Pub Date : 2015-06-16DOI: 10.1109/RAST.2015.7208426
I. Bekmezci, Ismail Sen, Ercan Erkalkan
One of the most important design problems for the multi unmanned aerial vehicles systems is communication between UAVs. In a multi-UAV system, the communication between UAVs is provided with all UAVs connecting directly to the ground station via satellite or infrastructure. However, infrastructure or satellite-based communication architectures restrict the capabilities of the multi-UAV systems. Infrastructure or satellite-based communication problems of multi-UAV systems can be solved with ad hoc networks among UAVs. This special ad hoc network structure is called as FANET. In this paper, a FANET test bed implementation study is presented.
{"title":"Flying ad hoc networks (FANET) test bed implementation","authors":"I. Bekmezci, Ismail Sen, Ercan Erkalkan","doi":"10.1109/RAST.2015.7208426","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208426","url":null,"abstract":"One of the most important design problems for the multi unmanned aerial vehicles systems is communication between UAVs. In a multi-UAV system, the communication between UAVs is provided with all UAVs connecting directly to the ground station via satellite or infrastructure. However, infrastructure or satellite-based communication architectures restrict the capabilities of the multi-UAV systems. Infrastructure or satellite-based communication problems of multi-UAV systems can be solved with ad hoc networks among UAVs. This special ad hoc network structure is called as FANET. In this paper, a FANET test bed implementation study is presented.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"65 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-06-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114803960","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 : 2015-06-16DOI: 10.1109/RAST.2015.7208374
T. Sorensen, E. Pilger, M. Nunes
The Hawaii Space Flight Laboratory (HSFL) at the University of Hawaii at Manoa developed the Comprehensive Open-architecture Solution for Mission Operations Systems (COSMOS) under a three-year NASA grant. This innovative suite of software and hardware was initially designed for supporting the operations of multiple small satellites, but during its development, it evolved into a comprehensive system of systems that is capable of providing nearly all operations functions to support an integrated system of objects to be monitored and controlled, called nodes. These nodes are not limited to spacecraft, but can be almost any type of vehicle or electronic entity that has communication connectivity with the distributed COSMOS system. Even the vehicles themselves can operate COSMOS as their onboard controlling software. HSFL built a 55-kg satellite called Hiakasat that is due to launch on the ORS-4 mission in 2015. This satellite uses COSMOS for its onboard flight software, which integrates seamlessly with the COSMOS system that is being used to operate the mission on the ground. COSMOS is currently being used to monitor research ship gathering data, and even controlling rovers on simulated lunar missions. This innovative nodal architecture will allow a fully integrated system that can combine satellites with UAVs, submersible, ships, and other robotic craft.
{"title":"COSMOS — An innovative nodal architecture for controlling large numbers of small satellites and other diverse assets","authors":"T. Sorensen, E. Pilger, M. Nunes","doi":"10.1109/RAST.2015.7208374","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208374","url":null,"abstract":"The Hawaii Space Flight Laboratory (HSFL) at the University of Hawaii at Manoa developed the Comprehensive Open-architecture Solution for Mission Operations Systems (COSMOS) under a three-year NASA grant. This innovative suite of software and hardware was initially designed for supporting the operations of multiple small satellites, but during its development, it evolved into a comprehensive system of systems that is capable of providing nearly all operations functions to support an integrated system of objects to be monitored and controlled, called nodes. These nodes are not limited to spacecraft, but can be almost any type of vehicle or electronic entity that has communication connectivity with the distributed COSMOS system. Even the vehicles themselves can operate COSMOS as their onboard controlling software. HSFL built a 55-kg satellite called Hiakasat that is due to launch on the ORS-4 mission in 2015. This satellite uses COSMOS for its onboard flight software, which integrates seamlessly with the COSMOS system that is being used to operate the mission on the ground. COSMOS is currently being used to monitor research ship gathering data, and even controlling rovers on simulated lunar missions. This innovative nodal architecture will allow a fully integrated system that can combine satellites with UAVs, submersible, ships, and other robotic craft.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"6 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-06-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130524248","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 : 2015-06-16DOI: 10.1109/RAST.2015.7208334
A. Şen, Cem Tansu, Erdogan C. Unlusoy, Metehan Yurt, Noyan Evirgen, O. Sakinci, B. Akbulut
This paper introduces the proof of concept of low-Earth-orbit satellite attitude determination using GNSS, mainly GPS satellite signals. Two methods are considered and compared in detail: carrier phase measurements and signal-to-noise ratio (SNR-RSS) method. A preliminary design to be used in testing the algorithms is explained, and results of simulations with RSS method are presented.
{"title":"Proof of concept for satellite attitude determination using GNSS","authors":"A. Şen, Cem Tansu, Erdogan C. Unlusoy, Metehan Yurt, Noyan Evirgen, O. Sakinci, B. Akbulut","doi":"10.1109/RAST.2015.7208334","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208334","url":null,"abstract":"This paper introduces the proof of concept of low-Earth-orbit satellite attitude determination using GNSS, mainly GPS satellite signals. Two methods are considered and compared in detail: carrier phase measurements and signal-to-noise ratio (SNR-RSS) method. A preliminary design to be used in testing the algorithms is explained, and results of simulations with RSS method are presented.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"31 1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-06-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125701569","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 : 2015-06-16DOI: 10.1109/RAST.2015.7208437
Murat Bağci, Cengiz Hacizade
Determination and control of the satellite's orbit is acting vital role on space mission. Accuracy in calculations for position and velocity of such a satellite is important for fulfilling the tasks. The motion of a Low Earth Orbit (LEO) satellite can be modelled with Keplerian equations. In this study, we use Keplerian equations to construct dynamic model of LEO satellite and analyze performances of three numerical methods (Newton-Raphson, Bancroft and Matlab fsolve) in Global Positioning System (GPS) based trilateration problem solving.
{"title":"Performance analysis of GPS based orbit determination via numerical methods for a LEO satellite","authors":"Murat Bağci, Cengiz Hacizade","doi":"10.1109/RAST.2015.7208437","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208437","url":null,"abstract":"Determination and control of the satellite's orbit is acting vital role on space mission. Accuracy in calculations for position and velocity of such a satellite is important for fulfilling the tasks. The motion of a Low Earth Orbit (LEO) satellite can be modelled with Keplerian equations. In this study, we use Keplerian equations to construct dynamic model of LEO satellite and analyze performances of three numerical methods (Newton-Raphson, Bancroft and Matlab fsolve) in Global Positioning System (GPS) based trilateration problem solving.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"9 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-06-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122310971","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 : 2015-06-16DOI: 10.1109/RAST.2015.7208392
E. Erdem, F. Ankan, M. N. Deviren, I. Cor
A wave propagation model based on ray tracing for anisotropic and inhomogeneous ionosphere is described in this paper. A modular software tool, named IONOLAB-RAY, is developed to represent ray tracing through the spherical 3D grid model of the ionosphere. Physical parameters of the ionosphere are obtained from IRI-Plas-G for each grid volume. Refractive index of each grid volume is calculated by using Appleton-Hartree formula, which represents the effects of Earth's magnetic field, electron cyclotron frequency and collision frequency. The user has the opportunity to import GIM-TEC data, so that physical parameters of ionosphere can be obtained from a more realistic model especially at storm days.
{"title":"A model based ray tracing algorithm for anisotropic and inhomogeneous ionosphere with GIM-TEC assimilation","authors":"E. Erdem, F. Ankan, M. N. Deviren, I. Cor","doi":"10.1109/RAST.2015.7208392","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208392","url":null,"abstract":"A wave propagation model based on ray tracing for anisotropic and inhomogeneous ionosphere is described in this paper. A modular software tool, named IONOLAB-RAY, is developed to represent ray tracing through the spherical 3D grid model of the ionosphere. Physical parameters of the ionosphere are obtained from IRI-Plas-G for each grid volume. Refractive index of each grid volume is calculated by using Appleton-Hartree formula, which represents the effects of Earth's magnetic field, electron cyclotron frequency and collision frequency. The user has the opportunity to import GIM-TEC data, so that physical parameters of ionosphere can be obtained from a more realistic model especially at storm days.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"21 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-06-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123402708","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 : 2015-06-16DOI: 10.1109/RAST.2015.7208337
A. F. Yagli, H. Ertok, S. Gulgonul, E. Goehler, J. Winkel
In this paper, a regional positioning system using three geosynchronous Turksat satellites is explained. A time code signal is transmitted via three satellites to the user at the Earth, while the user calculates the latitude and longitude position coordinates from the time difference of arrivals of the signals from the satellites. The attitude information is assumed to be measured by the user.
{"title":"Turksat regional positioning system development","authors":"A. F. Yagli, H. Ertok, S. Gulgonul, E. Goehler, J. Winkel","doi":"10.1109/RAST.2015.7208337","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208337","url":null,"abstract":"In this paper, a regional positioning system using three geosynchronous Turksat satellites is explained. A time code signal is transmitted via three satellites to the user at the Earth, while the user calculates the latitude and longitude position coordinates from the time difference of arrivals of the signals from the satellites. The attitude information is assumed to be measured by the user.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"202 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-06-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131453971","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 : 2015-06-16DOI: 10.1109/RAST.2015.7208332
Y. Parali, E. M. Jafarov
In this work robust autopilot is developed for highly maneuverable nonminimum phase missile system by using sliding mode control algorithm. Nonminimum phase nature of tail controlled missiles prevents direct implementation of Sliding Mode Control algorithms. Sliding mode control methods are not suitable to implement in nonminimum phase system because of unstable zero dynamics. To overcome this difficulty a new output redefinition technique is developed. The method is based on constructing a minimum phase ideal system that behaves similar to actual system. Outputs of the actual system and ideal system are blended to generate a virtual output and with this output the system becomes minimum phase or very slightly nonminimum phase. The sliding mode control algorithm can be used to control this virtual system. Because the outputs of virtual and real systems are converging, output tracking of the virtual systems also provides output tracking for real system. Simulation results shows that proposed output redefinition technique is successful for implementing sliding mode control schemes into nonminimum phase system.
{"title":"Output redefinition method for sliding mode control of nonminimum phase missile systems","authors":"Y. Parali, E. M. Jafarov","doi":"10.1109/RAST.2015.7208332","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208332","url":null,"abstract":"In this work robust autopilot is developed for highly maneuverable nonminimum phase missile system by using sliding mode control algorithm. Nonminimum phase nature of tail controlled missiles prevents direct implementation of Sliding Mode Control algorithms. Sliding mode control methods are not suitable to implement in nonminimum phase system because of unstable zero dynamics. To overcome this difficulty a new output redefinition technique is developed. The method is based on constructing a minimum phase ideal system that behaves similar to actual system. Outputs of the actual system and ideal system are blended to generate a virtual output and with this output the system becomes minimum phase or very slightly nonminimum phase. The sliding mode control algorithm can be used to control this virtual system. Because the outputs of virtual and real systems are converging, output tracking of the virtual systems also provides output tracking for real system. Simulation results shows that proposed output redefinition technique is successful for implementing sliding mode control schemes into nonminimum phase system.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-06-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130727782","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 : 2015-06-16DOI: 10.1109/RAST.2015.7208406
U. Leloglu, E. Tunali, Yuksel Subasi
In this work, a compact imager design concept for micro and nano satellites is introduced. Although the performances of these platforms are increasing, the imagers cannot keep up with the platforms due to mass and volume limitations. Hence payloads require novel designs to have better imagers on board of these platforms, in terms of spectral resolution, spatial resolution, signal to noise ratio and field of view. The concept that we present here involves an object-space flat mirror that can be rotated around two orthogonal axes. One of the movements helps scanning the Earth in cross-track direction while the other movement helps increasing the integration time by forward motion compensation. When used in combination with a frame sensor covered with parallel filter strips, the camera can fulfill all of the above mentioned requirements simultaneously with an optimal performance. To demonstrate the effectiveness of the concept, an example design is shown that can fit into a three unit cubesat.
{"title":"A compact imager design concept for micro/nanosatellites using scanning mirrors","authors":"U. Leloglu, E. Tunali, Yuksel Subasi","doi":"10.1109/RAST.2015.7208406","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208406","url":null,"abstract":"In this work, a compact imager design concept for micro and nano satellites is introduced. Although the performances of these platforms are increasing, the imagers cannot keep up with the platforms due to mass and volume limitations. Hence payloads require novel designs to have better imagers on board of these platforms, in terms of spectral resolution, spatial resolution, signal to noise ratio and field of view. The concept that we present here involves an object-space flat mirror that can be rotated around two orthogonal axes. One of the movements helps scanning the Earth in cross-track direction while the other movement helps increasing the integration time by forward motion compensation. When used in combination with a frame sensor covered with parallel filter strips, the camera can fulfill all of the above mentioned requirements simultaneously with an optimal performance. To demonstrate the effectiveness of the concept, an example design is shown that can fit into a three unit cubesat.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"64 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-06-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131062672","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 : 2015-06-16DOI: 10.1109/RAST.2015.7208346
Kadir Ozden, O. M. Yucedag, H. Kocer
Metamaterials have great potential for the practical applications of stealth technology. Therefore, it is important to understand effect of their geometrical parameters on the electromagnetic wave absorption. In this paper, dependence of the absorption on certain geometrical parameters of a metamaterial absorber is numerically investigated.
{"title":"Geometrical parameter investigation of metamaterial absorber for space based remote sensing applications","authors":"Kadir Ozden, O. M. Yucedag, H. Kocer","doi":"10.1109/RAST.2015.7208346","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208346","url":null,"abstract":"Metamaterials have great potential for the practical applications of stealth technology. Therefore, it is important to understand effect of their geometrical parameters on the electromagnetic wave absorption. In this paper, dependence of the absorption on certain geometrical parameters of a metamaterial absorber is numerically investigated.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"41 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-06-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126917349","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 : 2015-06-16DOI: 10.1109/RAST.2015.7208428
O. Zorlu
The Capacitated Vehicle Routing Problem (CVRP), is a capacity constrained type of vehicle routing problem, which is widely studied with many real-world applications. Based on this problem there are many researches and proposed papers depend on different types of algorithms. However, genetic algorithm based methods are scarcely proposed in the literature. In this paper, genetic algorithms are examined to routing unmanned aerial vehicles as adapting to capacitated vehicle routing problems. Researches based on this problem with genetic algorithms are discussed and simulation results for CVRP with genetic algorithms are implemented. It is also presented and discussed with the experimental results and compared our method with the some well-known benchmark algorithms.
{"title":"Routing unmanned aerial vehicles as adapting to capacitated vehicle routing problem with genetic algorithms","authors":"O. Zorlu","doi":"10.1109/RAST.2015.7208428","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208428","url":null,"abstract":"The Capacitated Vehicle Routing Problem (CVRP), is a capacity constrained type of vehicle routing problem, which is widely studied with many real-world applications. Based on this problem there are many researches and proposed papers depend on different types of algorithms. However, genetic algorithm based methods are scarcely proposed in the literature. In this paper, genetic algorithms are examined to routing unmanned aerial vehicles as adapting to capacitated vehicle routing problems. Researches based on this problem with genetic algorithms are discussed and simulation results for CVRP with genetic algorithms are implemented. It is also presented and discussed with the experimental results and compared our method with the some well-known benchmark algorithms.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"17 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-06-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123269868","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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