Failure of the orbit insertion maneuver has a significant impact on the entire mission, for the trajectory of a spacecraft is largely deflected by swing-by. The risk can be reduced by targeting a point on the B-plane where the spacecraft reaches the free-return (FR) trajectory with the target body in the case of insertion failure. The backup orbit must also satisfy conditions suitable for the mission. We investigated the type of orbit insertion that is both robust to failure and reasonable for the mission requirements. We call this method FR ensured orbit insertion. Among various failure modes of the orbit insertion maneuver, we focus on the complete maneuver failure. The impact parameters on the B-plane to achieve the orbit insertion are formulated based on the geometry of velocity vectors at swing-by. The necessary deflection angle α FR at swing-by must be smaller than the possible maximum deflection angle α max for the target body. When we introduce proper scaling factors, the relation of α max and α FR is characterized by a single parameter λ . Using polar orbit insertion as an example, maps which show the reachability of FR trajectory after the insertion failure for each approaching condition are presented. The derived maps can be used as a tool to assess the applicability of the method in the mission design. Finally, as an application to practical mission design, we demonstrate the use of FR ensured orbit insertion in JAXA’s MMX mission.
{"title":"General Characteristics of Free-Return Ensured Orbit Insertion and Trajectory Design with MOI Robustness in MMX Mission","authors":"Shota Takahashi, N. Ogawa, Y. Kawakatsu","doi":"10.2322/TASTJ.17.404","DOIUrl":"https://doi.org/10.2322/TASTJ.17.404","url":null,"abstract":"Failure of the orbit insertion maneuver has a significant impact on the entire mission, for the trajectory of a spacecraft is largely deflected by swing-by. The risk can be reduced by targeting a point on the B-plane where the spacecraft reaches the free-return (FR) trajectory with the target body in the case of insertion failure. The backup orbit must also satisfy conditions suitable for the mission. We investigated the type of orbit insertion that is both robust to failure and reasonable for the mission requirements. We call this method FR ensured orbit insertion. Among various failure modes of the orbit insertion maneuver, we focus on the complete maneuver failure. The impact parameters on the B-plane to achieve the orbit insertion are formulated based on the geometry of velocity vectors at swing-by. The necessary deflection angle α FR at swing-by must be smaller than the possible maximum deflection angle α max for the target body. When we introduce proper scaling factors, the relation of α max and α FR is characterized by a single parameter λ . Using polar orbit insertion as an example, maps which show the reachability of FR trajectory after the insertion failure for each approaching condition are presented. The derived maps can be used as a tool to assess the applicability of the method in the mission design. Finally, as an application to practical mission design, we demonstrate the use of FR ensured orbit insertion in JAXA’s MMX mission.","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":"116897223","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}
T. Okada, T. Fukuhara, Satoshi Tanaka, M. Taguchi, T. Arai, H. Senshu, N. Sakatani, Y. Shimaki, H. Demura, Y. Ogawa, K. Kitazato, K. Suko, T. Sekiguchi, T. Kouyama, J. Takita, T. Matsunaga, T. Imamura, T. Wada, S. Hasegawa, J. Helbert, T. Mueller, A. Hagermann, J. Biele, M. Grott, M. Hamm, M. Delbo’, N. Hirata, N. Hirata, Yukio Yamamoto, F. Terui, T. Saiki, S. Nakazawa, M. Yoshikawa, Sei‐ichiro Watanabe, Y. Tsuda
{"title":"Thermophysical Properties of C-Type Asteroid 162173 Ryugu Revealed by the Thermal Infrared Imager TIR on Hayabusa2","authors":"T. Okada, T. Fukuhara, Satoshi Tanaka, M. Taguchi, T. Arai, H. Senshu, N. Sakatani, Y. Shimaki, H. Demura, Y. Ogawa, K. Kitazato, K. Suko, T. Sekiguchi, T. Kouyama, J. Takita, T. Matsunaga, T. Imamura, T. Wada, S. Hasegawa, J. Helbert, T. Mueller, A. Hagermann, J. Biele, M. Grott, M. Hamm, M. Delbo’, N. Hirata, N. Hirata, Yukio Yamamoto, F. Terui, T. Saiki, S. Nakazawa, M. Yoshikawa, Sei‐ichiro Watanabe, Y. Tsuda","doi":"10.2322/tastj.19.654","DOIUrl":"https://doi.org/10.2322/tastj.19.654","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":"125820275","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 Study on the Application of Flat Spin to Vertical Landing of a Fixed-Wing Small UAV","authors":"S. Higashino, Kota Nakama, Yuki Sumitomo","doi":"10.2322/tastj.20.1","DOIUrl":"https://doi.org/10.2322/tastj.20.1","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":"127252853","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}
M. Hashimoto, M. Funatsu, Nurul Malisa, Gen Morioka, M. Ozawa
{"title":"Temperature Estimations of SiC Ablations with Several Kinds of Narrow Band-pass Filters","authors":"M. Hashimoto, M. Funatsu, Nurul Malisa, Gen Morioka, M. Ozawa","doi":"10.2322/TASTJ.17.561","DOIUrl":"https://doi.org/10.2322/TASTJ.17.561","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":"127301118","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}
JAXA has operated the heavy ion telescope located on the ISS/JEM-EF since 2009, and prepared for the publication of data. Due to the long-term operation, there are concerns over the degradation of its silicon sensors and circuits. The calibration operations were conducted in May 2012 and August 2016. We checked for such deterioration but have not yet to confirm the degree of degradation. For the correct determination of atomic number and incident energy, a more accurate calculation method was examined and then applied. As a result, a good correlation with CREME96 was confirmed.
{"title":"The Status of the Heavy Ion Telescope on the ISS/JEM-EF","authors":"H. Ueno, H. Matsumoto, K. Koga","doi":"10.2322/TASTJ.17.68","DOIUrl":"https://doi.org/10.2322/TASTJ.17.68","url":null,"abstract":"JAXA has operated the heavy ion telescope located on the ISS/JEM-EF since 2009, and prepared for the publication of data. Due to the long-term operation, there are concerns over the degradation of its silicon sensors and circuits. The calibration operations were conducted in May 2012 and August 2016. We checked for such deterioration but have not yet to confirm the degree of degradation. For the correct determination of atomic number and incident energy, a more accurate calculation method was examined and then applied. As a result, a good correlation with CREME96 was confirmed.","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":"122831544","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}
Joshua J. R. Critchley-Marrows, M. Isacsson, Agnes Gårdebäck
The power system is one of the most important subsystems for a successful space mission. Any failure in this subsystem leads to a direct loss of a satellite. This creates a need for a power schedule to be effectively and efficiently produced, especially if requirements are constantly changing. This paper presents the application of linear programming techniques to solving the power schedule problem, with the more specific usage of mixed-integer linear programming (MILP). The illustration of the approach is applied to a Swedish student satellite, which consists of the necessary subsystems and eight separate experiments. Two programs are developed, one studying the satellite lifetime in terms of orbital cycles and the other studying the individual orbit cycle. Simulating the lifetime of the satellite over 5000 orbit cycles, the battery level did not decline below 76.35%. Using a computer with an Intel i4 processor, this simulation took 3.2 hrs, with individual orbits taking 2.3 s each. Further work includes developing the program to be completed on-aboard the satellite, adapting to new scenarios, and incorporating a model for the decline of battery performance over time.
{"title":"Applications of Linear Programming Techniques to Satellite Power Management and Scheduling","authors":"Joshua J. R. Critchley-Marrows, M. Isacsson, Agnes Gårdebäck","doi":"10.2322/tastj.17.57","DOIUrl":"https://doi.org/10.2322/tastj.17.57","url":null,"abstract":"The power system is one of the most important subsystems for a successful space mission. Any failure in this subsystem leads to a direct loss of a satellite. This creates a need for a power schedule to be effectively and efficiently produced, especially if requirements are constantly changing. This paper presents the application of linear programming techniques to solving the power schedule problem, with the more specific usage of mixed-integer linear programming (MILP). The illustration of the approach is applied to a Swedish student satellite, which consists of the necessary subsystems and eight separate experiments. Two programs are developed, one studying the satellite lifetime in terms of orbital cycles and the other studying the individual orbit cycle. Simulating the lifetime of the satellite over 5000 orbit cycles, the battery level did not decline below 76.35%. Using a computer with an Intel i4 processor, this simulation took 3.2 hrs, with individual orbits taking 2.3 s each. Further work includes developing the program to be completed on-aboard the satellite, adapting to new scenarios, and incorporating a model for the decline of battery performance over time.","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":"121540347","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":"Automated Image Processing Module for Images Captured by Earth Observation Microsatellite Diwata-1 as Support for Ground Station Operations","authors":"Julie Ann Banatao, Y. Sakamoto, Kazuya Yoshida","doi":"10.2322/tastj.19.493","DOIUrl":"https://doi.org/10.2322/tastj.19.493","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":"131138904","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":"Performance of Gas-Generator-Type Hybrid Thruster Using a Laser Ignition","authors":"Shougo Yamashita, Yasuyuki Yano, Akira Kakami","doi":"10.2322/tastj.19.802","DOIUrl":"https://doi.org/10.2322/tastj.19.802","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":"134133767","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}
Masanori Matsushita, N. Okuizumi, Y. Satou, T. Iwasa, O. Mori, S. Matunaga
{"title":"Shape of a Square Solar Sail Consisted of Four Trapezoid Petals with Curved Thin-Film Devices: Simulations and Experiments","authors":"Masanori Matsushita, N. Okuizumi, Y. Satou, T. Iwasa, O. Mori, S. Matunaga","doi":"10.2322/tastj.19.604","DOIUrl":"https://doi.org/10.2322/tastj.19.604","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":"132389047","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}
Satellite charging causes anomalies and its effect still accounts for the main part of failure that occurs in the space environment. It is important to measure plasma particles in order to elucidate the interactions between such charging and the space environment. For this purpose, the Avalanche PhotoDiode (APD) type sensor is used to minimize instrument size and weight. The APD basically measures photons, but can also be used to measure electrons. This paper reports the performance of the APD sensor, and presents the instrument design results for flight investigation.
{"title":"Development of Avalanche PhotoDiode (APD) Type Electron Measurement Unit for Space Use Focused on Satellite Charging","authors":"K. Koga, H. Ueno","doi":"10.2322/tastj.17.380","DOIUrl":"https://doi.org/10.2322/tastj.17.380","url":null,"abstract":"Satellite charging causes anomalies and its effect still accounts for the main part of failure that occurs in the space environment. It is important to measure plasma particles in order to elucidate the interactions between such charging and the space environment. For this purpose, the Avalanche PhotoDiode (APD) type sensor is used to minimize instrument size and weight. The APD basically measures photons, but can also be used to measure electrons. This paper reports the performance of the APD sensor, and presents the instrument design results for flight investigation.","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":"114046999","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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