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}
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}
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.2010.5634042
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.2010.5632539
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}
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}
Gaussian Mixture probability hypothesis density (GM-PHD) filter is a closed-form solution to the probability hypothesis density filter, which could estimate states and time-varying number of targets based on theory of random finite set. Probability multiple hypotheses tracking (PMHT) is a multi-target tracking algorithm combining data association and expectation-maximization. However, GM-PHD can not give trajectories of target because of its disability of providing identity of target. Furthermore, PMHT need known number of targets and several frames trajectories of targets at first which are difficult in practical application. Firstly, we propose track oriented PMHT tracker (TO-PMHTT), then an approach of data association combining the advantage of GM-PHD with TO-PMHTT is designed in this paper. GM-PHD acts as the pre-filter of TO-PMHTT when there are no crossing targets in the scenario, while interaction between GM-PHD and TO-PMHTT is performed when targets enter crossing zone. Computer simulation results show that the method can provide association for both separated and crossing targets tracking.
{"title":"Data association for GM-PHD with track oriented PMHT","authors":"Shicang Zhang, Jian-xun Li, Binyi Fan, Liangbin Wu","doi":"10.1109/ISSCAA.2010.5633037","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633037","url":null,"abstract":"Gaussian Mixture probability hypothesis density (GM-PHD) filter is a closed-form solution to the probability hypothesis density filter, which could estimate states and time-varying number of targets based on theory of random finite set. Probability multiple hypotheses tracking (PMHT) is a multi-target tracking algorithm combining data association and expectation-maximization. However, GM-PHD can not give trajectories of target because of its disability of providing identity of target. Furthermore, PMHT need known number of targets and several frames trajectories of targets at first which are difficult in practical application. Firstly, we propose track oriented PMHT tracker (TO-PMHTT), then an approach of data association combining the advantage of GM-PHD with TO-PMHTT is designed in this paper. GM-PHD acts as the pre-filter of TO-PMHTT when there are no crossing targets in the scenario, while interaction between GM-PHD and TO-PMHTT is performed when targets enter crossing zone. Computer simulation results show that the method can provide association for both separated and crossing targets tracking.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"24 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121817069","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-06-08DOI: 10.1109/ISSCAA.2010.5633274
Zhaohui Yao, W. Bao
This paper has discussed a class of practical switched systems with multi proportional-integral controllers. And the switching control principles based on the Min(Max) switching law is described and the integral saturation limiting in proportional-integral controller to guarantee a rapid switching is discussed. A conservative dynamic performance of this class of switched systems under switching is presented, which is the possible maximum value of the system dynamic output maximum percent overshoot at any different switching points. The conservative dynamic performance is dependent just on the system parameters but not on the initial states caused by different switching points, which makes it easy to present an exact performance objective in switching control design. And finally, a general switching proportional-integral control design approach for this class of switched systems is generalized and is testified to be reasonable and reliable by simulations.
{"title":"A multiloop switching proportional-integral control design based on Min/Max law","authors":"Zhaohui Yao, W. Bao","doi":"10.1109/ISSCAA.2010.5633274","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633274","url":null,"abstract":"This paper has discussed a class of practical switched systems with multi proportional-integral controllers. And the switching control principles based on the Min(Max) switching law is described and the integral saturation limiting in proportional-integral controller to guarantee a rapid switching is discussed. A conservative dynamic performance of this class of switched systems under switching is presented, which is the possible maximum value of the system dynamic output maximum percent overshoot at any different switching points. The conservative dynamic performance is dependent just on the system parameters but not on the initial states caused by different switching points, which makes it easy to present an exact performance objective in switching control design. And finally, a general switching proportional-integral control design approach for this class of switched systems is generalized and is testified to be reasonable and reliable by simulations.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"30 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125158120","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-06-08DOI: 10.1109/ISSCAA.2010.5632540
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}
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