Pub Date : 2015-06-16DOI: 10.1109/RAST.2015.7208447
M. Cho, Masui Hirokazu, F. Graziani
There is increasing demand of small satellite development and utilization worldwide. The recent explosive growth of the small satellite launch has caused significant concerns among traditional space sector. Peaceful coexistence of the traditional sector and the emerging sector is crucial. There is a need to define “what is a small satellite” and lay out the requirements of small satellites. In 2014, an activity started to make an ISO standard to describe definition and requirements of small satellites. In parallel, a new study group was initiated at International Academy of Astronautics. The study group intends to make an important input to the ISO standard. Definition of small satellite was discussed extensively in the study group. The majority of the opinions were that mass nor size is not suitable for definition of small satellites and they should be defined by the philosophy of design, manufacturing, mission, program management and others. The workshop came to conclusion that “lean satellite” is the most suitable word to describe a satellite that utilizes untraditional risk-taking development approaches to achieve low-cost and fast-delivery with a small number of team. This paper provides the recent update on the lean satellite standard.
{"title":"Introduction to lean satellite and ISO standard for lean satellite","authors":"M. Cho, Masui Hirokazu, F. Graziani","doi":"10.1109/RAST.2015.7208447","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208447","url":null,"abstract":"There is increasing demand of small satellite development and utilization worldwide. The recent explosive growth of the small satellite launch has caused significant concerns among traditional space sector. Peaceful coexistence of the traditional sector and the emerging sector is crucial. There is a need to define “what is a small satellite” and lay out the requirements of small satellites. In 2014, an activity started to make an ISO standard to describe definition and requirements of small satellites. In parallel, a new study group was initiated at International Academy of Astronautics. The study group intends to make an important input to the ISO standard. Definition of small satellite was discussed extensively in the study group. The majority of the opinions were that mass nor size is not suitable for definition of small satellites and they should be defined by the philosophy of design, manufacturing, mission, program management and others. The workshop came to conclusion that “lean satellite” is the most suitable word to describe a satellite that utilizes untraditional risk-taking development approaches to achieve low-cost and fast-delivery with a small number of team. This paper provides the recent update on the lean satellite standard.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"5 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":"124035780","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.2015.7208381
Fatih Yılmaz, Ozan Oguz Haktanir, A. B. Uygur
Satellites are exposed to simultaneous static and dynamic loads during the launch phase due to launcher acceleration and aerodynamics. Therefore, they are designed and tested to withstand all these loads. From design perspective, a common approach is to combine static and dynamic loads into an equivalent static load which is referred to as quasi-static loads [1]. The validation of the structural design of the satellite is performed by tests and/or analysis. This paper discusses the static load test methods with an emphasis on the acceleration tests performed on vibration test systems.
{"title":"Quasi-static structural test of satellites","authors":"Fatih Yılmaz, Ozan Oguz Haktanir, A. B. Uygur","doi":"10.1109/RAST.2015.7208381","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208381","url":null,"abstract":"Satellites are exposed to simultaneous static and dynamic loads during the launch phase due to launcher acceleration and aerodynamics. Therefore, they are designed and tested to withstand all these loads. From design perspective, a common approach is to combine static and dynamic loads into an equivalent static load which is referred to as quasi-static loads [1]. The validation of the structural design of the satellite is performed by tests and/or analysis. This paper discusses the static load test methods with an emphasis on the acceleration tests performed on vibration test systems.","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":"129442633","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.2015.7208420
O. Korkmaz, Sina Jahanbakhsh, M. Çelik, H. Kurt
Development of reliable, successful and robust technologies for space systems demands realistic testing facilities. Low pressure levels are required for simulating the space vacuum conditions in earth's orbit or interplanetary-space. Therefore, establishment of a vacuum facility devoted specifically to the testing of thrusters is needed in order to develop, study and test thrusters to be deployed on spacecraft or satellites. In this study, the design, acquisition and manufacturing processes, and capabilities of a 1.5 m diameter and 2.7 m long cylindrical vacuum facility, that will primarily be used for the development and testing of electric spacecraft thrusters, at the Bogazici University Space Technologies Laboratory (BUSTLab) are presented.
{"title":"Space propulsion research vacuum facility of the Bogazici University space technologies laboratory","authors":"O. Korkmaz, Sina Jahanbakhsh, M. Çelik, H. Kurt","doi":"10.1109/RAST.2015.7208420","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208420","url":null,"abstract":"Development of reliable, successful and robust technologies for space systems demands realistic testing facilities. Low pressure levels are required for simulating the space vacuum conditions in earth's orbit or interplanetary-space. Therefore, establishment of a vacuum facility devoted specifically to the testing of thrusters is needed in order to develop, study and test thrusters to be deployed on spacecraft or satellites. In this study, the design, acquisition and manufacturing processes, and capabilities of a 1.5 m diameter and 2.7 m long cylindrical vacuum facility, that will primarily be used for the development and testing of electric spacecraft thrusters, at the Bogazici University Space Technologies Laboratory (BUSTLab) are presented.","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":"129826123","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.2015.7208344
Huseyin Ackin Erdem, G. Yilmaz
In this study, a satellite surveillance system has been created for wireless ad-hoc networks using network simulator-2 (ns2). Ad-hoc networks are infrastructure-less wireless networks which have no fixed network topology due to mobile nodes. In ad-hoc networks, the most important point is to find a communication path (routing). This study uses Ad-Hoc On-Demand Distance Vector (AODV) routing protocol as it discovers and maintains routes on demand and when the route to destination is unknown. In this routing protocol, routes to destinations are only maintained by nodes which are actively used in this route. Two wireless network scenarios with Constant-Bit Rate (CBR) traffics are investigated in this study. First scenario examines how node mobility affects the routing process and the second scenario simulates how congestion in nodes affects the routing mechanism.
{"title":"Creating ad-hoc networks for remote sensing: Routing simulation of a satellite surveillance system","authors":"Huseyin Ackin Erdem, G. Yilmaz","doi":"10.1109/RAST.2015.7208344","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208344","url":null,"abstract":"In this study, a satellite surveillance system has been created for wireless ad-hoc networks using network simulator-2 (ns2). Ad-hoc networks are infrastructure-less wireless networks which have no fixed network topology due to mobile nodes. In ad-hoc networks, the most important point is to find a communication path (routing). This study uses Ad-Hoc On-Demand Distance Vector (AODV) routing protocol as it discovers and maintains routes on demand and when the route to destination is unknown. In this routing protocol, routes to destinations are only maintained by nodes which are actively used in this route. Two wireless network scenarios with Constant-Bit Rate (CBR) traffics are investigated in this study. First scenario examines how node mobility affects the routing process and the second scenario simulates how congestion in nodes affects the routing mechanism.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"45 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":"127075139","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.2015.7208425
Serkan Caska, A. Gayretli
In the past decade Unmanned Vehicles have become a topic of interest in many research organizations. Unmanned vehicles based systems are integrated to many applications in various areas ranging from military missions to wildfire detection. Recently, there has been a great interest to design collaborative systems of unmanned air vehicles (UAV) and unmanned ground vehicles (UGV). This paper proposes a new algorithm that can be used to calculate optimal UAV paths and UAV-UGV quantities to cover a target area. This algorithm is useful for patrolling systems based on the collaboration of unmanned air vehicles and unmanned ground vehicles.
{"title":"An algorithm for collaborative patrolling systems with unmanned air vehicles and unmanned ground vehicles","authors":"Serkan Caska, A. Gayretli","doi":"10.1109/RAST.2015.7208425","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208425","url":null,"abstract":"In the past decade Unmanned Vehicles have become a topic of interest in many research organizations. Unmanned vehicles based systems are integrated to many applications in various areas ranging from military missions to wildfire detection. Recently, there has been a great interest to design collaborative systems of unmanned air vehicles (UAV) and unmanned ground vehicles (UGV). This paper proposes a new algorithm that can be used to calculate optimal UAV paths and UAV-UGV quantities to cover a target area. This algorithm is useful for patrolling systems based on the collaboration of unmanned air vehicles and unmanned ground vehicles.","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":"130904176","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.2015.7208370
J. Tayebi, A. Soleymani
In this paper, nonlinear attitude model of a satellite with pyramid Control Moment Gyros (CMG) and other with pyramid Fluid Momentum Controller (FMC) is developed. A comparative study between pyramidal cluster of FMC and CMG is conducted. This comparison is based on simulation of attitude control system a Nano satellite with two different actuators. For comparison purposes, a sliding mode controller based on modified Rodriguez parameters is considered for attitude control system. The efficiency of maneuvers, agility, power consumption, mass and capability of combination actuators have been compared for two different actuators. Results show that both systems successfully conducted different agile maneuvers and have a good performance in controller against disturbance. In same power consumption, capacity of CMG torque generation is more than FMC actuators.
{"title":"A comparative study of CMG and FMC actuators for Nano satellite attitude control system-pyramidal configuration","authors":"J. Tayebi, A. Soleymani","doi":"10.1109/RAST.2015.7208370","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208370","url":null,"abstract":"In this paper, nonlinear attitude model of a satellite with pyramid Control Moment Gyros (CMG) and other with pyramid Fluid Momentum Controller (FMC) is developed. A comparative study between pyramidal cluster of FMC and CMG is conducted. This comparison is based on simulation of attitude control system a Nano satellite with two different actuators. For comparison purposes, a sliding mode controller based on modified Rodriguez parameters is considered for attitude control system. The efficiency of maneuvers, agility, power consumption, mass and capability of combination actuators have been compared for two different actuators. Results show that both systems successfully conducted different agile maneuvers and have a good performance in controller against disturbance. In same power consumption, capacity of CMG torque generation is more than FMC actuators.","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":"131003724","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.2015.7208394
M. Koroglu, F. Arıkan, O. Koroglu
Ionosphere is an ionized layer of atmosphere and affects radio signals due to its variable electron density. Total Electron Content (TEC) and Slant Electron Content (STEC) is a measure of the ionizing of the electrons along a ray path in the ionosphere. STEC values of the ionosphere can be estimated by IONOLAB-TEC method. During extreme ionospheric storms gradients becomes larger than those of quiet days since time delays of the radio signals becomes anomalous. In this study, ionospheric gradients over Turkey are estimated using the Turkish National Permanent GPS Network (TNPGN-Active) between May 2009 and September 2012. GPS-STEC for each station is calculated using IONOLAB-TEC and IONOLAB-BIAS methods (www.ionolab.org). Significant variations in the structure of station-pair gradients have been observed depending on location of station-pairs, the path of the satellites, strength of the geomagnetic storms and type, depth and magnitude of the earthquakes.
{"title":"Detection of ionospheric disturbances over Turkey using ionospheric spatial gradient estimates","authors":"M. Koroglu, F. Arıkan, O. Koroglu","doi":"10.1109/RAST.2015.7208394","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208394","url":null,"abstract":"Ionosphere is an ionized layer of atmosphere and affects radio signals due to its variable electron density. Total Electron Content (TEC) and Slant Electron Content (STEC) is a measure of the ionizing of the electrons along a ray path in the ionosphere. STEC values of the ionosphere can be estimated by IONOLAB-TEC method. During extreme ionospheric storms gradients becomes larger than those of quiet days since time delays of the radio signals becomes anomalous. In this study, ionospheric gradients over Turkey are estimated using the Turkish National Permanent GPS Network (TNPGN-Active) between May 2009 and September 2012. GPS-STEC for each station is calculated using IONOLAB-TEC and IONOLAB-BIAS methods (www.ionolab.org). Significant variations in the structure of station-pair gradients have been observed depending on location of station-pairs, the path of the satellites, strength of the geomagnetic storms and type, depth and magnitude of the earthquakes.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"77 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":"115851207","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.2015.7208450
H. Masui, M. Cho, T. Hatamura, Tatsuo Shimizu
This paper describes that activity and strategy for Lean satellite in Kyushu Institute of Technology (KIT) and explain following 3 main works for Lean satellite community. First one is supporting environmental testing in Center of Lean Satellite (CeNT). CeNT provides most of requested environmental testing such as vibration, shock and thermal vacuum to outside satellite developers. Second work is developing satellite in KIT. We are developing 2 Lean satellites as Horyu-4 AEIGS and AOBA-VELOX III. Third work is the establishment of ISO standard relative to environmental testing for Lean satellite. Finally, the future plan will be explained.
{"title":"Activity and strategy for lean satellite in Kyushu Institute of Technology","authors":"H. Masui, M. Cho, T. Hatamura, Tatsuo Shimizu","doi":"10.1109/RAST.2015.7208450","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208450","url":null,"abstract":"This paper describes that activity and strategy for Lean satellite in Kyushu Institute of Technology (KIT) and explain following 3 main works for Lean satellite community. First one is supporting environmental testing in Center of Lean Satellite (CeNT). CeNT provides most of requested environmental testing such as vibration, shock and thermal vacuum to outside satellite developers. Second work is developing satellite in KIT. We are developing 2 Lean satellites as Horyu-4 AEIGS and AOBA-VELOX III. Third work is the establishment of ISO standard relative to environmental testing for Lean satellite. Finally, the future plan will be explained.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"19 7 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":"121037169","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.2015.7208422
O. Starinova, R. Khabibullin, I. Gorbunova
This paper discusses application of computerassisted design system to development of a solar sail powered spacecraft. Minimum orbit altitude is calculated; also non-linear static analysis for frame-type solar sail is performed in finite elements simulation system. Moreover, mathematical model of small solar sail spacecraft motion is considered. Finally, the analysis of this motion is performed.
{"title":"The project of the small frame-type solar sail spacecraft","authors":"O. Starinova, R. Khabibullin, I. Gorbunova","doi":"10.1109/RAST.2015.7208422","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208422","url":null,"abstract":"This paper discusses application of computerassisted design system to development of a solar sail powered spacecraft. Minimum orbit altitude is calculated; also non-linear static analysis for frame-type solar sail is performed in finite elements simulation system. Moreover, mathematical model of small solar sail spacecraft motion is considered. Finally, the analysis of this motion is performed.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"12 3","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-06-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114046276","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.2015.7208448
Yasuyuki Miyazaki, Noboru Tada, S. Inoue, Akihiro Tamura, M. Yamazaki
Recently, space science mission has been more and more complicated and advanced. Its scale has been larger and larger. Accordingly deployable structure grows increasingly important. The space verification is quite important or necessary for deployable structures that have not been proved in space. Thus more and more opportunities with low-cost are desired for the space verification. Nano-satellite in low earth orbit is most suitable for the test-bed of the small scale model of the structures. Moreover, such a deployable structure can be used as the deorbit device, so that it can be a solution of the space debris issue. This paper discusses the importance and the methodology of the space verification of the key technologies for advanced large deployable structures by using nano-satellites.
{"title":"Space verification of advanced deployable structure by using nano-satellite","authors":"Yasuyuki Miyazaki, Noboru Tada, S. Inoue, Akihiro Tamura, M. Yamazaki","doi":"10.1109/RAST.2015.7208448","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208448","url":null,"abstract":"Recently, space science mission has been more and more complicated and advanced. Its scale has been larger and larger. Accordingly deployable structure grows increasingly important. The space verification is quite important or necessary for deployable structures that have not been proved in space. Thus more and more opportunities with low-cost are desired for the space verification. Nano-satellite in low earth orbit is most suitable for the test-bed of the small scale model of the structures. Moreover, such a deployable structure can be used as the deorbit device, so that it can be a solution of the space debris issue. This paper discusses the importance and the methodology of the space verification of the key technologies for advanced large deployable structures by using nano-satellites.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"58 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":"127709203","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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