Pub Date : 2010-06-08DOI: 10.1109/ISSCAA.2010.5632323
Yanbin Li, Youhua Gao
The “Tabletop” and “umbrella” style platforms of 3DOF air-bearing spacecraft simulator were compared. According to the theory on kineto-elastodynamic analysis and on the spacecraft attitude kinetics, the formulary for the platform structure mass-center displacement is deduced. It is calculated that the unbalance torque resulted from deforming of the platform of air-bearing simulator acted on gravity. Both of the styles can be compared by analyzing unbalance torque influence by changing of distance between the plate and the center of rotation of the simulator.The result shows that tabletop style platform has such advantages as lower equilibrium sensitivity, higher adaptability for payload than umbrella style platform. However, because the rotation center of air bearing of tabletop style platform locates the plate of the platform, the maximal deflection angle of the simulator was restricted.
{"title":"Compare Tabletop style platform with umbrella style platform of air bearings spacecraft simulator","authors":"Yanbin Li, Youhua Gao","doi":"10.1109/ISSCAA.2010.5632323","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632323","url":null,"abstract":"The “Tabletop” and “umbrella” style platforms of 3DOF air-bearing spacecraft simulator were compared. According to the theory on kineto-elastodynamic analysis and on the spacecraft attitude kinetics, the formulary for the platform structure mass-center displacement is deduced. It is calculated that the unbalance torque resulted from deforming of the platform of air-bearing simulator acted on gravity. Both of the styles can be compared by analyzing unbalance torque influence by changing of distance between the plate and the center of rotation of the simulator.The result shows that tabletop style platform has such advantages as lower equilibrium sensitivity, higher adaptability for payload than umbrella style platform. However, because the rotation center of air bearing of tabletop style platform locates the plate of the platform, the maximal deflection angle of the simulator was restricted.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"47 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":"132110204","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.2010.5632498
C. Xiaojun, Cui Hutao, Cui Pingyuan, X. Rui
An autonomous large angular slew of deep spacecraft is studied, which is a key factor in the development of future spacecraft autonomous platform. The objective is to minimize some performance index and rotate the spacecraft to a desired attitude while subject to dynamic and geometric constraints. The investigated literature did not handle this problem very well either in performance or constraints consideration. In this paper, we propose a new approach based on pseudospectral method for autonomous attitude control, not only satisfies the nonconvex constraints but also optimizes performance. We approach this by two stages: (1) get the feasible path using RRT in Rodrigues space and (2) transform the optimal control problem to a nonlinear planning problem (NLP) utilizing Pseudospectral method. Finally, attitude path is obtained by solving the NLP with an initial value from (1). Simulation example is presented and discussed.
{"title":"Large angular autonomous attitude maneuver of deep spacecraft using pseudospectral method","authors":"C. Xiaojun, Cui Hutao, Cui Pingyuan, X. Rui","doi":"10.1109/ISSCAA.2010.5632498","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632498","url":null,"abstract":"An autonomous large angular slew of deep spacecraft is studied, which is a key factor in the development of future spacecraft autonomous platform. The objective is to minimize some performance index and rotate the spacecraft to a desired attitude while subject to dynamic and geometric constraints. The investigated literature did not handle this problem very well either in performance or constraints consideration. In this paper, we propose a new approach based on pseudospectral method for autonomous attitude control, not only satisfies the nonconvex constraints but also optimizes performance. We approach this by two stages: (1) get the feasible path using RRT in Rodrigues space and (2) transform the optimal control problem to a nonlinear planning problem (NLP) utilizing Pseudospectral method. Finally, attitude path is obtained by solving the NLP with an initial value from (1). Simulation example is presented and discussed.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"14 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":"122652826","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.2010.5632364
Wang Changhong, Liu Rui, L. Baohua, Kou Yimin
Geomagnetism Aided Navigation (GAN) is one of the most important methods to control the error in the INS. An Adaptive Genetic Algorithm applied in geomagnetic marching is proposed in this paper. By adjusting the Crossover Probability and Mutation Probability adaptively according to the value of fitness function, the AGA prevents the Genetic Algorithm from premature convergence or transforms the GA to a random search. Simulation results show that the proposed method can obtain high positioning accuracy and fast calculation. The method is robust.
{"title":"A geomagnetic positioning method with Adaptive Genetic Algorithm","authors":"Wang Changhong, Liu Rui, L. Baohua, Kou Yimin","doi":"10.1109/ISSCAA.2010.5632364","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632364","url":null,"abstract":"Geomagnetism Aided Navigation (GAN) is one of the most important methods to control the error in the INS. An Adaptive Genetic Algorithm applied in geomagnetic marching is proposed in this paper. By adjusting the Crossover Probability and Mutation Probability adaptively according to the value of fitness function, the AGA prevents the Genetic Algorithm from premature convergence or transforms the GA to a random search. Simulation results show that the proposed method can obtain high positioning accuracy and fast calculation. The method is robust.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"109 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":"122682939","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.2010.5632558
P. Cui, Xiaohua Chang, Hutao Cui
In this paper, two types of autonomous navigation method based on the Sun line-of-sight (LOS) vector are proposed for the problem of orbit determination of deep space probe. The radial velocity of the spacecraft relative to the Sun is measured by a spectrometer, and the LOS vector of the reference celestial body relative to the spacecraft is measured by the onboard camera. Then, two kinds of observation scheme, one is based on the Sun information and the other is based on the line-of-sight information, are constructed combined with the LOS vector from the spacecraft to the Sun. The fundamental of the observation schemes are analyzed and the observation equations are educed in detail. The orbit parameters of the spacecraft are estimated by utilizing extended Kalman filter. Finally, the autonomous navigation methods presented are verified by the practical data of Deep Impact mission.
{"title":"Autonomous orbit determination of deep space probe based on the Sun line-of-sight vector","authors":"P. Cui, Xiaohua Chang, Hutao Cui","doi":"10.1109/ISSCAA.2010.5632558","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632558","url":null,"abstract":"In this paper, two types of autonomous navigation method based on the Sun line-of-sight (LOS) vector are proposed for the problem of orbit determination of deep space probe. The radial velocity of the spacecraft relative to the Sun is measured by a spectrometer, and the LOS vector of the reference celestial body relative to the spacecraft is measured by the onboard camera. Then, two kinds of observation scheme, one is based on the Sun information and the other is based on the line-of-sight information, are constructed combined with the LOS vector from the spacecraft to the Sun. The fundamental of the observation schemes are analyzed and the observation equations are educed in detail. The orbit parameters of the spacecraft are estimated by utilizing extended Kalman filter. Finally, the autonomous navigation methods presented are verified by the practical data of Deep Impact mission.","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":"124035696","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.2010.5632356
Zhu Xiaolu, Zhang Fengming, Wang Yong
IMA avionics system integrates much more aviation buses as networks in avionics system. The modeling and simulation are the flexible and effective method to design and evaluate IMA avionics system which uses FC as the main network. By using simulation tool OPNET, a switch module is proposed and a FC-1553B network is simulated. We study the impact of 1553B on performance of FC network. Simulation results show that 1553B network, besides the switch nodes, reduces the performance of the FC network in avionics system. The results also show that FC-1553B network has more compatibility and less stability than FC and 1553B network.
{"title":"Study and simulation of Fibre Channel-1553B network in avionics system using OPNET","authors":"Zhu Xiaolu, Zhang Fengming, Wang Yong","doi":"10.1109/ISSCAA.2010.5632356","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632356","url":null,"abstract":"IMA avionics system integrates much more aviation buses as networks in avionics system. The modeling and simulation are the flexible and effective method to design and evaluate IMA avionics system which uses FC as the main network. By using simulation tool OPNET, a switch module is proposed and a FC-1553B network is simulated. We study the impact of 1553B on performance of FC network. Simulation results show that 1553B network, besides the switch nodes, reduces the performance of the FC network in avionics system. The results also show that FC-1553B network has more compatibility and less stability than FC and 1553B network.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"121 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":"116833258","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.2010.5632308
Yaobin Qu, Jingyu Zhang, Yiran Wu, Changhong Wang
A so called sliding-backstepping controller for attitude maneuver in some large flexible satellite is put forward. Further, combined with theory of Extended State Observer (ESO), the controller has been improved to estimate and compensate the uncertainties. After the stability analysis, simulation was carried out in particular using Single Gimbal Control Moment Gyros (SGCMGs) as the momentum actuator and considering the first ten elastic modes. The results achieve the mission requirements and conform to aforementioned theoretical analysis. Furthermore, the improved controller has significant advantages in pointing accuracy and flexible suppression.
{"title":"An improved sliding-backstepping control law for large flexible satellite attitude maneuver","authors":"Yaobin Qu, Jingyu Zhang, Yiran Wu, Changhong Wang","doi":"10.1109/ISSCAA.2010.5632308","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632308","url":null,"abstract":"A so called sliding-backstepping controller for attitude maneuver in some large flexible satellite is put forward. Further, combined with theory of Extended State Observer (ESO), the controller has been improved to estimate and compensate the uncertainties. After the stability analysis, simulation was carried out in particular using Single Gimbal Control Moment Gyros (SGCMGs) as the momentum actuator and considering the first ten elastic modes. The results achieve the mission requirements and conform to aforementioned theoretical analysis. Furthermore, the improved controller has significant advantages in pointing accuracy and flexible suppression.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"4 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":"116837811","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.2010.5633416
Hongmei Zhang, Guoshan Zhang, Z. Zuo
A sliding mode controller is designed for the longitudinal dynamics of a generic hypersonic vehicle. A generic nonlinear longitudinal dynamics model for wedge-shaped vehicle is used. Based on the dynamic inverse control, the sliding mode is adopted with the reaching law that contains a linear-quadratic controller. Optimal control techniques can be applied to search the parameters of linear-quadratic controller. Lyapunov stability analysis is included. Simulations demonstrate that the controller designed has good tracking performance and robustness in the presence of parametric uncertainty.
{"title":"A novel sliding mode control of a hypersonic aircraft","authors":"Hongmei Zhang, Guoshan Zhang, Z. Zuo","doi":"10.1109/ISSCAA.2010.5633416","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633416","url":null,"abstract":"A sliding mode controller is designed for the longitudinal dynamics of a generic hypersonic vehicle. A generic nonlinear longitudinal dynamics model for wedge-shaped vehicle is used. Based on the dynamic inverse control, the sliding mode is adopted with the reaching law that contains a linear-quadratic controller. Optimal control techniques can be applied to search the parameters of linear-quadratic controller. Lyapunov stability analysis is included. Simulations demonstrate that the controller designed has good tracking performance and robustness in the presence of parametric uncertainty.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"48 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":"116750803","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.2010.5633193
Zhang Ying-chun, Lian Jing-jing, Li Hua-yi
A method to estimate the line of sight(LOS) rate of strapdown imaging seeker based on Particle Filter(PF) is presented. PF algorithm is firstly put forward and then the model of strapdown imaging seeker is introduced. Because of the high nonlinearity in both process and measurement equations and more seriously nonGaussian noise in the measurements, the normally used Extended Kalman Filter(EKF) can not completely meet the requirements of filtering. Comparatively, PF is a congruent method for tracking in the conditions of nonlinearity and nonGaussian noise. At the last, PF and EKF are applied to estimate the LOS rate of strapdown imaging seeker respectively. Simulation results show that PF is more precise than EKF in LOS rate estimation.
{"title":"Line of sight rate estimation of strapdown imaging seeker based on Particle Filter","authors":"Zhang Ying-chun, Lian Jing-jing, Li Hua-yi","doi":"10.1109/ISSCAA.2010.5633193","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633193","url":null,"abstract":"A method to estimate the line of sight(LOS) rate of strapdown imaging seeker based on Particle Filter(PF) is presented. PF algorithm is firstly put forward and then the model of strapdown imaging seeker is introduced. Because of the high nonlinearity in both process and measurement equations and more seriously nonGaussian noise in the measurements, the normally used Extended Kalman Filter(EKF) can not completely meet the requirements of filtering. Comparatively, PF is a congruent method for tracking in the conditions of nonlinearity and nonGaussian noise. At the last, PF and EKF are applied to estimate the LOS rate of strapdown imaging seeker respectively. Simulation results show that PF is more precise than EKF in LOS rate estimation.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"108 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":"116787811","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.2010.5632495
Kong Xianren, Liao Jun, Xu Dafu
Random loading identification has long been a difficult problem for multi-input-multi-output stationary random vibration problems. In this paper, the inverse pseudo-excitation method is used for dealing with such identification problems, and condition number weighted average method is developed to improve the rank defect of the frequency response function matrix during the process of random loading identification; simulation process is given to compare the result between the presented method and routine method. It proves the optimizing result by use of the method; experiments are designed to certify the feasibility of the algorithm, and achieve good results, and the ill-conditioning problem can be conquered to some extent. The condition number of FRF is used to choose the response measuring point, it reduces the workload, and get a accurate result.
{"title":"An improved method of structural random loading identification","authors":"Kong Xianren, Liao Jun, Xu Dafu","doi":"10.1109/ISSCAA.2010.5632495","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632495","url":null,"abstract":"Random loading identification has long been a difficult problem for multi-input-multi-output stationary random vibration problems. In this paper, the inverse pseudo-excitation method is used for dealing with such identification problems, and condition number weighted average method is developed to improve the rank defect of the frequency response function matrix during the process of random loading identification; simulation process is given to compare the result between the presented method and routine method. It proves the optimizing result by use of the method; experiments are designed to certify the feasibility of the algorithm, and achieve good results, and the ill-conditioning problem can be conquered to some extent. The condition number of FRF is used to choose the response measuring point, it reduces the workload, and get a accurate result.","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":"114383148","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.2010.5632359
Yewei Zhang, B. Fang, Yang Chen
The viscoelastic material in vibration control is widely studied. The dynamic environment of spacecraft can be improved by whole-spacecraft vibration isolation during launch. The traditional solution of improving the dynamic environment of structure is to increase the area of viscoelastic material. In the paper, the problems of reliability and vibration isolation effect, which are focused by the designers, are dissused. By the reliability method, the dynamic model of coupled system is also studied. The natural frequencies and damping feature problems which are affected by the stiffness of viscoelastic material are dissussed by the dynamic model of coupled system. Furthermore, the stiffness of viscoelastic material is simplified to the structural damping. By both the computation result and the experiment data, it is demonstrated that raising the stiffness of viscoelastic material cannot raise the modal loss factor of system accordingly.
{"title":"Dynamic features analysis and reliability study of whole-spacecraft vibration isolation","authors":"Yewei Zhang, B. Fang, Yang Chen","doi":"10.1109/ISSCAA.2010.5632359","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632359","url":null,"abstract":"The viscoelastic material in vibration control is widely studied. The dynamic environment of spacecraft can be improved by whole-spacecraft vibration isolation during launch. The traditional solution of improving the dynamic environment of structure is to increase the area of viscoelastic material. In the paper, the problems of reliability and vibration isolation effect, which are focused by the designers, are dissused. By the reliability method, the dynamic model of coupled system is also studied. The natural frequencies and damping feature problems which are affected by the stiffness of viscoelastic material are dissussed by the dynamic model of coupled system. Furthermore, the stiffness of viscoelastic material is simplified to the structural damping. By both the computation result and the experiment data, it is demonstrated that raising the stiffness of viscoelastic material cannot raise the modal loss factor of system accordingly.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"32 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114911477","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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