Pub Date : 2009-06-11DOI: 10.1109/RAST.2009.5158296
E. Oland, R. Schlanbusch
This paper presents a reaction wheel design for CubeSats where it takes the limitation of size and mass into consideration. It presents an overview of which altitudes it is feasible to use magnetic torquers for momentum dumping as well as presenting equations for customizing reaction wheels for a CubeSat mission. The reaction wheels are then simulated for different CubeSat sizes and proved capable of performing attitude maneuvers. During these simulations a non-linear passivity-based sliding surface controller is used which through Lyapunov stability theory has been shown to be uniformly asymptotically stable.
{"title":"Reaction wheel design for CubeSats","authors":"E. Oland, R. Schlanbusch","doi":"10.1109/RAST.2009.5158296","DOIUrl":"https://doi.org/10.1109/RAST.2009.5158296","url":null,"abstract":"This paper presents a reaction wheel design for CubeSats where it takes the limitation of size and mass into consideration. It presents an overview of which altitudes it is feasible to use magnetic torquers for momentum dumping as well as presenting equations for customizing reaction wheels for a CubeSat mission. The reaction wheels are then simulated for different CubeSat sizes and proved capable of performing attitude maneuvers. During these simulations a non-linear passivity-based sliding surface controller is used which through Lyapunov stability theory has been shown to be uniformly asymptotically stable.","PeriodicalId":412236,"journal":{"name":"2009 4th International Conference on Recent Advances in Space Technologies","volume":"32 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129725282","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 : 2009-06-11DOI: 10.1109/RAST.2009.5158194
Teodor-Viorel Chelaru, C. Barbu, Adrian Chelaru
The paper purpose is to dignify some aspects regarding the calculus model and technical solutions for small multistage suborbital launchers used to test spatial equipment and scientific measurements. The calculus methodology consists in numerical simulation of launcher evolution for different start conditions. The rocket model presented will be with six DOF and variable mass. The results analyzed will be the flight parameters and ballistic performances. The discussions area will focus around the technical possibility to realize small suborbital multistage launchers recycling military rocket engines.
{"title":"Mathematical model and technical solution for small multistage suborbital launchers","authors":"Teodor-Viorel Chelaru, C. Barbu, Adrian Chelaru","doi":"10.1109/RAST.2009.5158194","DOIUrl":"https://doi.org/10.1109/RAST.2009.5158194","url":null,"abstract":"The paper purpose is to dignify some aspects regarding the calculus model and technical solutions for small multistage suborbital launchers used to test spatial equipment and scientific measurements. The calculus methodology consists in numerical simulation of launcher evolution for different start conditions. The rocket model presented will be with six DOF and variable mass. The results analyzed will be the flight parameters and ballistic performances. The discussions area will focus around the technical possibility to realize small suborbital multistage launchers recycling military rocket engines.","PeriodicalId":412236,"journal":{"name":"2009 4th International Conference on Recent Advances in Space Technologies","volume":"4 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125591693","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 : 2009-06-11DOI: 10.1109/RAST.2009.5158211
S. Kurnaz, G. Babayeva, R. Rustamov, Elman Aleskerov
The use of advanced technologies is available to enhance planning, design, management, operation and maintenance of the linear infrastructure. Aerial and satellite data based on the remote sensing methods with further integration to GIS technologies represent the area of rapid responds and developments which can be leveraged to assist the linear systems risk assessment to assure the safety of linear infrastructures. Industrial and scientific achievements in satellite remote sensing methods and appropriate data processing techniques are opening a new wide technological opportunities and availabilities to develop an enhanced capability to accomplish the linear systems mapping and safety needs of the oil and gas transportation. Combination of those technologies with GIS has a valuable and significant potential for further application to a huge of cross cutting system of security issues. This paper particularly undertakes the some of aspect of application of those technologies to the linear system monitoring for safety and security assessment.
{"title":"Monitoring of the linear infrastructure: Environmental and social impacts","authors":"S. Kurnaz, G. Babayeva, R. Rustamov, Elman Aleskerov","doi":"10.1109/RAST.2009.5158211","DOIUrl":"https://doi.org/10.1109/RAST.2009.5158211","url":null,"abstract":"The use of advanced technologies is available to enhance planning, design, management, operation and maintenance of the linear infrastructure. Aerial and satellite data based on the remote sensing methods with further integration to GIS technologies represent the area of rapid responds and developments which can be leveraged to assist the linear systems risk assessment to assure the safety of linear infrastructures. Industrial and scientific achievements in satellite remote sensing methods and appropriate data processing techniques are opening a new wide technological opportunities and availabilities to develop an enhanced capability to accomplish the linear systems mapping and safety needs of the oil and gas transportation. Combination of those technologies with GIS has a valuable and significant potential for further application to a huge of cross cutting system of security issues. This paper particularly undertakes the some of aspect of application of those technologies to the linear system monitoring for safety and security assessment.","PeriodicalId":412236,"journal":{"name":"2009 4th International Conference on Recent Advances in Space Technologies","volume":"17 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114530948","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 : 2009-06-11DOI: 10.1109/RAST.2009.5158284
E. Zereik, A. Sorbara, G. Casalino, F. Didot
Objective of the overall system is that of understanding (and demonstrating) what are the tasks that a robotic crew assistant must be able to execute, in order to be effective for space exploration missions. One of the most important tasks to be accomplished is the autonomous grasping of objects, which has been achieved through a vision and force-based control strategy. This paper deals with the completion of the autonomous grasping task previously described.
{"title":"Autonomous dual-arm mobile manipulator crew assistant for surface operations: Force/vision-guided grasping","authors":"E. Zereik, A. Sorbara, G. Casalino, F. Didot","doi":"10.1109/RAST.2009.5158284","DOIUrl":"https://doi.org/10.1109/RAST.2009.5158284","url":null,"abstract":"Objective of the overall system is that of understanding (and demonstrating) what are the tasks that a robotic crew assistant must be able to execute, in order to be effective for space exploration missions. One of the most important tasks to be accomplished is the autonomous grasping of objects, which has been achieved through a vision and force-based control strategy. This paper deals with the completion of the autonomous grasping task previously described.","PeriodicalId":412236,"journal":{"name":"2009 4th International Conference on Recent Advances in Space Technologies","volume":"4 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"117043038","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 : 2009-06-11DOI: 10.1109/RAST.2009.5158201
A. Pourrajabian, M. Bakhtiari, R. Ebrahimi, H. Karimi
In this study, to reduce the drag force, the nose shape of Launch Vehicle with determined flight conditions, is optimized. Two optimization methods are considered: binary genetic algorithm and response surface method. Since the value of drag coefficient is proportional to dynamic pressure, the objective function is based on minimization of drag coefficient in flight conditions which is corresponding to the maximum dynamic pressure. In order to evaluation of objective function, the aerodynamic prediction engineering code is used. The results of aerodynamic prediction code directly entered to binary genetic algorithm code and with common parameters of this algorithm like crossover, mutation and elitism, the optimization process is done. Moreover, the sensibility analysis of this algorithm respect to mutation parameter and size of population is analyzed and optimum values of them are obtained. Also, response Surface Method with quadratic model is considered. Some special points from domain of design variables are selected and corresponding drag coefficients for these points are calculated by aerodynamic prediction engineering code. Then, the appropriate second order surface is fitted to these points regarding to least square method. The results show that with optimum values of genetic algorithm parameters (rate of mutation and size of population); the algorithm converges rapidly with a few generations. In this case, the genetic algorithm only searches the 1.4% of solution space and then converged. Generally, the results show good agreement between two methods.
{"title":"Optimization of nose shape of Launch Vehicle using genetic algorithm and response surface methods","authors":"A. Pourrajabian, M. Bakhtiari, R. Ebrahimi, H. Karimi","doi":"10.1109/RAST.2009.5158201","DOIUrl":"https://doi.org/10.1109/RAST.2009.5158201","url":null,"abstract":"In this study, to reduce the drag force, the nose shape of Launch Vehicle with determined flight conditions, is optimized. Two optimization methods are considered: binary genetic algorithm and response surface method. Since the value of drag coefficient is proportional to dynamic pressure, the objective function is based on minimization of drag coefficient in flight conditions which is corresponding to the maximum dynamic pressure. In order to evaluation of objective function, the aerodynamic prediction engineering code is used. The results of aerodynamic prediction code directly entered to binary genetic algorithm code and with common parameters of this algorithm like crossover, mutation and elitism, the optimization process is done. Moreover, the sensibility analysis of this algorithm respect to mutation parameter and size of population is analyzed and optimum values of them are obtained. Also, response Surface Method with quadratic model is considered. Some special points from domain of design variables are selected and corresponding drag coefficients for these points are calculated by aerodynamic prediction engineering code. Then, the appropriate second order surface is fitted to these points regarding to least square method. The results show that with optimum values of genetic algorithm parameters (rate of mutation and size of population); the algorithm converges rapidly with a few generations. In this case, the genetic algorithm only searches the 1.4% of solution space and then converged. Generally, the results show good agreement between two methods.","PeriodicalId":412236,"journal":{"name":"2009 4th International Conference on Recent Advances in Space Technologies","volume":"50 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115863853","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 : 2009-06-11DOI: 10.1109/RAST.2009.5158216
M. Yağımlı, H. Varol
Mines which are located on the ground have been threating not only military forces but also civilians. These threating mines are classified as wooden, plastic and metal types. In this study a detector, which is able to detect all the mines placed on the ground, has been developed. Detecting and destroying the mines on a suspicious area without personel have been possible with remote control devices. In our work we aimed to produce a GPS-based mobile prototype vehicle carrying a system which can jam electromagnetic waves to blow up the mines with a remote control. This vehicle runs on solar energy and it can be steered by simulation glasses.
{"title":"Mine detecting GPS-based unmanned ground vehicle","authors":"M. Yağımlı, H. Varol","doi":"10.1109/RAST.2009.5158216","DOIUrl":"https://doi.org/10.1109/RAST.2009.5158216","url":null,"abstract":"Mines which are located on the ground have been threating not only military forces but also civilians. These threating mines are classified as wooden, plastic and metal types. In this study a detector, which is able to detect all the mines placed on the ground, has been developed. Detecting and destroying the mines on a suspicious area without personel have been possible with remote control devices. In our work we aimed to produce a GPS-based mobile prototype vehicle carrying a system which can jam electromagnetic waves to blow up the mines with a remote control. This vehicle runs on solar energy and it can be steered by simulation glasses.","PeriodicalId":412236,"journal":{"name":"2009 4th International Conference on Recent Advances in Space Technologies","volume":"10 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115092080","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 : 2009-06-11DOI: 10.1109/RAST.2009.5158207
H. Akah, A. Kamel, H. El-Hennawy
This paper studies the feasibility of using adaptive pulse shaping CP-OFDM in remote sensing satellites. A set of pulse shapes were generated using genetic algorithm that minimizes the mean square error of the timing offset estimator. These pulse shapes were used to train function approximation neural networks. Such neural networks make the use of adaptive pulse shaping in OFDM systems feasible. Results from neural networks simulation, which have shown the ability of neural networks to fulfill such function for a two ray model channels, are presented.
{"title":"Adaptive pulse shaped CP-OFDM for remote sensing satellites","authors":"H. Akah, A. Kamel, H. El-Hennawy","doi":"10.1109/RAST.2009.5158207","DOIUrl":"https://doi.org/10.1109/RAST.2009.5158207","url":null,"abstract":"This paper studies the feasibility of using adaptive pulse shaping CP-OFDM in remote sensing satellites. A set of pulse shapes were generated using genetic algorithm that minimizes the mean square error of the timing offset estimator. These pulse shapes were used to train function approximation neural networks. Such neural networks make the use of adaptive pulse shaping in OFDM systems feasible. Results from neural networks simulation, which have shown the ability of neural networks to fulfill such function for a two ray model channels, are presented.","PeriodicalId":412236,"journal":{"name":"2009 4th International Conference on Recent Advances in Space Technologies","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126549186","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 : 2009-06-11DOI: 10.1109/RAST.2009.5158280
M.Ayub Khan, Yousuf Zai, M. Hussain, M. Ansari
Phenomena like, atmospheric pollution, temperature variability, global warming, or ozone layer depletion (OLD) may be analyzed for forecasts etc. by solving the primitive dynamic equations along with the continuity and energy ones. The environmental variables actually observed are the consequences of thousand of events, some of which may be poorly defined or imperfectly understood. However, such atmospheric models of meteorological phenomena are simplistic in their nature, in the sense of largely hiding the character of nature as it ‘really’ is. This failure of reaching an exact solution and the fact that environmental phenomena nearly always include random components prompt us to leave the purely deterministic approach and invoke instead pseudo-randomness or randomness (stochasticity).
{"title":"Investigating chaos in ozone layer depletion at Pakistan air space","authors":"M.Ayub Khan, Yousuf Zai, M. Hussain, M. Ansari","doi":"10.1109/RAST.2009.5158280","DOIUrl":"https://doi.org/10.1109/RAST.2009.5158280","url":null,"abstract":"Phenomena like, atmospheric pollution, temperature variability, global warming, or ozone layer depletion (OLD) may be analyzed for forecasts etc. by solving the primitive dynamic equations along with the continuity and energy ones. The environmental variables actually observed are the consequences of thousand of events, some of which may be poorly defined or imperfectly understood. However, such atmospheric models of meteorological phenomena are simplistic in their nature, in the sense of largely hiding the character of nature as it ‘really’ is. This failure of reaching an exact solution and the fact that environmental phenomena nearly always include random components prompt us to leave the purely deterministic approach and invoke instead pseudo-randomness or randomness (stochasticity).","PeriodicalId":412236,"journal":{"name":"2009 4th International Conference on Recent Advances in Space Technologies","volume":"43 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126063679","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 : 2009-06-11DOI: 10.1109/RAST.2009.5158254
H. Soken, C. Hajiyev
Thus far, Kalman filter based attitude estimation algorithms have been used in many space applications. When the issue of pico satellite attitude estimation is taken into consideration, general linear approach to Kalman filter becomes insufficient and Extended Kalman Filters (EKF) are the types of filters, which are designed in order to overrun this problem. However, in case of attitude estimation of a pico satellite via magnetometer data, where the nonlinearity degree of both dynamics and measurement models are high, EKF may give inaccurate results. Unscented Kalman Filter (UKF) that does not require linearization phase and so Jacobians can be preferred instead of EKF in such circumstances. Nonetheless, if the UKF is built with an adaptive manner, such that, faulty measurements do not affect attitude estimation process, accurate estimation results even in case of measurement malfunctions can be guaranteed. In this study an Adaptive Unscented Kalman Filter with multiple fading factors based gain correction is introduced and tested on the attitude estimation system of a pico satellite by the use of simulations.
{"title":"Adaptive Unscented Kalman Filter with multiple fading factors for pico satellite attitude estimation","authors":"H. Soken, C. Hajiyev","doi":"10.1109/RAST.2009.5158254","DOIUrl":"https://doi.org/10.1109/RAST.2009.5158254","url":null,"abstract":"Thus far, Kalman filter based attitude estimation algorithms have been used in many space applications. When the issue of pico satellite attitude estimation is taken into consideration, general linear approach to Kalman filter becomes insufficient and Extended Kalman Filters (EKF) are the types of filters, which are designed in order to overrun this problem. However, in case of attitude estimation of a pico satellite via magnetometer data, where the nonlinearity degree of both dynamics and measurement models are high, EKF may give inaccurate results. Unscented Kalman Filter (UKF) that does not require linearization phase and so Jacobians can be preferred instead of EKF in such circumstances. Nonetheless, if the UKF is built with an adaptive manner, such that, faulty measurements do not affect attitude estimation process, accurate estimation results even in case of measurement malfunctions can be guaranteed. In this study an Adaptive Unscented Kalman Filter with multiple fading factors based gain correction is introduced and tested on the attitude estimation system of a pico satellite by the use of simulations.","PeriodicalId":412236,"journal":{"name":"2009 4th International Conference on Recent Advances in Space Technologies","volume":"116 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124133246","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 : 2009-06-11DOI: 10.1109/RAST.2009.5158260
Farid Gulmammadov
Inertial sensors have a broad field of applications and are especially essential for localization. One of the most severe errors of MEMS inertial sensors is bias drift. In this paper bias drift is mathematically modeled as a combination of time and temperature dependent behaviors which are fused together allowing online bias compensation. The example presented indicates an almost perfect estimation resulting in elimination of more than 99% of bias. In this paper, also, a novel technique for modeling systems with hysteresis is presented.
{"title":"Analysis, modeling and compensation of bias drift in MEMS inertial sensors","authors":"Farid Gulmammadov","doi":"10.1109/RAST.2009.5158260","DOIUrl":"https://doi.org/10.1109/RAST.2009.5158260","url":null,"abstract":"Inertial sensors have a broad field of applications and are especially essential for localization. One of the most severe errors of MEMS inertial sensors is bias drift. In this paper bias drift is mathematically modeled as a combination of time and temperature dependent behaviors which are fused together allowing online bias compensation. The example presented indicates an almost perfect estimation resulting in elimination of more than 99% of bias. In this paper, also, a novel technique for modeling systems with hysteresis is presented.","PeriodicalId":412236,"journal":{"name":"2009 4th International Conference on Recent Advances in Space Technologies","volume":"110 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129699043","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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