{"title":"Numerical Simulation of Impact and Penetration in Regolith with Fluid Model Considering Irreversible Compression and Hardening","authors":"Kojiro Suzuki","doi":"10.2322/tastj.19.726","DOIUrl":"https://doi.org/10.2322/tastj.19.726","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":"120806327","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}
Y. Maru, Kazuki Nohara, Kazuhiko Yamada, H. Takayanagi
{"title":"Aerodynamic Stabilization of Flat Plate for Parachute Drawing Device","authors":"Y. Maru, Kazuki Nohara, Kazuhiko Yamada, H. Takayanagi","doi":"10.2322/tastj.19.660","DOIUrl":"https://doi.org/10.2322/tastj.19.660","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":"120845994","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}
Motoo Ito, T. Okada, Y. Kebukawa, J. Aoki, Y. Kawai, J. Matsumoto, T. Chujo, R. Nakamura, H. Yano, S. Yokota, M. Toyoda, H. Yurimoto, Motoki Watanabe, R. Ikeda, Y. Kubo, N. Grand, H. Cottin, A. Buch, C. Szopa, O. Mori
{"title":"A Feasible Study of In-Situ Measurements of Light Isotopes and Organic Molecules with High Resolution Mass Spectrometer MULTUM on the OKEANOS Mission","authors":"Motoo Ito, T. Okada, Y. Kebukawa, J. Aoki, Y. Kawai, J. Matsumoto, T. Chujo, R. Nakamura, H. Yano, S. Yokota, M. Toyoda, H. Yurimoto, Motoki Watanabe, R. Ikeda, Y. Kubo, N. Grand, H. Cottin, A. Buch, C. Szopa, O. Mori","doi":"10.2322/tastj.19.477","DOIUrl":"https://doi.org/10.2322/tastj.19.477","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":"127488281","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":"Improving Performance of WAX-Based Hybrid Rocket Solid Fuel with Adding Ammonium Nitrate","authors":"Tatsuya Kitagawa, Ikuya Yamazoe, Yuki Nagatsuka, Kenichi Takahashi","doi":"10.2322/tastj.19.507","DOIUrl":"https://doi.org/10.2322/tastj.19.507","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":"125013396","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}
Tatsushi Isono, T. Fujikawa, T. Tsuchiya, Kan Kobayashi, M. Kodera, K. Tani, S. Tomioka
To avoid the severe thermal load within the embeddedly configured Rocket-Based Combined Cycle engine, we arranged the rocket engine location in the present study, that is, the rocket engine was separately mounted for the scramjet flowpath. The rocket engine was taken out from the scramjet flowpath and located on the ramp wall of the scramjet external nozzle. In this case, the ramp wall acted as the additional nozzle in the spike nozzle manner for the rocket internal nozzle. One-dimen-sional analysis showed that there was an optimal expansion ratio favorable for the scramjet external nozzle. Subsequently, more complex analysis was partially performed using Method-of-Characteristics based two-dimensional wave model with some novel modifications, which can express the pressure mismatching between the exhaust and the ambient flows. The two-dimensional analysis showed that thrust production within the scramjet external nozzle could become much lower due to impingement of the cowl lip expansion waves resulting from the pressure mismatching. This pressure change also sizably reduced the thrust performance of the rocket spike nozzle. It was, however, also demonstrated that presently analyzed nozzle system has great potential to drastically improve its thrust performance by means of controlling the impingement of the cowl lip expansion waves.
{"title":"Arrangement of Rocket Engine Location in a Combined Cycle Engine","authors":"Tatsushi Isono, T. Fujikawa, T. Tsuchiya, Kan Kobayashi, M. Kodera, K. Tani, S. Tomioka","doi":"10.2322/TASTJ.17.165","DOIUrl":"https://doi.org/10.2322/TASTJ.17.165","url":null,"abstract":"To avoid the severe thermal load within the embeddedly configured Rocket-Based Combined Cycle engine, we arranged the rocket engine location in the present study, that is, the rocket engine was separately mounted for the scramjet flowpath. The rocket engine was taken out from the scramjet flowpath and located on the ramp wall of the scramjet external nozzle. In this case, the ramp wall acted as the additional nozzle in the spike nozzle manner for the rocket internal nozzle. One-dimen-sional analysis showed that there was an optimal expansion ratio favorable for the scramjet external nozzle. Subsequently, more complex analysis was partially performed using Method-of-Characteristics based two-dimensional wave model with some novel modifications, which can express the pressure mismatching between the exhaust and the ambient flows. The two-dimensional analysis showed that thrust production within the scramjet external nozzle could become much lower due to impingement of the cowl lip expansion waves resulting from the pressure mismatching. This pressure change also sizably reduced the thrust performance of the rocket spike nozzle. It was, however, also demonstrated that presently analyzed nozzle system has great potential to drastically improve its thrust performance by means of controlling the impingement of the cowl lip expansion waves.","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":"123772204","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}
Jet noise is one of the major sources of takeoff and landing noise at airports. The noise is also known to sometimes cause more complicated jet noise-airframe interference problems. Several prediction methods have been proposed to assess this issue in the past. However, the advantages and disadvantages of these methods have not been investigated sufficiently. In this study, three different approaches (i.e., an empirical method, a theoretical method, and an analytical method using the boundary element method) are utilized to predict the effects of a single jet with a horizontal tail. These results are compared with experimental data to clarify the difference. Whereas the results show that none of the three methods can predict noise effects perfectly, we extracted information that can be used as a guideline to choose an appropriate method in the future.
{"title":"Comparison of Prediction Methods on Jet Noise Shielding and Reflection Effects","authors":"J. Akatsuka","doi":"10.2322/tastj.17.597","DOIUrl":"https://doi.org/10.2322/tastj.17.597","url":null,"abstract":"Jet noise is one of the major sources of takeoff and landing noise at airports. The noise is also known to sometimes cause more complicated jet noise-airframe interference problems. Several prediction methods have been proposed to assess this issue in the past. However, the advantages and disadvantages of these methods have not been investigated sufficiently. In this study, three different approaches (i.e., an empirical method, a theoretical method, and an analytical method using the boundary element method) are utilized to predict the effects of a single jet with a horizontal tail. These results are compared with experimental data to clarify the difference. Whereas the results show that none of the three methods can predict noise effects perfectly, we extracted information that can be used as a guideline to choose an appropriate method in the future.","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":"126715452","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. Kuwahara, S. Fujita, Yuji Sato, Yoshihiko Sibuya, Alperen Pala, Hannah Tomio, Yu Murata, Y. Sakamoto
{"title":"On-Board Computers for Micro-Satellites","authors":"T. Kuwahara, S. Fujita, Yuji Sato, Yoshihiko Sibuya, Alperen Pala, Hannah Tomio, Yu Murata, Y. Sakamoto","doi":"10.2322/tastj.19.485","DOIUrl":"https://doi.org/10.2322/tastj.19.485","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":"122037328","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 new performance parameter titled “tubular equivalent regression rate” is introduced to evaluate burning rates in hybrid rockets with geometrically complex solid propellant grains. Tubular equivalent regression rates are calculated for eight previously reported CAMUI-type hybrid rocket firing tests and compared with extrapolations of previously reported empirical correlations for classic, swirl and vortex hybrid rockets. A non-dimensional number titled “CAMUI Number” is introduced to evaluate how CAMUI-like a solid propellant stack is. The CAMUI Number ranges from 0-1: 0 means no CAMUI-type blocks are used, 1 means only CAMUI-type blocks are used. The results show that the tubular equivalent regression rate increases logarithmically with CAMUI Number, and approaches a value of around 3 [mm/s] for a CAMUI Number of 1. This increase in tubular equivalent regression rate is shown to correspond to an increase in performance range from a classic (tubular) hybrid rocket at low CAMUI Numbers (0.1) to surpassing a vortex hybrid rocket for high CAMUI Numbers (>0.7). Furthermore, through the block-by-block analysis of tubular equivalent regression rate in a fuel stack with a CAMUI Number of 0.71, it is shown that maximum burning rates were achieved in blocks under slightly oxidizer rich conditions.
{"title":"Tubular Equivalent Regression Rate in Hybrid Rockets with Complex Geometries","authors":"L. Kamps, H. Nagata","doi":"10.2322/TASTJ.17.544","DOIUrl":"https://doi.org/10.2322/TASTJ.17.544","url":null,"abstract":"A new performance parameter titled “tubular equivalent regression rate” is introduced to evaluate burning rates in hybrid rockets with geometrically complex solid propellant grains. Tubular equivalent regression rates are calculated for eight previously reported CAMUI-type hybrid rocket firing tests and compared with extrapolations of previously reported empirical correlations for classic, swirl and vortex hybrid rockets. A non-dimensional number titled “CAMUI Number” is introduced to evaluate how CAMUI-like a solid propellant stack is. The CAMUI Number ranges from 0-1: 0 means no CAMUI-type blocks are used, 1 means only CAMUI-type blocks are used. The results show that the tubular equivalent regression rate increases logarithmically with CAMUI Number, and approaches a value of around 3 [mm/s] for a CAMUI Number of 1. This increase in tubular equivalent regression rate is shown to correspond to an increase in performance range from a classic (tubular) hybrid rocket at low CAMUI Numbers (0.1) to surpassing a vortex hybrid rocket for high CAMUI Numbers (>0.7). Furthermore, through the block-by-block analysis of tubular equivalent regression rate in a fuel stack with a CAMUI Number of 0.71, it is shown that maximum burning rates were achieved in blocks under slightly oxidizer rich conditions.","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":"124713509","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}
Makoto Wakabayashi, Taku Takada, K. Imai, Y. Kajimura, Jun Nakaya, Kentaro Kitamura, Yukikazu Murakami, Fumio Asai, Masahiro Tokumitsu, Manabu Shinohara, Kazuo Shimada
1) National Institute of Technology (NIT), Niihama College, Niihama, Japan 2) NIT, Kochi College, Nankoku, Japan 3) NIT, Akashi College, Akashi, Japan 4) NIT, Gifu College, Motosu, Japan 5) NIT, Tokuyama College, Shunan, Japan 6) NIT, Kagawa College, Takamatsu, Japan 7) Radio Amateur Satellite Corporation (AMSAT-NA), Kensington, MD, USA 8) NIT, Yonago College, Yonago, Japan 9) NIT, Kagoshima College, Kirishima, Japan 10) Human Network KOSEN, Akishima, Japan
{"title":"Education in Aerospace Engineering: A Report on the 2016 KOSEN Space Camp","authors":"Makoto Wakabayashi, Taku Takada, K. Imai, Y. Kajimura, Jun Nakaya, Kentaro Kitamura, Yukikazu Murakami, Fumio Asai, Masahiro Tokumitsu, Manabu Shinohara, Kazuo Shimada","doi":"10.2322/TASTJ.17.392","DOIUrl":"https://doi.org/10.2322/TASTJ.17.392","url":null,"abstract":"1) National Institute of Technology (NIT), Niihama College, Niihama, Japan 2) NIT, Kochi College, Nankoku, Japan 3) NIT, Akashi College, Akashi, Japan 4) NIT, Gifu College, Motosu, Japan 5) NIT, Tokuyama College, Shunan, Japan 6) NIT, Kagawa College, Takamatsu, Japan 7) Radio Amateur Satellite Corporation (AMSAT-NA), Kensington, MD, USA 8) NIT, Yonago College, Yonago, Japan 9) NIT, Kagoshima College, Kirishima, Japan 10) Human Network KOSEN, Akishima, Japan","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":"124763332","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}
The reference orbit implemented for the active TerraSAR-X mission works remarkably well for orbit control purposes, but an unexpected secular drift in the along-track separation between satellite and reference orbits has built up to a 60 s flight-time offset within 10 years of operation. The scope of this work is to understand the origin of the drift and to eliminate the effect for DLRs future repeat ground-track missions EnMAP and Tandem-L. The improved process of reference orbit generation is discussed and the underlying relations for the suggested inclination adjustment are derived. The improved process is successfully validated by means of 1-year numerical orbit control simulation. The presented process is generic and can be applied to any repeat-ground track mission.
{"title":"Improved Reference Orbits for the Repeat-Ground-Track Missions EnMAP and Tandem-L","authors":"R. Kahle, S. Spiridonova, M. Kirschner","doi":"10.2322/tastj.17.308","DOIUrl":"https://doi.org/10.2322/tastj.17.308","url":null,"abstract":"The reference orbit implemented for the active TerraSAR-X mission works remarkably well for orbit control purposes, but an unexpected secular drift in the along-track separation between satellite and reference orbits has built up to a 60 s flight-time offset within 10 years of operation. The scope of this work is to understand the origin of the drift and to eliminate the effect for DLRs future repeat ground-track missions EnMAP and Tandem-L. The improved process of reference orbit generation is discussed and the underlying relations for the suggested inclination adjustment are derived. The improved process is successfully validated by means of 1-year numerical orbit control simulation. The presented process is generic and can be applied to any repeat-ground track 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":"116287796","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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