Pub Date : 2010-06-08DOI: 10.1109/ISSCAA.2010.5633144
Wei Zhao, Ye San
Aiming at the drawback of being easily trapped into the local optima and premature convergence in quantum-behaved particle swarm optimization algorithm, clustering coefficient and characteristic distance is proposed to measure diversity of the population by which quantum-behaved particle swarm optimization algorithm is guided. The population is divergent to increase population diversity and enhance exploration if clustering coefficient is large and characteristic distance is small; the population is convergent to reduce population diversity and enhance exploitation if clustering coefficient is small and characteristic distance is large. The simulation results of testing four benchmark functions show that diversity-guided quantum-behaved particle swarm optimization algorithm based on clustering coefficient and characteristic distance has better optimization performance than other algorithms, the validity and feasibility of the method is verified.
{"title":"Diversity-guided quantum-behaved particle swarm optimization algorithm based on clustering coefficient and characteristic distance","authors":"Wei Zhao, Ye San","doi":"10.1109/ISSCAA.2010.5633144","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633144","url":null,"abstract":"Aiming at the drawback of being easily trapped into the local optima and premature convergence in quantum-behaved particle swarm optimization algorithm, clustering coefficient and characteristic distance is proposed to measure diversity of the population by which quantum-behaved particle swarm optimization algorithm is guided. The population is divergent to increase population diversity and enhance exploration if clustering coefficient is large and characteristic distance is small; the population is convergent to reduce population diversity and enhance exploitation if clustering coefficient is small and characteristic distance is large. The simulation results of testing four benchmark functions show that diversity-guided quantum-behaved particle swarm optimization algorithm based on clustering coefficient and characteristic distance has better optimization performance than other algorithms, the validity and feasibility of the method is verified.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"102 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":"122505416","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.2010.5632499
Wei Hongtao, Kong Xianren
Using FE method, the typical honeycomb core modulus is studied, the nonlinear stress-strain relationship with a property of “harden spring” under tensile load and “soften spring” under compress load is obtained. The effect of the height of the core on the analysis of the modulus is discussed, the results are compared with these acquired from Gibson formula. The polynomial fitting method is adopted to get the nonlinear modulus. The Kirchhoff assumption and Galerkin approximation are used to get the equation of motion of the typical honeycomb core sandwich beam. The numerical results are obtained. The nonlinear amplitude-frequency response of forced vibration is discussed.
{"title":"Effect of non-linear in-plane honeycomb core modulus on forced vibration of sandwich beam","authors":"Wei Hongtao, Kong Xianren","doi":"10.1109/ISSCAA.2010.5632499","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632499","url":null,"abstract":"Using FE method, the typical honeycomb core modulus is studied, the nonlinear stress-strain relationship with a property of “harden spring” under tensile load and “soften spring” under compress load is obtained. The effect of the height of the core on the analysis of the modulus is discussed, the results are compared with these acquired from Gibson formula. The polynomial fitting method is adopted to get the nonlinear modulus. The Kirchhoff assumption and Galerkin approximation are used to get the equation of motion of the typical honeycomb core sandwich beam. The numerical results are obtained. The nonlinear amplitude-frequency response of forced vibration is discussed.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"185 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":"131622431","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.2010.5632330
Yao Yu, Jia Jie, M. Kemao
Space missions to libration points are an interesting opportunity to perform deep space explorations reducing costs and risks and to obtain better results by taking advantages of invariant manifolds of periodic orbits. This paper studies the chaining of periodic orbits via their invariant manifolds to provide various types of low energy orbits for space exploration, particularly in the Sun-Earth-Moon system. Recent work shows that this approach may be used to design planetary flyby and planetary capture orbits. This shows that the technique for chaining periodic orbits is much more general and widely applicable, and is not restricted to libration missions only. The use of invariant manifolds provides a unified theoretical approach for studying different mission applications. It also provides robust numerical algorithms for the computation and optimization of such trajectories.
{"title":"Chaining simple periodic orbits design based on invariant manifolds in the Circular Restricted Three-Body Problem","authors":"Yao Yu, Jia Jie, M. Kemao","doi":"10.1109/ISSCAA.2010.5632330","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632330","url":null,"abstract":"Space missions to libration points are an interesting opportunity to perform deep space explorations reducing costs and risks and to obtain better results by taking advantages of invariant manifolds of periodic orbits. This paper studies the chaining of periodic orbits via their invariant manifolds to provide various types of low energy orbits for space exploration, particularly in the Sun-Earth-Moon system. Recent work shows that this approach may be used to design planetary flyby and planetary capture orbits. This shows that the technique for chaining periodic orbits is much more general and widely applicable, and is not restricted to libration missions only. The use of invariant manifolds provides a unified theoretical approach for studying different mission applications. It also provides robust numerical algorithms for the computation and optimization of such trajectories.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"81 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":"132709383","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.2010.5632539
Fanming Liu, Dong Qian, Yingfa Zhang, Yan Li
In order to investigate the influence of gravity gradiometer instrument (GGI), gyroscope, and accelerator on navigation precision, simulation program of gravity gradient aided inertial navigation system is established in this paper. The detailed mathematical model of gravity gradient aided navigation system is given. Simulation results under Matlab environment prove that remarkably promotion of navigation precision can be obtained by using five independent gravity gradient tensors into the integrated system. Meanwhile, it also shows that both the gradiometer accuracy and the matching map resolution has large influence on navigation precision, while the gyroscope and accelerator accuracy make a minor one by comparison. These conclusions indicate that gravity gradient aided inertial navigation has a lower demand on inertial sensors, which is helpful to reduce the design cost of inertial navigation system.
{"title":"A computer simulation of the influence of GGI and inertial sensors on gravity gradient aided navigation","authors":"Fanming Liu, Dong Qian, Yingfa Zhang, Yan Li","doi":"10.1109/ISSCAA.2010.5632539","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632539","url":null,"abstract":"In order to investigate the influence of gravity gradiometer instrument (GGI), gyroscope, and accelerator on navigation precision, simulation program of gravity gradient aided inertial navigation system is established in this paper. The detailed mathematical model of gravity gradient aided navigation system is given. Simulation results under Matlab environment prove that remarkably promotion of navigation precision can be obtained by using five independent gravity gradient tensors into the integrated system. Meanwhile, it also shows that both the gradiometer accuracy and the matching map resolution has large influence on navigation precision, while the gyroscope and accelerator accuracy make a minor one by comparison. These conclusions indicate that gravity gradient aided inertial navigation has a lower demand on inertial sensors, which is helpful to reduce the design cost of inertial navigation system.","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":"114728889","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}
As the health status of aeroplane structural components has direct influence on the flight safety, it is important to monitor the health status of structural components timely. In this paper, acoustic emission technology is used to monitor the health status of the aeroplane structural component. The acoustic emission health information from the aeroplane structural component is analyzed and disposed. The fault inference engine that bases on rules and the forward chaining control strategies is designed. The K-means clustering analysis algorithm is used to monitor the health status of aeroplane structural component. Experiments show that the method has good performance on monitoring the status of aeroplane structural components. It presents an effective health monitoring method of aeroplane structural components, which can also be directly applied to other structural systems in machine equipments.
{"title":"Health monitoring of aeroplane structural component based on K-means clustering","authors":"Jianguo Cui, Yingyu Wang, Zhonghai Li, Li Liqiu, Zhao Yun, Guangyan Xu","doi":"10.1109/ISSCAA.2010.5633092","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633092","url":null,"abstract":"As the health status of aeroplane structural components has direct influence on the flight safety, it is important to monitor the health status of structural components timely. In this paper, acoustic emission technology is used to monitor the health status of the aeroplane structural component. The acoustic emission health information from the aeroplane structural component is analyzed and disposed. The fault inference engine that bases on rules and the forward chaining control strategies is designed. The K-means clustering analysis algorithm is used to monitor the health status of aeroplane structural component. Experiments show that the method has good performance on monitoring the status of aeroplane structural components. It presents an effective health monitoring method of aeroplane structural components, which can also be directly applied to other structural systems in machine equipments.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"117 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":"117249428","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.2010.5632745
Yongxin Yin, Zhongming Ou, Wen Shi
The flight control system design method of wing-in-ground effect aircraft is presented based on robust control theory. With a view to uncertainty of lengthways channels, the simplified mathematical model is constituted for wing-in-ground effect aircraft. According to this simplified model, the lengthways control system is designed. In order to overcome defect of uncertain system, the flight controller of wing-in-ground effect aircraft is designed using robust control theory. Simulation results show that this control method can implement efficiently precision control mission for wing-in-ground effect aircraft as well as preferable robustness.
{"title":"Robust design method for flight control system of cruise missile","authors":"Yongxin Yin, Zhongming Ou, Wen Shi","doi":"10.1109/ISSCAA.2010.5632745","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632745","url":null,"abstract":"The flight control system design method of wing-in-ground effect aircraft is presented based on robust control theory. With a view to uncertainty of lengthways channels, the simplified mathematical model is constituted for wing-in-ground effect aircraft. According to this simplified model, the lengthways control system is designed. In order to overcome defect of uncertain system, the flight controller of wing-in-ground effect aircraft is designed using robust control theory. Simulation results show that this control method can implement efficiently precision control mission for wing-in-ground effect aircraft as well as preferable robustness.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"31 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":"115266411","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.2010.5633074
Changhong Wang, Taoyi Chen, Zhenshen Qu
This paper proposes a novel improved median filter algorithm for the images highly corrupted with salt-and-pepper noise. Firstly all the pixels are classified into signal pixels and noisy pixels by using the Max-Min noise detector. The noisy pixels are then separated into three classes, which are low-density, moderate-density, and high-density noises, based on the local statistic information. Finally the weighted 8-neighborhood similarity function filter, the 5×5 median filter and the 4-neighborhood mean filter are adopted to remove the noises for the low, moderate and high level cases, respectively. In experiment, the proposed algorithm is compared with three typical methods, named Standard Median filter, Extremum Median filter and Adaptive Median filter, respectively. The validation results show that the proposed algorithm has better performance for capabilities of noise removal, adaptivity, and detail preservation, especially effective for the cases when the images are extremely highly corrupted.
{"title":"A novel improved median filter for salt-and-pepper noise from highly corrupted images","authors":"Changhong Wang, Taoyi Chen, Zhenshen Qu","doi":"10.1109/ISSCAA.2010.5633074","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633074","url":null,"abstract":"This paper proposes a novel improved median filter algorithm for the images highly corrupted with salt-and-pepper noise. Firstly all the pixels are classified into signal pixels and noisy pixels by using the Max-Min noise detector. The noisy pixels are then separated into three classes, which are low-density, moderate-density, and high-density noises, based on the local statistic information. Finally the weighted 8-neighborhood similarity function filter, the 5×5 median filter and the 4-neighborhood mean filter are adopted to remove the noises for the low, moderate and high level cases, respectively. In experiment, the proposed algorithm is compared with three typical methods, named Standard Median filter, Extremum Median filter and Adaptive Median filter, respectively. The validation results show that the proposed algorithm has better performance for capabilities of noise removal, adaptivity, and detail preservation, especially effective for the cases when the images are extremely highly corrupted.","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":"115519161","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.2010.5632540
Liqiang. Xu, Junli Chen, Guozhong Chen, Xiaowei Shao, D. Duan
The spotlight mode of spaceborne SAR platforms often have to point its payload to immobile target on the ground which means the satellite attitude have to follow a specific trajectory in a fixed time span. In this paper, the attitude angle, angular velocities and angular accelerate are derived. A PD control law with feedforward is developed to achieve the purpose. The approach is verified using numerical simulation with external disturbance and uncertain model.
{"title":"The attitude tracking maneuvers of spaceborne spotlight SAR","authors":"Liqiang. Xu, Junli Chen, Guozhong Chen, Xiaowei Shao, D. Duan","doi":"10.1109/ISSCAA.2010.5632540","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632540","url":null,"abstract":"The spotlight mode of spaceborne SAR platforms often have to point its payload to immobile target on the ground which means the satellite attitude have to follow a specific trajectory in a fixed time span. In this paper, the attitude angle, angular velocities and angular accelerate are derived. A PD control law with feedforward is developed to achieve the purpose. The approach is verified using numerical simulation with external disturbance and uncertain model.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"84 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":"123339628","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.2010.5634042
Du Yunli, Xia Qunli, Wang Zhuomin
Due to the imperfect disturbance rejection performance, missile motion may severely degrade the seeker tracking accuracy. In this paper, the process of the missile body angular motion acting on seeker servo platform is analyzed, the model of parasitical loop of seeker disturbance rejection is constructed, and the conception of seeker disturbance rejection with phase lag is present. Through simulation, the stability zone of system with respect to disturbance rejection rate is plotted, and the effect of disturbance rejection rate phase lag on system stability is analyzed. The study results give a constructive advice about how to choose the key parameters of the missile guidance and control system. The conclusion of this paper is helpful for the engineers of missile during the preliminary design period.
{"title":"Effect of seeker disturbance rejection performance on the control system stability","authors":"Du Yunli, Xia Qunli, Wang Zhuomin","doi":"10.1109/ISSCAA.2010.5634042","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5634042","url":null,"abstract":"Due to the imperfect disturbance rejection performance, missile motion may severely degrade the seeker tracking accuracy. In this paper, the process of the missile body angular motion acting on seeker servo platform is analyzed, the model of parasitical loop of seeker disturbance rejection is constructed, and the conception of seeker disturbance rejection with phase lag is present. Through simulation, the stability zone of system with respect to disturbance rejection rate is plotted, and the effect of disturbance rejection rate phase lag on system stability is analyzed. The study results give a constructive advice about how to choose the key parameters of the missile guidance and control system. The conclusion of this paper is helpful for the engineers of missile during the preliminary design period.","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":"114965575","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.2010.5632900
Dan Wang, Zhi Xiong, Fang Chen, Jian-ye Liu
The error of the inertia navigation system can be modulated critically by using the real-time SAR image through image matching and positioning. The mismatching points are inevitable in the SAR aided navigation. In the integrated navigation, the measurement outliers will affect the filter seriously. In order to eliminate the effect of the mismatching points, combining the discontinuous working characteristics of the SAR image matching navigation, the paper proposes the image mismatching points eliminating arithmetic and the integrated navigation arithmetic. We found the mathematical models of the INS/SAR integrated navigation system which has the discontinuous working characteristics. And basing on the Kalman filtering information we design the arithmetic to eliminate and displace the image mismatching points. The simulation indicates the arithmetic proposed in this paper can eliminate and displace the image mismatching points availably and consequently improves the accuracy of the integrated navigation greatly.
{"title":"Research on the image mismatching points eliminating and the integrated arithmetic in the INS/SAR integrated navigation","authors":"Dan Wang, Zhi Xiong, Fang Chen, Jian-ye Liu","doi":"10.1109/ISSCAA.2010.5632900","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632900","url":null,"abstract":"The error of the inertia navigation system can be modulated critically by using the real-time SAR image through image matching and positioning. The mismatching points are inevitable in the SAR aided navigation. In the integrated navigation, the measurement outliers will affect the filter seriously. In order to eliminate the effect of the mismatching points, combining the discontinuous working characteristics of the SAR image matching navigation, the paper proposes the image mismatching points eliminating arithmetic and the integrated navigation arithmetic. We found the mathematical models of the INS/SAR integrated navigation system which has the discontinuous working characteristics. And basing on the Kalman filtering information we design the arithmetic to eliminate and displace the image mismatching points. The simulation indicates the arithmetic proposed in this paper can eliminate and displace the image mismatching points availably and consequently improves the accuracy of the integrated navigation greatly.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"15 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":"124007609","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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