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":"133593680","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.2010.5633358
Wu Wei
The performance of multitarget tracking in clutter can be improved by using higher accuracy data association algorithm and more efficient state estimation method. This paper presents a novel fixed-lag TSDA-AI smoothing algorithm, which enhances the accuracy of state estimation by using fixed-lag smoothing, and improves the probability of real “measurement-target” combination by using two-scan measurements and the associated amplitude feature in the data association method. Its efficiency has been confirmed by computer simulations.
{"title":"Multitarget tracking in clutter using two-scan data association algorithm and fixed-lag smoothing","authors":"Wu Wei","doi":"10.1109/ISSCAA.2010.5633358","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633358","url":null,"abstract":"The performance of multitarget tracking in clutter can be improved by using higher accuracy data association algorithm and more efficient state estimation method. This paper presents a novel fixed-lag TSDA-AI smoothing algorithm, which enhances the accuracy of state estimation by using fixed-lag smoothing, and improves the probability of real “measurement-target” combination by using two-scan measurements and the associated amplitude feature in the data association method. 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":"13 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":"122200700","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.2010.5633417
Fuhai Zhang, Yili Fu, Shibo Yan, Shuguo Wang
In recent years, research on space robotics has attracted considerable attention. Kinematics of the free-flying or free-floating space manipulator system, including a spacecraft and a manipulator mounted on the spacecraft, is a significant problem. In free-floating work mode, the spacecraft will move freely in response to the disturbances caused by the manipulator motions. From the view of application, change of the spacecraft attitude for the space manipulator system is not desirable. Therefore, it is of significance to adopt the free-floating with zero-disturbance spacecraft attitude work mode. This paper presents an overview of the kinematics of the space manipulator system. Position and velocity kinematics solutions in three work modes are analyzed. The kinematics differences among the three work modes are formulated. The simulation results validate the effectiveness of the kinematics solutions in the three work modes.
{"title":"Kinematics and simulations of space manipulator in three work modes","authors":"Fuhai Zhang, Yili Fu, Shibo Yan, Shuguo Wang","doi":"10.1109/ISSCAA.2010.5633417","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633417","url":null,"abstract":"In recent years, research on space robotics has attracted considerable attention. Kinematics of the free-flying or free-floating space manipulator system, including a spacecraft and a manipulator mounted on the spacecraft, is a significant problem. In free-floating work mode, the spacecraft will move freely in response to the disturbances caused by the manipulator motions. From the view of application, change of the spacecraft attitude for the space manipulator system is not desirable. Therefore, it is of significance to adopt the free-floating with zero-disturbance spacecraft attitude work mode. This paper presents an overview of the kinematics of the space manipulator system. Position and velocity kinematics solutions in three work modes are analyzed. The kinematics differences among the three work modes are formulated. The simulation results validate the effectiveness of the kinematics solutions in the three work modes.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"22 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":"130449409","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.2010.5632307
W. Liang, Zhenqing Wang, Pengcheng Lin
The existence of viscosity effect at the interface of double dissimilar materials has an important impact to the distribution of interface crack-tip field and the properties variety of the interface itself. The singular is considered in crack-tip, and the elastic-viscoplastic quasi-static propagating governing equations of double dissimilar materials at interface crack-tip field are established. The displacement potential function and boundary condition of interface crack-tip are introduced and the numerical analysis of rigid-elastic viscoplastic interface for mode III are worked out. The stress-strain fields are obtained at the crack-tip and the variations of solutions are discussed according to each parameter. The numerical results show that the viscosity effect is a main factor of interface propagating crack-tip field, and the interface crack-tip is a viscoplastic field that is governed by viscosity coefficient, Mach number and singular factor.
{"title":"The elastic-viscoplastic field near mode iii dynamic propagating crack-tip of interface in double dissimilar materials","authors":"W. Liang, Zhenqing Wang, Pengcheng Lin","doi":"10.1109/ISSCAA.2010.5632307","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632307","url":null,"abstract":"The existence of viscosity effect at the interface of double dissimilar materials has an important impact to the distribution of interface crack-tip field and the properties variety of the interface itself. The singular is considered in crack-tip, and the elastic-viscoplastic quasi-static propagating governing equations of double dissimilar materials at interface crack-tip field are established. The displacement potential function and boundary condition of interface crack-tip are introduced and the numerical analysis of rigid-elastic viscoplastic interface for mode III are worked out. The stress-strain fields are obtained at the crack-tip and the variations of solutions are discussed according to each parameter. The numerical results show that the viscosity effect is a main factor of interface propagating crack-tip field, and the interface crack-tip is a viscoplastic field that is governed by viscosity coefficient, Mach number and singular factor.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"8 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":"130722464","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.2010.5632396
E. Atkins
Unmanned Air Systems (UAS) have numerous applications. Commercial potential in particular will not be realized until a comprehensive strategy is developed for safely and fully integrating UAS into an airspace currently dominated by commercial transport operations. This paper overviews a challenging benchmark application, on-demand surveillance over a densely-populated urban region, then presents a spectrum of risks that might be encountered. We describe novel risk mitigation criteria for small UAS that focus not on vehicle preservation but instead on minimizing risk of harm to people and property on the ground as well as to higher-value airborne assets. We conclude with a case study in which wind shear and turbulence in an urban canyon require a small UAS to execute an unplanned landing.
{"title":"Risk identification and management for safe UAS operation","authors":"E. Atkins","doi":"10.1109/ISSCAA.2010.5632396","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632396","url":null,"abstract":"Unmanned Air Systems (UAS) have numerous applications. Commercial potential in particular will not be realized until a comprehensive strategy is developed for safely and fully integrating UAS into an airspace currently dominated by commercial transport operations. This paper overviews a challenging benchmark application, on-demand surveillance over a densely-populated urban region, then presents a spectrum of risks that might be encountered. We describe novel risk mitigation criteria for small UAS that focus not on vehicle preservation but instead on minimizing risk of harm to people and property on the ground as well as to higher-value airborne assets. We conclude with a case study in which wind shear and turbulence in an urban canyon require a small UAS to execute an unplanned landing.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"10 3","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131435256","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.2010.5633382
Canchang Liu, Chuanbo Ren
Based on spring time-delay feedback controller, the excited cantilever beam modeled as an inextensible Euler-Bernoulli beam is investigated for the primary resonance. The spring controller is designed to control the dynamic behavior of the nonlinear dynamic system. The method of multiple scales is utilized directly to obtain the linear equations. The effect of the feedback gain and time-delay on the steady state response is investigated. It is found that proper selection of the feedback gain and time-delay can enhance the control performance. The bifurcation can be eliminated or the position of bifurcation point can be changed.
{"title":"Time-delay control for non-linear dynamic cantilever beam","authors":"Canchang Liu, Chuanbo Ren","doi":"10.1109/ISSCAA.2010.5633382","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633382","url":null,"abstract":"Based on spring time-delay feedback controller, the excited cantilever beam modeled as an inextensible Euler-Bernoulli beam is investigated for the primary resonance. The spring controller is designed to control the dynamic behavior of the nonlinear dynamic system. The method of multiple scales is utilized directly to obtain the linear equations. The effect of the feedback gain and time-delay on the steady state response is investigated. It is found that proper selection of the feedback gain and time-delay can enhance the control performance. The bifurcation can be eliminated or the position of bifurcation point can be changed.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"58 12","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134127352","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.2010.5633434
H. Ju, Liping Tian
Characteristic, normal and completely normal interval-valued fuzzy left h-ideals of hemirings are described. Then some basic results are given.
描述了半分的特征、正态和完全正态区间值模糊左h理想。然后给出了一些基本结果。
{"title":"Special types of interval-valued fuzzy left h-ideals of hemirings","authors":"H. Ju, Liping Tian","doi":"10.1109/ISSCAA.2010.5633434","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633434","url":null,"abstract":"Characteristic, normal and completely normal interval-valued fuzzy left h-ideals of hemirings are described. Then some basic results are given.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"26 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":"134355512","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.2010.5633299
Wanli Zhang, Changhong Wang, Baomin Feng
Using aerodynamic force to finish the orbital transfer mission can save a lot of fuels and increase the payload. In this paper, After giving the mathematical description of the Aero-assisted Orbital Transfer(AOT) problem, we discrete it through the Guess-pseudospectral method and then apply SNOPT algorithm to get the optimal state trajectory. After that we do some simplify to original dynamic equations and design a real-time closed-Loop state feedback guidance law. About the singularity issue of the control variable, we give an effective method to deal with it. Though the comparison of this closed-loop guidance law with the Matched Asymptotic Expansion(MAE) predictor-corrector method, this method can save a lot of calculation quantity and have some improvement in its guidance performance, Simulation result shows that even when the external parameter vary, guidance trajectory can still track the optimal trajectory perfectly, so it has an excellent robustness.
{"title":"Trajectory optimization and closed-Loop guidance law design of Aero-assisted Orbital Transfer problem","authors":"Wanli Zhang, Changhong Wang, Baomin Feng","doi":"10.1109/ISSCAA.2010.5633299","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633299","url":null,"abstract":"Using aerodynamic force to finish the orbital transfer mission can save a lot of fuels and increase the payload. In this paper, After giving the mathematical description of the Aero-assisted Orbital Transfer(AOT) problem, we discrete it through the Guess-pseudospectral method and then apply SNOPT algorithm to get the optimal state trajectory. After that we do some simplify to original dynamic equations and design a real-time closed-Loop state feedback guidance law. About the singularity issue of the control variable, we give an effective method to deal with it. Though the comparison of this closed-loop guidance law with the Matched Asymptotic Expansion(MAE) predictor-corrector method, this method can save a lot of calculation quantity and have some improvement in its guidance performance, Simulation result shows that even when the external parameter vary, guidance trajectory can still track the optimal trajectory perfectly, so it has an excellent robustness.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"172 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":"133013103","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.2010.5632509
C. Dong, Song-yan Wang, Ming Yang
In the entry phase, aero-environment is extremely complex for Reusable Launch Vehicles (RLVs). This brings a huge challenge to design the entry guidance law for RLVs. In this paper, an entry trajectory planning method for RLVs is researched and the algorithm is improved to ensure the continuity and smoothness of the longitudinal reference trajectory. Meanwhile, the skipping of trajectory control is decreased, and the flyability of trajectory is enhanced. Moreover, a new lateral guidance logic is proposed to reinforce the reliability of the algorithm. At the end of this paper, simulation and analysis are given to demonstrate the guidance method.
{"title":"Research on entry guidance for Reusable Launch Vehicles","authors":"C. Dong, Song-yan Wang, Ming Yang","doi":"10.1109/ISSCAA.2010.5632509","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632509","url":null,"abstract":"In the entry phase, aero-environment is extremely complex for Reusable Launch Vehicles (RLVs). This brings a huge challenge to design the entry guidance law for RLVs. In this paper, an entry trajectory planning method for RLVs is researched and the algorithm is improved to ensure the continuity and smoothness of the longitudinal reference trajectory. Meanwhile, the skipping of trajectory control is decreased, and the flyability of trajectory is enhanced. Moreover, a new lateral guidance logic is proposed to reinforce the reliability of the algorithm. At the end of this paper, simulation and analysis are given to demonstrate the guidance method.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"101 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":"133199186","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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