Pub Date : 2015-06-16DOI: 10.1109/RAST.2015.7208430
V. Mitev, A. Pollini
This paper presents the evaluation of two perspective techniques in flash imaging lidar realization for space applications. One of these techniques is the indirect time-of-flight measurement, implemented in the combination of APS/IPPD array and continuous wave harmonically modulated laser. The other technique is the direct time-of-flight, realized in a combination of SPAD array and picosecond pulse laser. A prototype and a breadboard are realized and tested, respectively for the both flash imaging lidar techniques. The test results allow conclusions for the perspective area of applications in future space missions of each of these techniques.
{"title":"Flash imaging sensors for space applications","authors":"V. Mitev, A. Pollini","doi":"10.1109/RAST.2015.7208430","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208430","url":null,"abstract":"This paper presents the evaluation of two perspective techniques in flash imaging lidar realization for space applications. One of these techniques is the indirect time-of-flight measurement, implemented in the combination of APS/IPPD array and continuous wave harmonically modulated laser. The other technique is the direct time-of-flight, realized in a combination of SPAD array and picosecond pulse laser. A prototype and a breadboard are realized and tested, respectively for the both flash imaging lidar techniques. The test results allow conclusions for the perspective area of applications in future space missions of each of these techniques.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"98 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":"133821256","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.2015.7208306
M. Yaylı, S. Y. Kandemir, Y. C. Toklu
Lunar exploration is very important in the world. Investigation of lunar surface materials such as Agglutinitic Glass (A), Morris Is/FeO (M), LSCC Is/FeO (L), Total Pyx (T) and Plagioclase (P) is increase last years. The prediction of lunar surface materials including A, M, L, T and P is significant. In this study, the A (one of the important materials in the moon) were predicted by applying the linear regression analysis model. The R2 and R2adj are calculated that 81.20% and 75.83%, respectively. Finally, it was concluded that A can reliably be predicted by using the linear regression analysis model.
{"title":"Assessment of lunar surface materials","authors":"M. Yaylı, S. Y. Kandemir, Y. C. Toklu","doi":"10.1109/RAST.2015.7208306","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208306","url":null,"abstract":"Lunar exploration is very important in the world. Investigation of lunar surface materials such as Agglutinitic Glass (A), Morris Is/FeO (M), LSCC Is/FeO (L), Total Pyx (T) and Plagioclase (P) is increase last years. The prediction of lunar surface materials including A, M, L, T and P is significant. In this study, the A (one of the important materials in the moon) were predicted by applying the linear regression analysis model. The R2 and R2adj are calculated that 81.20% and 75.83%, respectively. Finally, it was concluded that A can reliably be predicted by using the linear regression analysis model.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"18 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":"128431359","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.2015.7208460
Fariba Razipour
Iran's first endeavor in space dates back to 1958 when established the United Nations ad-hoc Committee on the Peaceful Uses of Outer Space with other 17 countries(later changed its name to the Committee on the Peaceful Uses of Outer Space : COPUOS). Because of an 8 year imposed war following the Islamic revolution (1979), the country's space activities were halted until 2004 when Iranian Space Agency was established. In this article the structure of ISA and its changes to meet the needs of coordinating with international space law will be reviewed. We will go through rules and regulations according to private space activities and their shortcomings and at the end there are some recommendations to improve private sector's role in this regard.
{"title":"Role of private sector in Iran's space activities","authors":"Fariba Razipour","doi":"10.1109/RAST.2015.7208460","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208460","url":null,"abstract":"Iran's first endeavor in space dates back to 1958 when established the United Nations ad-hoc Committee on the Peaceful Uses of Outer Space with other 17 countries(later changed its name to the Committee on the Peaceful Uses of Outer Space : COPUOS). Because of an 8 year imposed war following the Islamic revolution (1979), the country's space activities were halted until 2004 when Iranian Space Agency was established. In this article the structure of ISA and its changes to meet the needs of coordinating with international space law will be reviewed. We will go through rules and regulations according to private space activities and their shortcomings and at the end there are some recommendations to improve private sector's role in this regard.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"3 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":"128536769","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.2015.7208442
Y. Somov, S. Butyrin, S. Somov, V. Salmin
Contemporary land-survey mini-satellites have general mass up to 500 kg and are placed onto the orbit altitudes up to 800 km. For such spacecraft some principle problems on optimal attitude guidance and robust control are considered and elaborated methods are presented for their solving.
{"title":"Attitude guidance and control of land-survey mini-satellite","authors":"Y. Somov, S. Butyrin, S. Somov, V. Salmin","doi":"10.1109/RAST.2015.7208442","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208442","url":null,"abstract":"Contemporary land-survey mini-satellites have general mass up to 500 kg and are placed onto the orbit altitudes up to 800 km. For such spacecraft some principle problems on optimal attitude guidance and robust control are considered and elaborated methods are presented for their solving.","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":"128766668","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.2015.7208369
M. Mirshams, E. Zabihian, A. Zabihian
In this paper, we introduce SDM design method. This method analyses statistical data with a particular procedure. Using this method, we can acceptably design satellite subsystems. To implement SDM method, a complete database is required. Therefore, we first collect spacecraft data and create a database, and then we extract statistical graphs using SPSS, from which we further extract mathematical models. Inputs parameters of the method are mass, mission, and life time of the satellite. As we use statistical data, detailed analysis and extracted mathematical models, accuracy of the method is relatively high. We test the accuracy and verify the method using a case study. Mean error of the method is shown to be around 10% with respect to a fabricated satellite. This is an acceptable error rate for conceptual design phase.
{"title":"Statistical design model (SDM) of communication satellites","authors":"M. Mirshams, E. Zabihian, A. Zabihian","doi":"10.1109/RAST.2015.7208369","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208369","url":null,"abstract":"In this paper, we introduce SDM design method. This method analyses statistical data with a particular procedure. Using this method, we can acceptably design satellite subsystems. To implement SDM method, a complete database is required. Therefore, we first collect spacecraft data and create a database, and then we extract statistical graphs using SPSS, from which we further extract mathematical models. Inputs parameters of the method are mass, mission, and life time of the satellite. As we use statistical data, detailed analysis and extracted mathematical models, accuracy of the method is relatively high. We test the accuracy and verify the method using a case study. Mean error of the method is shown to be around 10% with respect to a fabricated satellite. This is an acceptable error rate for conceptual design phase.","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":"127562452","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.2015.7208378
Goksel Gurgenburan, E. Cinar
The first high resolution research and development (R&D) earth observation satellite of Turkey, named as GÖKTÜRK-2 (GKT-2), was successfully launched on 18 December 2012 from Jiuquan Satellite Launch Center, China on a LM-2D launcher to its Low Earth Orbit (LEO). Reaching its operational LEO, the satellite underwent in orbit tests lasting for about 6 months. Both space and ground segments passed acceptance and commissioning tests successfully before the satellite was fully ceded to Turkish Air Force (TurAF) satellite operations team. After commissioning, regular operations such as telemetry, tracking, and command (TT&C), mission planning, data acquisition and image processing have started. This paper will include GKT-2 mission overview, technical specifications and nominal operations loop concept which describes on orbit servicing (OOS), mission planning, image acquisition modes, storage planning and restriction, TT&C, trend analyses and conjunction assessment.
{"title":"GÖKTÜRK-2: Two years of operation","authors":"Goksel Gurgenburan, E. Cinar","doi":"10.1109/RAST.2015.7208378","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208378","url":null,"abstract":"The first high resolution research and development (R&D) earth observation satellite of Turkey, named as GÖKTÜRK-2 (GKT-2), was successfully launched on 18 December 2012 from Jiuquan Satellite Launch Center, China on a LM-2D launcher to its Low Earth Orbit (LEO). Reaching its operational LEO, the satellite underwent in orbit tests lasting for about 6 months. Both space and ground segments passed acceptance and commissioning tests successfully before the satellite was fully ceded to Turkish Air Force (TurAF) satellite operations team. After commissioning, regular operations such as telemetry, tracking, and command (TT&C), mission planning, data acquisition and image processing have started. This paper will include GKT-2 mission overview, technical specifications and nominal operations loop concept which describes on orbit servicing (OOS), mission planning, image acquisition modes, storage planning and restriction, TT&C, trend analyses and conjunction assessment.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"408 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":"113998402","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.2015.7208343
Aziz Ahmed, Muhammad Muaz, Manzoor Ali, Muhammad Yasir, N. Minallah, S. Ullah, Shahbaz Khan
Pakistan faces heavy revenue losses in terms of one of its major cash crop i.e. Tobacco, due to the unavailability of accurate statistics of the total tobacco production. During the cropping season, there are many competing crops along with tobacco in the neighboring fields - making tobacco identification a challenging task. This study considers a pilot region of interest that spans over 64844 hectares, in the north-western Pakistan, covered through SPOT5 (2.5m) satellite imagery, acquired on June, 28, 2013. Two supervised pixel based classifiers: (1) minimum distance (MD) and (2) Spectral Angle Mapper (SAM) are compared and their overall accuracy discussed. The results show that there is no significant difference in the overall classification accuracy of MD and SAM. However, SAM performs better than MD with overall accuracy and Kappa coefficient of 76.56% and 0.7009 respectively. For the specific case of Tobacco crop, MD classifier has producer's accuracy of 81.7% while SAM has that of 70.44%. The study also finds that Euclidean distance (in case of MD) and angle difference (in case of SAM) has no significant difference in classifying land cover types. It is also learnt that if area estimation is the objective, both of the classifiers will under-estimate tobacco covered area.
{"title":"Comparing pixel-based classifiers for detecting tobacco crops in north-west Pakistan","authors":"Aziz Ahmed, Muhammad Muaz, Manzoor Ali, Muhammad Yasir, N. Minallah, S. Ullah, Shahbaz Khan","doi":"10.1109/RAST.2015.7208343","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208343","url":null,"abstract":"Pakistan faces heavy revenue losses in terms of one of its major cash crop i.e. Tobacco, due to the unavailability of accurate statistics of the total tobacco production. During the cropping season, there are many competing crops along with tobacco in the neighboring fields - making tobacco identification a challenging task. This study considers a pilot region of interest that spans over 64844 hectares, in the north-western Pakistan, covered through SPOT5 (2.5m) satellite imagery, acquired on June, 28, 2013. Two supervised pixel based classifiers: (1) minimum distance (MD) and (2) Spectral Angle Mapper (SAM) are compared and their overall accuracy discussed. The results show that there is no significant difference in the overall classification accuracy of MD and SAM. However, SAM performs better than MD with overall accuracy and Kappa coefficient of 76.56% and 0.7009 respectively. For the specific case of Tobacco crop, MD classifier has producer's accuracy of 81.7% while SAM has that of 70.44%. The study also finds that Euclidean distance (in case of MD) and angle difference (in case of SAM) has no significant difference in classifying land cover types. It is also learnt that if area estimation is the objective, both of the classifiers will under-estimate tobacco covered area.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"84 4 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":"126016810","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.2015.7208439
Murat Parlak, R. McGlen
An engineering model of a phased array antenna, cooled using axially grooved heat pipes (AGHP) is presented. Solid state power amplifier's (SSPA) located inside the satellite are wave transmitted to the reflector through waveguides. This integration technique is preferred to minimise electrical losses. However, usually when designing waveguides, minimising antenna losses takes precedence, which leads to an un-optimised design for thermal performance. Because of this situation, a thermal solution has become a challenging problem on this project. With a total heat load of 578 W, it is essential that the waste heat is transferred to the radiator of the satellite which is designed to operate in GEO orbit. This work presents a thermal solution being developed for a satellite phased array antenna that incorporates 4 AGHP's to carry the heat from the SSPA to the radiator. Thermal design work for the antenna and heat pipes completed for the specific boundary conditions for the application, using Icepack® computational fluid dynamics (CFD) thermal software is presented. It is crucial in this pre-development phase to identify problems which can arise from electronic performance loss or thermal issues in advance, both by theoretical design and ground testing.
{"title":"Cooling of high power active phased array antenna using axially grooved heat pipe for a space application","authors":"Murat Parlak, R. McGlen","doi":"10.1109/RAST.2015.7208439","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208439","url":null,"abstract":"An engineering model of a phased array antenna, cooled using axially grooved heat pipes (AGHP) is presented. Solid state power amplifier's (SSPA) located inside the satellite are wave transmitted to the reflector through waveguides. This integration technique is preferred to minimise electrical losses. However, usually when designing waveguides, minimising antenna losses takes precedence, which leads to an un-optimised design for thermal performance. Because of this situation, a thermal solution has become a challenging problem on this project. With a total heat load of 578 W, it is essential that the waste heat is transferred to the radiator of the satellite which is designed to operate in GEO orbit. This work presents a thermal solution being developed for a satellite phased array antenna that incorporates 4 AGHP's to carry the heat from the SSPA to the radiator. Thermal design work for the antenna and heat pipes completed for the specific boundary conditions for the application, using Icepack® computational fluid dynamics (CFD) thermal software is presented. It is crucial in this pre-development phase to identify problems which can arise from electronic performance loss or thermal issues in advance, both by theoretical design and ground testing.","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":"123870700","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.2015.7208356
Ibrahim S. Acikgoz, Mustafa Teke, Uğurhan Kutbay, F. Hardalaç
Turkey is among the countries which could develop earth observation satellites. RASAT and Göktürk-2 satellites are still operational and continuously acquire images of the Earth. Their images are processed before sharing with end users. Pansharpening, at which high resolution pan and low resolution multi-spectral images are fused, is an important step in image processing chain. As the resolution and number of images increase, pansharpening of satellite images take considerable amount of time. Multithread programming and General Purpose GPU (GPGPU) programming implementation improve performance of image processing applications, where most operations carried out on individual pixels. In this paper, we compared pansharpening applications and their CPU and GPU implementations for RASAT images. GPU implementations of pansharpening algorithms provides 20-25 times speed-up compared to CPU implementations.
{"title":"Performance evaluation of pansharpening methods on GPU for RASAT images","authors":"Ibrahim S. Acikgoz, Mustafa Teke, Uğurhan Kutbay, F. Hardalaç","doi":"10.1109/RAST.2015.7208356","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208356","url":null,"abstract":"Turkey is among the countries which could develop earth observation satellites. RASAT and Göktürk-2 satellites are still operational and continuously acquire images of the Earth. Their images are processed before sharing with end users. Pansharpening, at which high resolution pan and low resolution multi-spectral images are fused, is an important step in image processing chain. As the resolution and number of images increase, pansharpening of satellite images take considerable amount of time. Multithread programming and General Purpose GPU (GPGPU) programming implementation improve performance of image processing applications, where most operations carried out on individual pixels. In this paper, we compared pansharpening applications and their CPU and GPU implementations for RASAT images. GPU implementations of pansharpening algorithms provides 20-25 times speed-up compared to CPU implementations.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"10 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":"128632354","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.2015.7208317
Arthur Huang, E. Huang
Taiwan and the U.S. are collaborating to jointly develop, launch and operate the FORMOSAT-7/ Constellation Observing System for Meteorology, Ionosphere and Climate-2 (COSMIC)-2 mission through their agencies the National Space Organization (NSPO) for Taiwan and the National Oceanic and Atmospheric Administration (NOAA) for United States, respectively. This paper presents the quality control system for the international joint mission risk management and QC collaboration activities.
{"title":"The joint mission quality control system for FORMOSAT-7/COSMIC-2 satellite development","authors":"Arthur Huang, E. Huang","doi":"10.1109/RAST.2015.7208317","DOIUrl":"https://doi.org/10.1109/RAST.2015.7208317","url":null,"abstract":"Taiwan and the U.S. are collaborating to jointly develop, launch and operate the FORMOSAT-7/ Constellation Observing System for Meteorology, Ionosphere and Climate-2 (COSMIC)-2 mission through their agencies the National Space Organization (NSPO) for Taiwan and the National Oceanic and Atmospheric Administration (NOAA) for United States, respectively. This paper presents the quality control system for the international joint mission risk management and QC collaboration activities.","PeriodicalId":282476,"journal":{"name":"2015 7th International Conference on Recent Advances in Space Technologies (RAST)","volume":"49 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":"117156501","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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