TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN最新文献_第2页

Numerical Simulation of Impact and Penetration in Regolith with Fluid Model Considering Irreversible Compression and Hardening 考虑不可逆压缩和硬化的风化层冲击和侵彻的流体模型数值模拟

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN Pub Date : 1900-01-01 DOI: 10.2322/tastj.19.726

Kojiro Suzuki

引用次数: 0

Aerodynamic Stabilization of Flat Plate for Parachute Drawing Device 降落伞牵引装置平板气动稳定性研究

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN Pub Date : 1900-01-01 DOI: 10.2322/tastj.19.660

Y. Maru, Kazuki Nohara, Kazuhiko Yamada, H. Takayanagi

引用次数: 0

A Feasible Study of In-Situ Measurements of Light Isotopes and Organic Molecules with High Resolution Mass Spectrometer MULTUM on the OKEANOS Mission 在OKEANOS任务中使用MULTUM高分辨率质谱仪原位测量轻同位素和有机分子的可行性研究

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN Pub Date : 1900-01-01 DOI: 10.2322/tastj.19.477

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

引用次数: 1

Improving Performance of WAX-Based Hybrid Rocket Solid Fuel with Adding Ammonium Nitrate 硝酸铵对蜡基混合火箭固体燃料性能的改善

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN Pub Date : 1900-01-01 DOI: 10.2322/tastj.19.507

Tatsuya Kitagawa, Ikuya Yamazoe, Yuki Nagatsuka, Kenichi Takahashi

引用次数: 0

Arrangement of Rocket Engine Location in a Combined Cycle Engine 联合循环发动机中火箭发动机位置的布置

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN Pub Date : 1900-01-01 DOI: 10.2322/TASTJ.17.165

Tatsushi Isono, T. Fujikawa, T. Tsuchiya, Kan Kobayashi, M. Kodera, K. Tani, S. Tomioka

{"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}

引用次数: 0

Comparison of Prediction Methods on Jet Noise Shielding and Reflection Effects 射流噪声屏蔽与反射效应预测方法的比较

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN Pub Date : 1900-01-01 DOI: 10.2322/tastj.17.597

J. Akatsuka

引用次数: 0

On-Board Computers for Micro-Satellites 微型卫星机载计算机

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN Pub Date : 1900-01-01 DOI: 10.2322/tastj.19.485

T. Kuwahara, S. Fujita, Yuji Sato, Yoshihiko Sibuya, Alperen Pala, Hannah Tomio, Yu Murata, Y. Sakamoto

引用次数: 0

Tubular Equivalent Regression Rate in Hybrid Rockets with Complex Geometries 复杂几何形状混合火箭的管状等效回归率

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN Pub Date : 1900-01-01 DOI: 10.2322/TASTJ.17.544

L. Kamps, H. Nagata

{"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}

引用次数: 4

Education in Aerospace Engineering: A Report on the 2016 KOSEN Space Camp 航空航天工程教育:2016年科森太空营报告

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN Pub Date : 1900-01-01 DOI: 10.2322/TASTJ.17.392

Makoto Wakabayashi, Taku Takada, K. Imai, Y. Kajimura, Jun Nakaya, Kentaro Kitamura, Yukikazu Murakami, Fumio Asai, Masahiro Tokumitsu, Manabu Shinohara, Kazuo Shimada

引用次数: 0

Improved Reference Orbits for the Repeat-Ground-Track Missions EnMAP and Tandem-L 重复地面轨道任务EnMAP和Tandem-L的改进参考轨道

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN Pub Date : 1900-01-01 DOI: 10.2322/tastj.17.308

R. Kahle, S. Spiridonova, M. Kirschner

引用次数: 4