Pub Date : 2010-06-08DOI: 10.1109/ISSCAA.2010.5633237
Wei Jing, Ya-qiu Liu, Wu Qu
With multiprocessor systems, redundant scheduling is a technique that trades processing power for increased reliability through redundancy. One novel approach, called primary-backup task scheduling, is a large number of used in hard real-time multiprocessor systems to guarantee the deadlines of tasks faults. In this paper, we analysis and compare the scheduling algorithm based on primary-backup replication in current distributed system. Finally, the important features that fault-tolerant Task Scheduling in Multiprocessor Systems based on primary-backup are summarized, and the future research strategies and tends are given.
{"title":"Fault-tolerant task scheduling in multiprocessor systems based on primary-backup scheme","authors":"Wei Jing, Ya-qiu Liu, Wu Qu","doi":"10.1109/ISSCAA.2010.5633237","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633237","url":null,"abstract":"With multiprocessor systems, redundant scheduling is a technique that trades processing power for increased reliability through redundancy. One novel approach, called primary-backup task scheduling, is a large number of used in hard real-time multiprocessor systems to guarantee the deadlines of tasks faults. In this paper, we analysis and compare the scheduling algorithm based on primary-backup replication in current distributed system. Finally, the important features that fault-tolerant Task Scheduling in Multiprocessor Systems based on primary-backup are summarized, and the future research strategies and tends are given.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"24 7 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":"125673960","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.2010.5633241
Yansong Jiang, Bao-ku Su, Yu Liu
The high accuracy accelerometer can be demarcated in multiposition tumbling experiment under 1g gravitational field. The g2 observation model of Two Orthometric Accelerometers can eliminate the corner error. there is a serious multicollinearity exit in this system because some model coefficient mix together. In view of above question, this article has given the arithmetic of Empirical Bayes Estimation(EB), and applied this method in model which is mentioned above. The result of the simulation and the experiment shows that compared with the conventional least squares method and the generalized diagonal ridge estimation, the Empirical Bayes Estimation can overcome the influence of the multicollinearity and can separate two coefficients which are The Second-Order Terms and the cross-coupling terms.
{"title":"Application of Empirical Bayes Estimation in Error Model Identification of Two Orthometric Accelerometers","authors":"Yansong Jiang, Bao-ku Su, Yu Liu","doi":"10.1109/ISSCAA.2010.5633241","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633241","url":null,"abstract":"The high accuracy accelerometer can be demarcated in multiposition tumbling experiment under 1g gravitational field. The g2 observation model of Two Orthometric Accelerometers can eliminate the corner error. there is a serious multicollinearity exit in this system because some model coefficient mix together. In view of above question, this article has given the arithmetic of Empirical Bayes Estimation(EB), and applied this method in model which is mentioned above. The result of the simulation and the experiment shows that compared with the conventional least squares method and the generalized diagonal ridge estimation, the Empirical Bayes Estimation can overcome the influence of the multicollinearity and can separate two coefficients which are The Second-Order Terms and the cross-coupling terms.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"1 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":"128887984","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.2010.5633383
G. Duan, M. Hou, Feng Tan
The problem of integrated guidance and control for homing missiles is considered. A time-varying integrated guidance and control model of the pitch plane is formulated, and further changed into the normal form by nonlinear coordinate transformation. In order to deal with the unmatched and unknown bounded uncertainties, an adaptive auxiliary system is first constructed to approximate the normal plant, and then a sliding mode based controller is designed with the help of the auxiliary system. It is proved that the proposed feedback controller can ensure not only the accuracy of target interception, but also the stability of the missile dynamics. The 6DOF nonlinear missile simulation results indicate the effect and feasibility of the proposed integrated guidance and control design scheme.
{"title":"Auxiliary system based integrated missile guidance and control","authors":"G. Duan, M. Hou, Feng Tan","doi":"10.1109/ISSCAA.2010.5633383","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633383","url":null,"abstract":"The problem of integrated guidance and control for homing missiles is considered. A time-varying integrated guidance and control model of the pitch plane is formulated, and further changed into the normal form by nonlinear coordinate transformation. In order to deal with the unmatched and unknown bounded uncertainties, an adaptive auxiliary system is first constructed to approximate the normal plant, and then a sliding mode based controller is designed with the help of the auxiliary system. It is proved that the proposed feedback controller can ensure not only the accuracy of target interception, but also the stability of the missile dynamics. The 6DOF nonlinear missile simulation results indicate the effect and feasibility of the proposed integrated guidance and control design scheme.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"5 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":"130529437","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.2010.5632397
Xiaoxiang Hu, Changxing Ding, Ligang Wu, Changhua Hu, Hongyi Li, Y. Si, Zeguo Wang
A terminal sliding mode controller is designed for a generic air-breathing hypersonic vehicles (AHVs). The model of AHVs is nonlinear, and includes uncertain parameters and intricate coupling between the engine and flight dynamics. An affine form of the longitudinal model is obtained by input/output linearization, and then a controller is designed by using terminal sliding mode method. The terminal sliding mode can make the system stabilize in finite time. Simulation results are provided to show the availability of the designed controller by excellent altitude and velocity tracking performance.
{"title":"Terminal sliding mode control design for air-breathing hypersonic vehicles","authors":"Xiaoxiang Hu, Changxing Ding, Ligang Wu, Changhua Hu, Hongyi Li, Y. Si, Zeguo Wang","doi":"10.1109/ISSCAA.2010.5632397","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632397","url":null,"abstract":"A terminal sliding mode controller is designed for a generic air-breathing hypersonic vehicles (AHVs). The model of AHVs is nonlinear, and includes uncertain parameters and intricate coupling between the engine and flight dynamics. An affine form of the longitudinal model is obtained by input/output linearization, and then a controller is designed by using terminal sliding mode method. The terminal sliding mode can make the system stabilize in finite time. Simulation results are provided to show the availability of the designed controller by excellent altitude and velocity tracking performance.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"2 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":"130658216","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}
Propellant transfer control in microgravity is the key problems of on-orbit refueling. The paper proposes a simultaneously vented refueling technique to control the propellant transfer. Establishes numeric model to calculate the process of propellant filling, and that the results can satisfy the requirement of on-orbit refueling. When the propellant transfers into the tank, it is needs to control the fluid-flow with propellant management device. The paper uses VOF model to simulate the propellant filling process in the vane-type surface tension tank. The stability of propellant fluid correlates with Weber number. As the results of simulation, the propellant management device in the tank can increase the Weber number then make the fluid-flow stable. Compares to the VTRE test results, the simulation results makes good agreement.
{"title":"Simulation and analysis of propellant transfer control in on-orbit refueling","authors":"Jinghao Li, Jianguo Tan, Xiaoqian Chen, Yiyong Huang","doi":"10.1109/ISSCAA.2010.5633235","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633235","url":null,"abstract":"Propellant transfer control in microgravity is the key problems of on-orbit refueling. The paper proposes a simultaneously vented refueling technique to control the propellant transfer. Establishes numeric model to calculate the process of propellant filling, and that the results can satisfy the requirement of on-orbit refueling. When the propellant transfers into the tank, it is needs to control the fluid-flow with propellant management device. The paper uses VOF model to simulate the propellant filling process in the vane-type surface tension tank. The stability of propellant fluid correlates with Weber number. As the results of simulation, the propellant management device in the tank can increase the Weber number then make the fluid-flow stable. Compares to the VTRE test results, the simulation results makes good agreement.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"115 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":"132886025","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.2010.5633609
Lilian Huang, Xiaoyang Wang, Guanghui Sun
In this paper, a new chaotic system is proposed. It also belongs to Lorenz system, which has three parameters and two nonlinear terms, and one of the parameters is the bifurcation parameter. The nonlinear dynamic properties of the system such as strange attractor, the largest Lyapunov index, fractal dimension, spectrum, power spectrum and bifurcation are researched via theoretical analysis and digital simulation. EWB software is used to design and simulate the circuit. The numerical and circuit simulation indicates the new nonlinear system proposed can show chaotic characteristics.
{"title":"Design and circuit simulation of the new Lorenz chaotic system","authors":"Lilian Huang, Xiaoyang Wang, Guanghui Sun","doi":"10.1109/ISSCAA.2010.5633609","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633609","url":null,"abstract":"In this paper, a new chaotic system is proposed. It also belongs to Lorenz system, which has three parameters and two nonlinear terms, and one of the parameters is the bifurcation parameter. The nonlinear dynamic properties of the system such as strange attractor, the largest Lyapunov index, fractal dimension, spectrum, power spectrum and bifurcation are researched via theoretical analysis and digital simulation. EWB software is used to design and simulate the circuit. The numerical and circuit simulation indicates the new nonlinear system proposed can show chaotic characteristics.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"1 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":"130423928","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.2010.5633470
Xia Zhang, Xu-dong Zheng, Shi-chang Hu, Hao Wang, Zhongkun Jin
A bulk micromachined gyroscope fabricated with an improved process flow is measured systematically. It achieves good performance at atmosphere. The driving resonant frequency is 1663.5Hz with a quality factor 195, and the sensing resonant frequency is 1677Hz with a quality factor 200. The R2-nonlinearity is 0.008% within the range of ±43°/s, which is limited by the digital to analogue converter, with a scale factor of 42.17mV/°/s. The scale factor is reduced to 7.4mV/°/s to perform linear test within a larger range, and the R2-nonlinearity is 0.032% within ±200°/s. The bias stability is 19.55°/h and the measured noise floor is 0.0125°/s/√Hz at 1Hz.
{"title":"Performance characterization of a bulk micromachined gyroscope working at atmosphere","authors":"Xia Zhang, Xu-dong Zheng, Shi-chang Hu, Hao Wang, Zhongkun Jin","doi":"10.1109/ISSCAA.2010.5633470","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633470","url":null,"abstract":"A bulk micromachined gyroscope fabricated with an improved process flow is measured systematically. It achieves good performance at atmosphere. The driving resonant frequency is 1663.5Hz with a quality factor 195, and the sensing resonant frequency is 1677Hz with a quality factor 200. The R<sup>2</sup>-nonlinearity is 0.008% within the range of ±43°/s, which is limited by the digital to analogue converter, with a scale factor of 42.17mV/°/s. The scale factor is reduced to 7.4mV/°/s to perform linear test within a larger range, and the R<sup>2</sup>-nonlinearity is 0.032% within ±200°/s. The bias stability is 19.55°/h and the measured noise floor is 0.0125°/s/√Hz at 1Hz.","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":"123110771","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.2010.5633582
Kong Xianren, Xu Dafu, Liao Jun
This paper presents a flexible cable model considering that tether is easy to inflect can be used for analyzing the dynamic behavior of the electro-dynamic tether (EDT) de-orbiting system. The model can describe tether inflecting and bowing under action of electro-dynamic drag and gravity gradient induced force, and the influences on electro motive force and electro-dynamic drag. Two mathematical simulations are employed to show the differences between the flexible cable model and the rigid bar model. Vibration of the EDT system during de-orbiting course is discussed, at which the simulation result shows vertical response is the main vibration way of EDT.
{"title":"Dynamics of electro-dynamic tether de-orbiting system for LEO satellites","authors":"Kong Xianren, Xu Dafu, Liao Jun","doi":"10.1109/ISSCAA.2010.5633582","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633582","url":null,"abstract":"This paper presents a flexible cable model considering that tether is easy to inflect can be used for analyzing the dynamic behavior of the electro-dynamic tether (EDT) de-orbiting system. The model can describe tether inflecting and bowing under action of electro-dynamic drag and gravity gradient induced force, and the influences on electro motive force and electro-dynamic drag. Two mathematical simulations are employed to show the differences between the flexible cable model and the rigid bar model. Vibration of the EDT system during de-orbiting course is discussed, at which the simulation result shows vertical response is the main vibration way of EDT.","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":"125736765","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.2010.5633603
G. Yuan, Haibo Liang, K. He, Yanjun Xie
To effectively wipe out random drift and extract valid signal of MEMS gyro, the methods of adaptive Kalman filtering and wavelet analysis are investigated. For the first method, the autoregressive moving average (ARMA) model of random drift is established, which is essential to the adaptive Kalman filter. For the second one, the wavelet basis, decomposition level, and threshold-choosing principle are determined. Then the de-noising test is implemented by using real signal of MEMS gyro, and both methods are of good effectiveness. The contrast analysis between both methods indicates that the adaptive Kalman filtering approach is more suitable for the real-time de-noising of MEMS gyro signal.
{"title":"Research on signal de-noising technique for MEMS gyro","authors":"G. Yuan, Haibo Liang, K. He, Yanjun Xie","doi":"10.1109/ISSCAA.2010.5633603","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633603","url":null,"abstract":"To effectively wipe out random drift and extract valid signal of MEMS gyro, the methods of adaptive Kalman filtering and wavelet analysis are investigated. For the first method, the autoregressive moving average (ARMA) model of random drift is established, which is essential to the adaptive Kalman filter. For the second one, the wavelet basis, decomposition level, and threshold-choosing principle are determined. Then the de-noising test is implemented by using real signal of MEMS gyro, and both methods are of good effectiveness. The contrast analysis between both methods indicates that the adaptive Kalman filtering approach is more suitable for the real-time de-noising of MEMS gyro signal.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"23 2","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114036532","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.2010.5633103
Xiao-Liang Wang, Wenbin Song
Interpolation methods are very important in computational aeroelasticity in both the closely and loosely coupled analysis method. In this paper, the characteristics of thin plate splines (TPS), multiquadrics surface spline methods(MQ) and kriging method were first analyzed for interface data interpolation in computational aeroelasticity. Through the analysis of different methods, a hybrid interpolation method is proposed which combines the thin palte spline and kriging method. The AGRAD 445.6 wing is used to demonstrate the efficiency and accuracy of this method .The method can be used to exchange interface data of computational aeroelasticity.
{"title":"A new hybrid interpolation method for information exchange in computational aeroelasticity","authors":"Xiao-Liang Wang, Wenbin Song","doi":"10.1109/ISSCAA.2010.5633103","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633103","url":null,"abstract":"Interpolation methods are very important in computational aeroelasticity in both the closely and loosely coupled analysis method. In this paper, the characteristics of thin plate splines (TPS), multiquadrics surface spline methods(MQ) and kriging method were first analyzed for interface data interpolation in computational aeroelasticity. Through the analysis of different methods, a hybrid interpolation method is proposed which combines the thin palte spline and kriging method. The AGRAD 445.6 wing is used to demonstrate the efficiency and accuracy of this method .The method can be used to exchange interface data of computational aeroelasticity.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"40 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":"122502418","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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