Pub Date : 2019-10-01DOI: 10.1109/ICARES.2019.8914549
Z. Sahwee, S. A. Hamid, N. Kamal, N. Norhashim
One of the recent area where renewable energy is used is in Unmanned Aerial Vehicle. It does offer many benefits but at the same time, create technical challenges both in the design and the manufacturing process. The photovoltaic (PV) cell in its raw form is very fragile and easily being damaged. Once cracked, the electrical output reduces, while a severe crack will cause the solar cell to be unusable. In this research, an encapsulation process to increase the durability and reliability were explored by performing a series of tests. Thus the objective of this study is to explore solar encapsulation process while aiming to maintain its conversion efficiency. Conversion efficiency and weight penalty of each technique were recorded and were measured under sun irradiance. The results show that epoxy resin encapsulation together with advance composite fabrication technique provide the best results in terms of reliability and conversion efficiency. This method helps to protect the PV cell against moisture and damage, thus prolong the life-span of the solar cells.
{"title":"Experimental Evaluation of Encapsulated Solar cells for Unmanned Aerial Vehicle Application","authors":"Z. Sahwee, S. A. Hamid, N. Kamal, N. Norhashim","doi":"10.1109/ICARES.2019.8914549","DOIUrl":"https://doi.org/10.1109/ICARES.2019.8914549","url":null,"abstract":"One of the recent area where renewable energy is used is in Unmanned Aerial Vehicle. It does offer many benefits but at the same time, create technical challenges both in the design and the manufacturing process. The photovoltaic (PV) cell in its raw form is very fragile and easily being damaged. Once cracked, the electrical output reduces, while a severe crack will cause the solar cell to be unusable. In this research, an encapsulation process to increase the durability and reliability were explored by performing a series of tests. Thus the objective of this study is to explore solar encapsulation process while aiming to maintain its conversion efficiency. Conversion efficiency and weight penalty of each technique were recorded and were measured under sun irradiance. The results show that epoxy resin encapsulation together with advance composite fabrication technique provide the best results in terms of reliability and conversion efficiency. This method helps to protect the PV cell against moisture and damage, thus prolong the life-span of the solar cells.","PeriodicalId":376964,"journal":{"name":"2019 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology (ICARES)","volume":"61 3","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"120817480","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 : 2019-10-01DOI: 10.1109/ICARES.2019.8914338
S. Utama, P. R. Hakim, M. A. Saifudin
It is widely known that star sensor is the most accurate attitude sensor. Nevertheless, despite the good accuracy, star sensor becomes vulnerable when facing bright objects such as sun, earth, and moon. Event when not face directly, due to stray light from sun, earth or moon, star sensor reading can be obstructed. Based on LAPAN-A3 flight experience, this research studied availability of its star sensor due to stray light from sun and earth. From star sensor availability profile, the angle between sun or earth to star sensor when its availability decreased, later stated as obstruction angle, can be measured. The measured obstruction angle will be used for recommendations to improve star sensor availability for the next generation satellite. To achieve the objective, telemetry data from January 1st, 2017 until May 25th, 2019 are observed. The result shows that the obstruction of the star sensor occurred when sun angle 68° or earth angle 95°. Star sensor of LAPAN-A3 is located 60° from the Y+ axis to the Z-axis, this configuration will lead to 38% of time star sensor availability less than 0.95. The next LAPAN's satellite, LAPAN-A4, is designed has the same orbit as LAPAN-A3, hence based on this research it is recommended that the star sensor is located between 5° to 50° from the Y+ axis to the Z- axis to avoids obstruction from sun and earth. To accommodate off-nadir maneuver, the best configuration for star sensor is 27.5° from Y+ axis to Z- axis that will give roll ability up to 22.5° before obstruction occurs.
{"title":"Obstruction Angle Measurement to Improve Star Sensor Availability Based on LAPAN-A3 Experience","authors":"S. Utama, P. R. Hakim, M. A. Saifudin","doi":"10.1109/ICARES.2019.8914338","DOIUrl":"https://doi.org/10.1109/ICARES.2019.8914338","url":null,"abstract":"It is widely known that star sensor is the most accurate attitude sensor. Nevertheless, despite the good accuracy, star sensor becomes vulnerable when facing bright objects such as sun, earth, and moon. Event when not face directly, due to stray light from sun, earth or moon, star sensor reading can be obstructed. Based on LAPAN-A3 flight experience, this research studied availability of its star sensor due to stray light from sun and earth. From star sensor availability profile, the angle between sun or earth to star sensor when its availability decreased, later stated as obstruction angle, can be measured. The measured obstruction angle will be used for recommendations to improve star sensor availability for the next generation satellite. To achieve the objective, telemetry data from January 1st, 2017 until May 25th, 2019 are observed. The result shows that the obstruction of the star sensor occurred when sun angle 68° or earth angle 95°. Star sensor of LAPAN-A3 is located 60° from the Y+ axis to the Z-axis, this configuration will lead to 38% of time star sensor availability less than 0.95. The next LAPAN's satellite, LAPAN-A4, is designed has the same orbit as LAPAN-A3, hence based on this research it is recommended that the star sensor is located between 5° to 50° from the Y+ axis to the Z- axis to avoids obstruction from sun and earth. To accommodate off-nadir maneuver, the best configuration for star sensor is 27.5° from Y+ axis to Z- axis that will give roll ability up to 22.5° before obstruction occurs.","PeriodicalId":376964,"journal":{"name":"2019 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology (ICARES)","volume":"19 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126811080","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 : 2019-10-01DOI: 10.1109/ICARES.2019.8914342
Agustan, D. Karmiadji, M. N. Putri, O. B. Bintoro, I. N. Djarot, Hasan Soleh, Aris Irawan, Hary Soebagyo
Trend Assessment and Scenario Development Analysis approach was carried out in this study. This approach is a framework specifically designed to look at the direction of technological development and possible conditions that occur in the future. First stage of the framework consists of the Delphi study, which is a method for obtaining issues related to maritime and possible conditions in the future. Second stage of the framework, scenario planning, which is a method to illustrate the possibility of future conditions by taking into account the main driving factors; then technology road-mapping illustrate the steps that must be taken to achieve the ideal conditions planned. The Delphi study is applied to develop a consensus-based, prioritized research agenda for Indonesia Foresight Maritime Research Topics in year 2018–2045. Expert investigation of the web-based Delphi method was employed to develop online survey. In this study, a three round modified Delphi survey was conducted. A total of 45 study participants were participated in the third round of study. Some interview study was designed to validate some of the findings. The top 10 priority themes were determined by the web-based Delphi method result and in-depth interview of experts. The results of this study indicate that among the Indonesian maritime researcher and maritime technology expert in this study, they have a high degree consensus on some research topics. In the second stage of the framework, we used “scenario planning” approach. Scenario planning is intended to understand the perception of management in recognizing future alternatives so that appropriate decisions can be taken. Experts and stakeholders have better understanding of the issues pertaining the development of Maritime Frontier Research Topics in Indonesia, including those related to tourism, ocean and fisheries, infrastructures, energy and mineral etc. This study then analyzes the dynamics of strategic environment changes (socio-political-economic context) that determine the construction of Maritime Frontier Research Topics. By using a scenario planning analysis framework, the driving factors and uncertainty factors are formulated which are then developed into a strategic environmental scenario. There are 40 experts participated in two scenario planning workshops. The results of scenario planning exercises map 4 (four) scenarios in 2030 and 4 (four) scenario in 2045. The framework for this foresight technology activities has produced the documents for the development of the Foresight Maritime Research topics that use the combination of Delphi study and scenario planning approach.
{"title":"Combining Delphi Study and Scenario Planning for Indonesia Research Priorities in Maritime Sector","authors":"Agustan, D. Karmiadji, M. N. Putri, O. B. Bintoro, I. N. Djarot, Hasan Soleh, Aris Irawan, Hary Soebagyo","doi":"10.1109/ICARES.2019.8914342","DOIUrl":"https://doi.org/10.1109/ICARES.2019.8914342","url":null,"abstract":"Trend Assessment and Scenario Development Analysis approach was carried out in this study. This approach is a framework specifically designed to look at the direction of technological development and possible conditions that occur in the future. First stage of the framework consists of the Delphi study, which is a method for obtaining issues related to maritime and possible conditions in the future. Second stage of the framework, scenario planning, which is a method to illustrate the possibility of future conditions by taking into account the main driving factors; then technology road-mapping illustrate the steps that must be taken to achieve the ideal conditions planned. The Delphi study is applied to develop a consensus-based, prioritized research agenda for Indonesia Foresight Maritime Research Topics in year 2018–2045. Expert investigation of the web-based Delphi method was employed to develop online survey. In this study, a three round modified Delphi survey was conducted. A total of 45 study participants were participated in the third round of study. Some interview study was designed to validate some of the findings. The top 10 priority themes were determined by the web-based Delphi method result and in-depth interview of experts. The results of this study indicate that among the Indonesian maritime researcher and maritime technology expert in this study, they have a high degree consensus on some research topics. In the second stage of the framework, we used “scenario planning” approach. Scenario planning is intended to understand the perception of management in recognizing future alternatives so that appropriate decisions can be taken. Experts and stakeholders have better understanding of the issues pertaining the development of Maritime Frontier Research Topics in Indonesia, including those related to tourism, ocean and fisheries, infrastructures, energy and mineral etc. This study then analyzes the dynamics of strategic environment changes (socio-political-economic context) that determine the construction of Maritime Frontier Research Topics. By using a scenario planning analysis framework, the driving factors and uncertainty factors are formulated which are then developed into a strategic environmental scenario. There are 40 experts participated in two scenario planning workshops. The results of scenario planning exercises map 4 (four) scenarios in 2030 and 4 (four) scenario in 2045. The framework for this foresight technology activities has produced the documents for the development of the Foresight Maritime Research topics that use the combination of Delphi study and scenario planning approach.","PeriodicalId":376964,"journal":{"name":"2019 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology (ICARES)","volume":"92 2 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123168788","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 : 2019-10-01DOI: 10.1109/ICARES.2019.8914551
Daniel Sande Bona, A. Murni, P. Mursanto
Classical methods for image segmentation such as pixel thresholding, clustering, region growing, maximum likelihood have been used regularly and relied on for a long time. However, these classical methods have limitations, particularly on images where there are many overlapping pixel values between features, which is common in remote sensing images. The advent of machine learning, in particular, deep learning in computer vision and image analysis, has gained interest in the remote sensing field. Current deep learning architecture has been able to achieve high accuracy for image recognition, object detection, and segmentation. This study performed image segmentation on the coastal area with high water turbidity using Landsat-8 images. Currently, the standard tool to derive water turbidity data from Landsat-8 images is the level-2 plugin of SEADAS software. However, due to its rigorous processing method, the processing time using SEADAS Level-2 Plugin is quite long; for example, processing one Landsat-8 image took around 8 hours. As a consequence, the amount of time needed to process multiple images is increasing. Deep learning has advantages once the model trained, the inference or prediction process is quite fast. Therefore it has the potential to be used as a complementary tool to predict and segment high turbidity areas, because in deep learning. In this study, we implemented U-Net architecture with ResNet connection and used Generative-Adversarial Network (GAN) to refined segmentation results.
{"title":"Semantic Segmentation And Segmentation Refinement Using Machine Learning Case Study: Water Turbidity Segmentation","authors":"Daniel Sande Bona, A. Murni, P. Mursanto","doi":"10.1109/ICARES.2019.8914551","DOIUrl":"https://doi.org/10.1109/ICARES.2019.8914551","url":null,"abstract":"Classical methods for image segmentation such as pixel thresholding, clustering, region growing, maximum likelihood have been used regularly and relied on for a long time. However, these classical methods have limitations, particularly on images where there are many overlapping pixel values between features, which is common in remote sensing images. The advent of machine learning, in particular, deep learning in computer vision and image analysis, has gained interest in the remote sensing field. Current deep learning architecture has been able to achieve high accuracy for image recognition, object detection, and segmentation. This study performed image segmentation on the coastal area with high water turbidity using Landsat-8 images. Currently, the standard tool to derive water turbidity data from Landsat-8 images is the level-2 plugin of SEADAS software. However, due to its rigorous processing method, the processing time using SEADAS Level-2 Plugin is quite long; for example, processing one Landsat-8 image took around 8 hours. As a consequence, the amount of time needed to process multiple images is increasing. Deep learning has advantages once the model trained, the inference or prediction process is quite fast. Therefore it has the potential to be used as a complementary tool to predict and segment high turbidity areas, because in deep learning. In this study, we implemented U-Net architecture with ResNet connection and used Generative-Adversarial Network (GAN) to refined segmentation results.","PeriodicalId":376964,"journal":{"name":"2019 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology (ICARES)","volume":"23 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129828000","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 : 2019-10-01DOI: 10.1109/ICARES.2019.8914348
Idris E. Putro, S. Sofyan, R. Andiarti
Unexpected external disturbance, parameter uncertainties, and UAV model inaccuracy are several issues causing significant reduction in UAV stability. Robust nominal control based sliding mode control (SMC) has been developed to maintain the flight performance. However, chattering problem comes along with the implementation of discontinuous switching control law in SMC. This paper presents the application of incremental control for LAPAN Turbojet UAV to turn the UAV becomes less sensitive from model dependency, and overcome parameter uncertainties. Incremental approach on SMC (ISMC) and chattering reduction methods are implemented to keep robustness of the control and solve the chattering phenomena occurs on control surface. The proposed control systems are implemented for the decoupled linear UAV models and observed through simulations using MATLAB/Simulink program. The simulation results are analyzed and the advantages of the proposed approach are validated through comparing the results.
{"title":"Incremental Control for LAPAN Turbojet UAV Considering Disturbance and Uncertainties","authors":"Idris E. Putro, S. Sofyan, R. Andiarti","doi":"10.1109/ICARES.2019.8914348","DOIUrl":"https://doi.org/10.1109/ICARES.2019.8914348","url":null,"abstract":"Unexpected external disturbance, parameter uncertainties, and UAV model inaccuracy are several issues causing significant reduction in UAV stability. Robust nominal control based sliding mode control (SMC) has been developed to maintain the flight performance. However, chattering problem comes along with the implementation of discontinuous switching control law in SMC. This paper presents the application of incremental control for LAPAN Turbojet UAV to turn the UAV becomes less sensitive from model dependency, and overcome parameter uncertainties. Incremental approach on SMC (ISMC) and chattering reduction methods are implemented to keep robustness of the control and solve the chattering phenomena occurs on control surface. The proposed control systems are implemented for the decoupled linear UAV models and observed through simulations using MATLAB/Simulink program. The simulation results are analyzed and the advantages of the proposed approach are validated through comparing the results.","PeriodicalId":376964,"journal":{"name":"2019 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology (ICARES)","volume":"39 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134079455","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 : 2019-10-01DOI: 10.1109/ICARES.2019.8914548
J. Koh
Radar Cross Section (RCS) is one of the necessary factors for the design of communication system antenna and aircraft, where the scattering and reflection of electromagnetic waves plays a vital role. To measure RCS in electrically large objects such as aircraft and ships large amounts of resources are required. In this paper, we used the free function and TLS (Total Least Squares) theory to low-frequency RCS data and predicted high-frequency RCS data. In this approach, the result shows that the numerical verification of estimates lies within the tolerance limit.
{"title":"High-Frequency RCS Estimation","authors":"J. Koh","doi":"10.1109/ICARES.2019.8914548","DOIUrl":"https://doi.org/10.1109/ICARES.2019.8914548","url":null,"abstract":"Radar Cross Section (RCS) is one of the necessary factors for the design of communication system antenna and aircraft, where the scattering and reflection of electromagnetic waves plays a vital role. To measure RCS in electrically large objects such as aircraft and ships large amounts of resources are required. In this paper, we used the free function and TLS (Total Least Squares) theory to low-frequency RCS data and predicted high-frequency RCS data. In this approach, the result shows that the numerical verification of estimates lies within the tolerance limit.","PeriodicalId":376964,"journal":{"name":"2019 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology (ICARES)","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130838247","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 : 2019-10-01DOI: 10.1109/ICARES.2019.8914355
Adelia Revani Sastaviyana, R. Hartono
Automatic Identification System (AIS) system, that is equipped with transceiver device, works by continuously broadcasting status and position information of host vessel that enables other similar equipped vessels in the surrounding area to receive, decode, then display the information to provide maritime traffic information. One of AIS data processor IC that can be used in AIS transceiver device is CMX7032. For communicating with other IC, CMX7032 provides C-BUS interface feature that is compatible with SPI interface. ATxmega128A1, that has SPI feature and its operating voltage requirement is compatible with CMX7032, can be used to load and activate Function Image™ (FI) via C-BUS - SPI communication into CMX7032 so it can work properly. Method used to observe C-BUS - SPI communication performance is literature review and observation using various CMX7032 and ATxmega128A1 main clock frequency and C-BUS - SPI clock frequency. Observation results show that right checksum values and increased CMX7032 power consumption are successful FI loading indicators, while increased ATxmega128A1 power consumption exceeding in successful FI loading and activating case is unsuccessful FI activating indicator. Higher CMX7032 main clock frequency demands higher C-BUS - SPI clock frequency to support successful FI loading and activating process. Observation results also show that using same ATxmega128A1 main clock frequency, higher C-BUS - SPI clock frequency results less required time for loading and activating FI. Then, when using same C-BUS - SPI clock frequency, different CMX7032 main clock frequency does not affect significantly to the time required for loading and activating FI.
{"title":"Performance of C-BUS Communication in CMX7032 IC with SPI Communication in ATxmega128A1 IC","authors":"Adelia Revani Sastaviyana, R. Hartono","doi":"10.1109/ICARES.2019.8914355","DOIUrl":"https://doi.org/10.1109/ICARES.2019.8914355","url":null,"abstract":"Automatic Identification System (AIS) system, that is equipped with transceiver device, works by continuously broadcasting status and position information of host vessel that enables other similar equipped vessels in the surrounding area to receive, decode, then display the information to provide maritime traffic information. One of AIS data processor IC that can be used in AIS transceiver device is CMX7032. For communicating with other IC, CMX7032 provides C-BUS interface feature that is compatible with SPI interface. ATxmega128A1, that has SPI feature and its operating voltage requirement is compatible with CMX7032, can be used to load and activate Function Image™ (FI) via C-BUS - SPI communication into CMX7032 so it can work properly. Method used to observe C-BUS - SPI communication performance is literature review and observation using various CMX7032 and ATxmega128A1 main clock frequency and C-BUS - SPI clock frequency. Observation results show that right checksum values and increased CMX7032 power consumption are successful FI loading indicators, while increased ATxmega128A1 power consumption exceeding in successful FI loading and activating case is unsuccessful FI activating indicator. Higher CMX7032 main clock frequency demands higher C-BUS - SPI clock frequency to support successful FI loading and activating process. Observation results also show that using same ATxmega128A1 main clock frequency, higher C-BUS - SPI clock frequency results less required time for loading and activating FI. Then, when using same C-BUS - SPI clock frequency, different CMX7032 main clock frequency does not affect significantly to the time required for loading and activating FI.","PeriodicalId":376964,"journal":{"name":"2019 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology (ICARES)","volume":"12 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133517244","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 : 2019-10-01DOI: 10.1109/ICARES.2019.8914339
A. Z. Ribah, S. Utama, P. R. Hakim
During the day of LAPAN A3 operation, the temperature of the multispectral Imager or LISA (Line Imager Space Applications), does not stay continually at the positive value, especially during May - June 2017 and 2018. Based on the beta angle variation, May and June have a minimum beta angle condition that affects LISA temperature. However, there are two procedures we perform for maintaining LISA temperature, both are the stop-release and the stop-release with additional roll angle. The idea in the stop-release maneuver is stopping the satellite for orbiting in nadir pointing mode, by giving 0°/s of nadir rate or 0° of pitch angle, at specific latitude. After a certain duration, the satellite should be release into nadir pointing back at the same specific latitude. This method has a purpose to point some satellite side to the sun for the increasing temperature of the multispectral Imager. Meanwhile, the second method is giving roll angle before the satellite executes the stop maneuver. Before the release maneuver, the attitude must be fixed back by giving a negative value of roll angle. Based on the result, the stop-release maneuver could increase the LISA temperature when it executes at 200 of latitude in ascending orbit condition. Therefore, the additional roll angle in the stop-release maneuver could increase the LISA temperature better than only use a normal stop-release.
在LAPAN A3运行的白天，多光谱成像仪或LISA (Line Imager Space Applications)的温度并没有持续保持正值，特别是在2017年5 - 6月和2018年。基于β角变化，5月和6月有最小β角条件影响LISA温度。然而，我们执行两个程序来维持LISA温度，都是停止释放和停止释放额外的滚转角。停止释放机动的思想是停止卫星在最低点指向模式下运行，通过给出0°/s的最低点速率或0°的俯仰角，在特定的纬度。经过一段时间后，卫星应该被释放到指向同一特定纬度的最低点。这种方法的目的是在多光谱成像仪温度升高时，使卫星的某一面指向太阳。同时，第二种方法是在卫星执行停止机动前给出滚转角。在释放机动之前，必须通过给一个负值的滚转角将姿态固定回来。结果表明，在上升轨道条件下，在纬度200度处执行停止释放机动可以提高LISA的温度。因此，在停止释放机动中增加翻滚角比仅使用正常停止释放能更好地提高LISA温度。
{"title":"Maneuver Strategy for Increasing Multispectral Imager Temperature on LAPAN A3/IPB Microsatellite","authors":"A. Z. Ribah, S. Utama, P. R. Hakim","doi":"10.1109/ICARES.2019.8914339","DOIUrl":"https://doi.org/10.1109/ICARES.2019.8914339","url":null,"abstract":"During the day of LAPAN A3 operation, the temperature of the multispectral Imager or LISA (Line Imager Space Applications), does not stay continually at the positive value, especially during May - June 2017 and 2018. Based on the beta angle variation, May and June have a minimum beta angle condition that affects LISA temperature. However, there are two procedures we perform for maintaining LISA temperature, both are the stop-release and the stop-release with additional roll angle. The idea in the stop-release maneuver is stopping the satellite for orbiting in nadir pointing mode, by giving 0°/s of nadir rate or 0° of pitch angle, at specific latitude. After a certain duration, the satellite should be release into nadir pointing back at the same specific latitude. This method has a purpose to point some satellite side to the sun for the increasing temperature of the multispectral Imager. Meanwhile, the second method is giving roll angle before the satellite executes the stop maneuver. Before the release maneuver, the attitude must be fixed back by giving a negative value of roll angle. Based on the result, the stop-release maneuver could increase the LISA temperature when it executes at 200 of latitude in ascending orbit condition. Therefore, the additional roll angle in the stop-release maneuver could increase the LISA temperature better than only use a normal stop-release.","PeriodicalId":376964,"journal":{"name":"2019 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology (ICARES)","volume":"13 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130077056","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 : 2019-10-01DOI: 10.1109/ICARES.2019.8914351
R. Madina, A. P. S. Jayani, A. Sarah, M. Mukhayadi
The missions of LAPAN-A2 satellite are Earth observation using an RGB digital camera, maritime traffic monitoring, and amateur radio communications. The satellite carries a digital camera, to support the mission, with ground resolution 4 m and a swath width 7 km. It is necessary to do pointing calibration to measure misalignment between spacecraft's attitude sensors, spacecraft axis, and cameras, to make sure the accuracy of the camera pointing when capture the image. By using the inertial pointing method, that the satellite is controlled in three axis to direct the satellite camera to the Moon. Nevertheless, the field of view (FOV) of high-resolution digital cameras is very narrow, which is only 0.7° for the Moon to be fully visible in the camera frame. During image acquisition, the star sensor should be still able to see the star so the attitude information of spacecraft can be well determined. It means the time period and position for Moon acquisition is limited. By capturing multiple images, LAPAN-A2 satellite success to get the Moon images right in the center of the frame within the offset between camera and spacecraft axis are 0.1232° on the $x$ axis and −0.93° on the $y$ axis.
{"title":"Moon Image Acquisition for Pointing Calibration of LAPAN-A2 Satellite's High Resolution Camera","authors":"R. Madina, A. P. S. Jayani, A. Sarah, M. Mukhayadi","doi":"10.1109/ICARES.2019.8914351","DOIUrl":"https://doi.org/10.1109/ICARES.2019.8914351","url":null,"abstract":"The missions of LAPAN-A2 satellite are Earth observation using an RGB digital camera, maritime traffic monitoring, and amateur radio communications. The satellite carries a digital camera, to support the mission, with ground resolution 4 m and a swath width 7 km. It is necessary to do pointing calibration to measure misalignment between spacecraft's attitude sensors, spacecraft axis, and cameras, to make sure the accuracy of the camera pointing when capture the image. By using the inertial pointing method, that the satellite is controlled in three axis to direct the satellite camera to the Moon. Nevertheless, the field of view (FOV) of high-resolution digital cameras is very narrow, which is only 0.7° for the Moon to be fully visible in the camera frame. During image acquisition, the star sensor should be still able to see the star so the attitude information of spacecraft can be well determined. It means the time period and position for Moon acquisition is limited. By capturing multiple images, LAPAN-A2 satellite success to get the Moon images right in the center of the frame within the offset between camera and spacecraft axis are 0.1232° on the $x$ axis and −0.93° on the $y$ axis.","PeriodicalId":376964,"journal":{"name":"2019 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology (ICARES)","volume":"17 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130439615","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 : 2019-10-01DOI: 10.1109/ICARES.2019.8914340
Nurul Fadilah, I. Choiriyah, Nayla Najati
Receiving AIS (Automatic Identification System) signal using satellite makes it possible to track the seafaring vessels beyond coastal areas that cannot be covered by ground AIS receiver that have limitation in coverage. Based on IALA (International Association of Maritime Aids to Navigation and Lighthouse Authorities), AIS has a purpose to enhance the maritime safety and navigation efficiency, the marine environment protection. LAPAN-A2 and LAPAN-A3 have been constructed by LAPAN (National Institute of Aeronautics and Space). LAPAN-A2 and LAPAN-A3 carry AIS Receiver as one of the payloads to monitoring ship. Next-generation satellite of LAPAN will also carry AIS receiver as one of the payloads. This AIS receiver is an improvement from AIS Receiver that carried in LAPAN-A2 and LAPAN-A3. To improve the AIS reception in next-generation satellites, the satellite will carry two VHF antenna. This paper simulated the radiation pattern of the VHF antenna to know the direction of the radiated signal, the coverage of AIS signal reception by the satellite and the link budget to receive the AIS signal.
{"title":"Analysis of Two Monopole Antennas Placement on Satellite for AIS Signal Reception","authors":"Nurul Fadilah, I. Choiriyah, Nayla Najati","doi":"10.1109/ICARES.2019.8914340","DOIUrl":"https://doi.org/10.1109/ICARES.2019.8914340","url":null,"abstract":"Receiving AIS (Automatic Identification System) signal using satellite makes it possible to track the seafaring vessels beyond coastal areas that cannot be covered by ground AIS receiver that have limitation in coverage. Based on IALA (International Association of Maritime Aids to Navigation and Lighthouse Authorities), AIS has a purpose to enhance the maritime safety and navigation efficiency, the marine environment protection. LAPAN-A2 and LAPAN-A3 have been constructed by LAPAN (National Institute of Aeronautics and Space). LAPAN-A2 and LAPAN-A3 carry AIS Receiver as one of the payloads to monitoring ship. Next-generation satellite of LAPAN will also carry AIS receiver as one of the payloads. This AIS receiver is an improvement from AIS Receiver that carried in LAPAN-A2 and LAPAN-A3. To improve the AIS reception in next-generation satellites, the satellite will carry two VHF antenna. This paper simulated the radiation pattern of the VHF antenna to know the direction of the radiated signal, the coverage of AIS signal reception by the satellite and the link budget to receive the AIS signal.","PeriodicalId":376964,"journal":{"name":"2019 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology (ICARES)","volume":"53 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115839434","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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