Nandinbaatar Tsog, S. Mubeen, Mikael Sjödin, F. Bruhn
{"title":"A Trade-Off between Computing Power and Energy Consumption of On-Board Data Processing in GPU Accelerated In-Orbit Space Systems","authors":"Nandinbaatar Tsog, S. Mubeen, Mikael Sjödin, F. Bruhn","doi":"10.2322/tastj.19.700","DOIUrl":"https://doi.org/10.2322/tastj.19.700","url":null,"abstract":"","PeriodicalId":120185,"journal":{"name":"TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115807027","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}
K. Sasahara, Y. Uwamino, S. Hasegawa, Kanjuro Makihara
Space debris poses a serious threat and the problem must be solved. Space debris should be removed to maintain the space environment. One of the techniques to remove it is an electrodynamic tether system (EDTS). To improve the toughness of the tether used in EDTS, this study investigated the tether shape of a hollow cylinder instead of the conventional solid cylinder. When the mass and length of a hollow tether are the same as those of the solid tether, the hollow cylindrical tether has a larger diameter. Thus, the toughness against small debris collisions will be improved. To investigate the damage to the hollow tether following a debris collision, hypervelocity impact experiments were performed using a two-stage light-gas gun. Through the impact experiments, the relationship between the damage to the hollow tether and the impact condition of the debris was revealed. It was confirmed that when the impact angle increased the damage area increased as well. The experiments validated that a hollow tether is superior to a solid tether in terms of resistance to debris collisions. In addition, the importance of considering the influence of the impact angle was shown by an evaluation of the lifetime of the hollow tether.
{"title":"Fracture Investigation of Hollow Cylindrical Tether during Space Debris Impact","authors":"K. Sasahara, Y. Uwamino, S. Hasegawa, Kanjuro Makihara","doi":"10.2322/TASTJ.17.383","DOIUrl":"https://doi.org/10.2322/TASTJ.17.383","url":null,"abstract":"Space debris poses a serious threat and the problem must be solved. Space debris should be removed to maintain the space environment. One of the techniques to remove it is an electrodynamic tether system (EDTS). To improve the toughness of the tether used in EDTS, this study investigated the tether shape of a hollow cylinder instead of the conventional solid cylinder. When the mass and length of a hollow tether are the same as those of the solid tether, the hollow cylindrical tether has a larger diameter. Thus, the toughness against small debris collisions will be improved. To investigate the damage to the hollow tether following a debris collision, hypervelocity impact experiments were performed using a two-stage light-gas gun. Through the impact experiments, the relationship between the damage to the hollow tether and the impact condition of the debris was revealed. It was confirmed that when the impact angle increased the damage area increased as well. The experiments validated that a hollow tether is superior to a solid tether in terms of resistance to debris collisions. In addition, the importance of considering the influence of the impact angle was shown by an evaluation of the lifetime of the hollow tether.","PeriodicalId":120185,"journal":{"name":"TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127481426","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}
This paper describes the error and uncertainty analysis of the CAMUI hybrid rocket regression simulator. Simulation errors compared to test firings are described and followed by an analysis of the potential uncertainties causing this error. For each uncertainty identified, a sensitivity analysis is then performed with the help of a custom-built simulator to evaluate its impact on the simulator accuracy. It was found that uncertainties in LOX travel time, Reynolds number grouping and model assumptions for the first upstream burning surface have the largest impact on the simulator accuracy and are identified as the main focus points for further research.
{"title":"Error Analysis for CAMUI Type Hybrid Rocket Regression Simulation","authors":"V. Tor, H. Nagata","doi":"10.2322/TASTJ.17.519","DOIUrl":"https://doi.org/10.2322/TASTJ.17.519","url":null,"abstract":"This paper describes the error and uncertainty analysis of the CAMUI hybrid rocket regression simulator. Simulation errors compared to test firings are described and followed by an analysis of the potential uncertainties causing this error. For each uncertainty identified, a sensitivity analysis is then performed with the help of a custom-built simulator to evaluate its impact on the simulator accuracy. It was found that uncertainties in LOX travel time, Reynolds number grouping and model assumptions for the first upstream burning surface have the largest impact on the simulator accuracy and are identified as the main focus points for further research.","PeriodicalId":120185,"journal":{"name":"TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127023974","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}
{"title":"Experimental and Numerical Study of Hypersonic Flow over Backward-Facing Step","authors":"C. Zhong, Kojiro Suzuki, Yasumasa Watanabe","doi":"10.2322/tastj.19.735","DOIUrl":"https://doi.org/10.2322/tastj.19.735","url":null,"abstract":"","PeriodicalId":120185,"journal":{"name":"TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123716908","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}
Most of solid propellants have difficulty in controlling magnitude of their thrust or stopping their operation arbitrarily. Some solid propellants show a unique property of self-quenching in intermediate pressure range. This property could be utilized for the realization of actively controlled solid propellant rocket motor. However, little is known about the mechanism of this self-quenching phenomenon. In this paper, a simulation model of this phenomenon is developed and the simulation results are compared with the experiment results to determine the mechanism of this self-quenching phenomenon. The simulation results are in good agreement with the experiment results by assuming self-quenching phenomenon has stochastic nature and by selecting proper parameters.
{"title":"Active Interruption of Motor Combustion for Ammonium-Perchlorate Composite Propellant","authors":"Y. Meichin, Masafumi Tanaka","doi":"10.2322/TASTJ.17.282","DOIUrl":"https://doi.org/10.2322/TASTJ.17.282","url":null,"abstract":"Most of solid propellants have difficulty in controlling magnitude of their thrust or stopping their operation arbitrarily. Some solid propellants show a unique property of self-quenching in intermediate pressure range. This property could be utilized for the realization of actively controlled solid propellant rocket motor. However, little is known about the mechanism of this self-quenching phenomenon. In this paper, a simulation model of this phenomenon is developed and the simulation results are compared with the experiment results to determine the mechanism of this self-quenching phenomenon. The simulation results are in good agreement with the experiment results by assuming self-quenching phenomenon has stochastic nature and by selecting proper parameters.","PeriodicalId":120185,"journal":{"name":"TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122910860","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}
A. Nagata, Atsushi Yasuda, Hiromasa Watanabe, T. Kameda
In recent years, consumer parts have been used in nano satellites or small satellites. Radiation resistance testing is a useful method of evaluating operational stability in the space environment. Since the single event effect (SEE) is a probabilistic phenomenon, it is necessary to monitor the test pieces at all times during the radiation test. If response to a serious error such as SEL is delayed, the test pieces may be damaged or broken, and the accuracy of the test result may be reduced. In this research, a test support system that can instantly detect the occurrence of an SEE and respond automatically was developed in order to improve the efficiency and accuracy of radiation tests. Radiation resistance tests for consumer microcomputers and communication module were conducted using the test support system. From the test results, the effectiveness of the test support system and improvement points were confirmed, and the possibility of space application of consumer microcomputers and communication module were evaluated.
{"title":"Development of a Support System for Radiation Resistance Testing","authors":"A. Nagata, Atsushi Yasuda, Hiromasa Watanabe, T. Kameda","doi":"10.2322/TASTJ.17.263","DOIUrl":"https://doi.org/10.2322/TASTJ.17.263","url":null,"abstract":"In recent years, consumer parts have been used in nano satellites or small satellites. Radiation resistance testing is a useful method of evaluating operational stability in the space environment. Since the single event effect (SEE) is a probabilistic phenomenon, it is necessary to monitor the test pieces at all times during the radiation test. If response to a serious error such as SEL is delayed, the test pieces may be damaged or broken, and the accuracy of the test result may be reduced. In this research, a test support system that can instantly detect the occurrence of an SEE and respond automatically was developed in order to improve the efficiency and accuracy of radiation tests. Radiation resistance tests for consumer microcomputers and communication module were conducted using the test support system. From the test results, the effectiveness of the test support system and improvement points were confirmed, and the possibility of space application of consumer microcomputers and communication module were evaluated.","PeriodicalId":120185,"journal":{"name":"TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114777673","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}
This paper proposes and investigates the use of Adaptive Coding and Modulation (ACM) to maintain high frequency utilization efficiency in accordance with the change of power limits and frequency bandwidth channel limits for the Ka-band high through-put satellite (HTS) system. Improvements in frequency utilization efficiency of the Ka-band satellite channel model have been observed when carrying out ACM using the DVB-S2X modulation scheme and error correcting codes.
{"title":"A Study on ACM for Power and Bandwidth Limited Channel in Satellite Communication System","authors":"M. Ohkawa, H. Wakana, A. Miura","doi":"10.2322/TASTJ.17.142","DOIUrl":"https://doi.org/10.2322/TASTJ.17.142","url":null,"abstract":"This paper proposes and investigates the use of Adaptive Coding and Modulation (ACM) to maintain high frequency utilization efficiency in accordance with the change of power limits and frequency bandwidth channel limits for the Ka-band high through-put satellite (HTS) system. Improvements in frequency utilization efficiency of the Ka-band satellite channel model have been observed when carrying out ACM using the DVB-S2X modulation scheme and error correcting codes.","PeriodicalId":120185,"journal":{"name":"TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123868277","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}
{"title":"Orbit Maintenance for Quasi-Periodic Orbit in Earth-Moon System","authors":"Yang Zhou, M. Bando, S. Hokamoto, Panlong Wu","doi":"10.2322/tastj.19.562","DOIUrl":"https://doi.org/10.2322/tastj.19.562","url":null,"abstract":"","PeriodicalId":120185,"journal":{"name":"TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124267712","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}
{"title":"Process Optimization Method for the Simplification of Developing Indoor Positioning Environment","authors":"K. Tabata, M. Nakajima, N. Kohtake","doi":"10.2322/TASTJ.17.552","DOIUrl":"https://doi.org/10.2322/TASTJ.17.552","url":null,"abstract":"","PeriodicalId":120185,"journal":{"name":"TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116799051","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}
These days, spacecrafts using membrane structures, such as a solar sail, membrane solar panels and so on, have been attracting attention for the use in deep space exploration missions. At the orbit insertion with the aerocapture technique, the membrane structure is expected to work as an efficient decelerator with a large area and small mass. However, its flexible structure causes difficulty in the trajectory analysis and the evaluation of the success rate of the aerocapture because its easily deformed shape as well as the uncertainty in the atmospheric properties significantly degrade the reliability for estimation of the aerodynamic forces, the spacecraft motion and the trajectory. To overcome these problems, the coupled analysis code of the aerodynamics, the structural deformation and the spacecraft motion was developed using the particle based method. In this paper, the method and the validation studies were explained in detail. The simulation results for a solar-sail-type spacecraft flying in the upper atmosphere of Mars for the aerocapture were presented.
{"title":"Coupled Analysis of Aerodynamics, Deformation and Motion for Mars Probe with Flexible Surface in Upper Atmosphere","authors":"Kakeru Tokunaga, Kojiro Suzuki","doi":"10.2322/TASTJ.17.211","DOIUrl":"https://doi.org/10.2322/TASTJ.17.211","url":null,"abstract":"These days, spacecrafts using membrane structures, such as a solar sail, membrane solar panels and so on, have been attracting attention for the use in deep space exploration missions. At the orbit insertion with the aerocapture technique, the membrane structure is expected to work as an efficient decelerator with a large area and small mass. However, its flexible structure causes difficulty in the trajectory analysis and the evaluation of the success rate of the aerocapture because its easily deformed shape as well as the uncertainty in the atmospheric properties significantly degrade the reliability for estimation of the aerodynamic forces, the spacecraft motion and the trajectory. To overcome these problems, the coupled analysis code of the aerodynamics, the structural deformation and the spacecraft motion was developed using the particle based method. In this paper, the method and the validation studies were explained in detail. The simulation results for a solar-sail-type spacecraft flying in the upper atmosphere of Mars for the aerocapture were presented.","PeriodicalId":120185,"journal":{"name":"TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115357983","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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