著者

笠原 次郎 松山 行一 松岡 健 川崎 央 渡部 広吾輝 伊東山 登 後藤 啓介 石原 一輝 松尾 亜紀子 船木 一幸 中田 大将 内海 政春 羽生 宏人 竹内 伸介 荒川 聡 増田 純一 前原 健次 和田 明哲 山田 和彦 KASAHARA Jiro MATSUYAMA Koichi MATSUOKA Ken KAWASAKI Akira WATANABE Hiroaki ITOUYAMA Noboru GOTO Keisuke ISHIHARA Kazuki MATSUO Akiko FUNAKI Ikkoh NAKATA Daisuke UCHIUMI Masaharu HABU Hiroto TAKEUCHI Shinsuke ARAKAWA Satoshi MASUDA Junichi MAEHARA Kenji@@WADA Asato YAMADA Kazuhiko

出版者

宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)

雑誌

観測ロケットシンポジウム2020 講演集 = Proceedings of Sounding Rocket Symposium 2020

巻号頁・発行日

2021-03

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第3回観測ロケットシンポジウム(2021年3月24-25日. オンライン開催)

著者

Goto Keisuke Nishimura Junpei Kawasaki Akira Matsuoka Ken Kasahara Jiro Matsuo Akiko Funaki Ikkoh Nakata Daisuke Uchiumi Masaharu Higashino Kazuyuki

出版者

American Institute of Aeronautics and Astronautics

雑誌

Journal of Propulsion and Power (ISSN:07484658)

巻号頁・発行日

vol.35, no.1, pp.213-223, 2019-01

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Geometric throats are commonly applied to rocket combustors to increase pressure and specific impulse. This paper presents the results from thrust measurements of an ethylene/gas-oxygen rotating detonation engine with various throat geometries in a vacuum chamber to simulate varied backpressure conditions in a range of 1.1–104 kPa. For the throatless case, the detonation channel area was regarded to be equivalent the throat area, and three throat-contraction ratios were tested: 1, 2.5, and 8. Results revealed that combustor pressure was approximately proportional to equivalent throat mass flux for all test cases. Specific impulse was measured for a wide range of pressure ratios, defined as the ratio of the combustor pressure to the backpressure in the vacuum chamber. The rotating detonation engine could achieve almost the same level of optimum specific impulse for each backpressure, whether or not flow was squeezed by a geometric throat. In addition, heat-flux measurements using heat-resistant material are summarized. Temporally and spatially averaged heat flux in the engine were roughly proportional to channel mass flux. Heat-resistant material wall compatibility with two injector shapes of doublet and triplet injection is also discussed.

著者

笠原 次郎 松岡 健 川崎 央 後藤 啓介 横尾 颯也 ブヤコフ バレンティン 松尾 亜紀子 船木 一幸 中田 大将 内海 政春 羽生 宏人 竹内 伸介 山田 和彦 北川 幸樹 戸部 裕史 岩崎 祥大 和田 明哲 Kasahara Jiro Matsuoka Ken Kawasaki Akira Goto Keisuke Yokoo Ryuya Buyakofu Valentin Matsuo Akiko Funaki Ikkoh Nakata Daisuke Uchiumi Masaharu Habu Hiroto Takeuchi Shinsuke Yamada Kazuhiko Kitagawa Koki Tobe Hirobumi Iwasaki Akihiro Wada Asato

出版者

宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)

雑誌

観測ロケットシンポジウム2019 講演集 = Proceedings of Sounding Rocket Symposium 2019

巻号頁・発行日

2019-08

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第2回観測ロケットシンポジウム(2019年8月5日-6日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県

著者

佐藤 哲也 田口 秀之 津江 光洋 土屋 武司 松尾 亜紀子 藤川 貴弘 鈴木 宏二郎 中谷 辰爾 渡邉 保真 森田 直人 手塚 亜聖 石村 康生 宮路 幸二 増田 和三 廣谷 智成 高橋 英美 今村 俊介 大木 純一 西田 俊介 本郷 素行 小島 孝之 SATO Tetsuya TAGUCHI Hideyuki TSUE Mitsuhiro TSUCHIYA Takeshi MATSUO Akiko FUJIKAWA Takahiro SUZUKI Kojiro NAKAYA Shinji WATANAB Yasumasa MORITA Naoto TEZUKA Asei ISHIMURA Kosei MIYAJI Koji MASUDA Kazumi HIROTANI Tomonari TAKAHASHI Hidemi IMAMURA Shunsuke OKI Junichi NISHIDA Shunsuke HONGOH Motoyuki KOJIMA Takayuki

出版者

宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)

雑誌

観測ロケットシンポジウム2020 講演集 = Proceedings of Sounding Rocket Symposium 2020

巻号頁・発行日

2021-03

---

第3回観測ロケットシンポジウム(2021年3月24-25日. オンライン開催)

著者

松岡 健 後藤 啓介 ブヤコフ バレンティン 石原 一輝 野田 朋之 伊東山 登 川﨑 央 渡部 広吾輝 松山 行一 笠原 次郎 松尾 亜紀子 船木 一幸 中田 大将 内海 政春 竹内 伸介 岩崎 祥大 和田 明哲 増田 純一 荒川 聡 羽生 宏人 山田 和彦 MATSUOKA Ken GOTO Keisuke BUYAKOFU Valentin ISHIHARA Kazuki NODA Tomoyuki ITOYAMA Noboru KAWASAKI Akira WATANABE Hiroaki MATSUYAMA Koichi KASAHARA Jiro MATSUO Akiko FUNAKI Ikkoh NAKATA Daisuke UCHIUMI Masaharu TAKEUCHI Shinsuke IWASAKI Akihiro WADA Asato MASUDA Junichi ARAKAWA Satoshi HABU Hiroto YAMADA Kazuhiko

出版者

宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)

雑誌

令和二年度宇宙輸送シンポジウム: 講演集録 = Proceedings of Space Transportation Symposium FY2020

巻号頁・発行日

2021-01

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令和二年度宇宙輸送シンポジウム(2021年1月14日-15日. オンライン開催)

著者

佐藤 哲也 田口 秀之 土屋 武司 藤川 貴弘 小林 弘明 増田 和三 鈴木 宏二郎 松尾 亜紀子 手塚 亜聖 宮路 幸二 青木 隆平 横関 智弘 津江 光洋 中谷 辰璽 廣谷 智成 本郷 素行 小島 孝之 Sato Tetsuya Taguchi Hideyuki Tsuchiya Takeshi Fujikawa Takahiro Kobayashi Hiroaki Masuda Kazumi Suzuki Kojiro Matsuo Akiko Tezuka Asei Miyaji Koji Aoki Takahira Yokozeki Tomohiro Tsue Mitsuhiro Nakaya Shinji Hirotani Tomonari Hongoh Motoyuki Kojima Takayuki

出版者

宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)

雑誌

観測ロケットシンポジウム2019 講演集 = Proceedings of Sounding Rocket Symposium 2019

巻号頁・発行日

2019-08

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第2回観測ロケットシンポジウム(2019年8月5日-6日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県

著者

松岡 健 後藤 啓介 ブヤコフ バレンティン 石原 一輝 野田 朋之 伊東山 登 川﨑 央 渡部 広吾輝 松山 行一 笠原 次郎 松尾 亜紀子 船木 一幸 中田 大将 内海 政春 竹内 伸介 岩崎 祥大 和田 明哲 増田 純一 荒川 聡 羽生 宏人 山田 和彦 MATSUOKA Ken GOTO Keisuke BUYAKOFU Valentin ISHIHARA Kazuki NODA Tomoyuki ITOYAMA Noboru KAWASAKI Akira WATANABE Hiroaki MATSUYAMA Koichi KASAHARA Jiro MATSUO Akiko FUNAKI Ikkoh NAKATA Daisuke UCHIUMI Masaharu TAKEUCHI Shinsuke IWASAKI Akihiro WADA Asato MASUDA Junichi ARAKAWA Satoshi HABU Hiroto YAMADA Kazuhiko

出版者

宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)

雑誌

令和二年度宇宙輸送シンポジウム: 講演集録 = Proceedings of Space Transportation Symposium FY2020

巻号頁・発行日

2021-01

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令和二年度宇宙輸送シンポジウム(2021年1月14日-15日. オンライン開催)著者人数: 21名資料番号: SA6000160027レポート番号: STCP-2020-027

著者

笠原 次郎 松岡 健 川崎 央 松尾 亜紀子 船木 一幸 中田 大将 内海 政春 東野 和幸 Kasahara Jiro Matsuoka Ken Kawasaki Akira Matsuo Akiko Funaki Ikkoh Nakata Daisuke Uchiumi Masaharu Higashino Kazuyuki

出版者

宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)

雑誌

観測ロケットシンポジウム2018 講演集 = Proceedings of Sounding Rocket Symposium 2018

巻号頁・発行日

2018-07

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第1回観測ロケットシンポジウム(2018年7月17日-18日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県

著者

笠原 次郎 松岡 健 川崎 央 後藤 啓介 横尾 颯也 ブヤコフ バレンティン 松尾 亜紀子 船木 一幸 中田 大将 内海 政春 羽生 宏人 竹内 伸介 山田 和彦 北川 幸樹 戸部 裕史 岩崎 祥大 和田 明哲 Kasahara Jiro Matsuoka Ken Kawasaki Akira Goto Keisuke Yokoo Ryuya Buyakofu Valentin Matsuo Akiko Funaki Ikkoh Nakata Daisuke Uchiumi Masaharu Habu Hiroto Takeuchi Shinsuke Yamada Kazuhiko Kitagawa Koki Tobe Hirobumi Iwasaki Akihiro Wada Asato

出版者

宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)

雑誌

観測ロケットシンポジウム2019 講演集 = Proceedings of Sounding Rocket Symposium 2019

巻号頁・発行日

2019-08

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第2回観測ロケットシンポジウム(2019年8月5日-6日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県著者人数: 17名設計製造協力: NETS, 山本機械設計資料番号: SA6000142024レポート番号: Ⅷ-1

著者

Maeda Shinichi Sumiya Satoshi Kasahara Jiro Matsuo Akiko

出版者

Elsevier Inc.

雑誌

Proceedings of the Combustion Institute (ISSN:15407489)

巻号頁・発行日

vol.34, no.2, pp.1973-1980, 2013

被引用文献数

27

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Direct initiations and stabilizations of three-dimensional conical detonation waves were attained by launching spheres with 1.06–1.31 times the C–J velocities into detonable mixtures. We conducted high time-resolution Schlieren visualizations of the whole processes over unsteady initiations to stable propagations of the stabilized Oblique Detonation Waves (ODWs) using a high-speed camera. The detonable mixtures were stoichiometric oxygen mixtures with acetylene, ethylene or hydrogen. They were diluted with argon in a 50% volumetric fraction, and a 75% diluted mixture was also tested for the acetylene/oxygen. The direct initiation of detonation by the projectile and the DDT process like the re-initiation appeared in the initiation process of stabilized ODW. This process eventually led to the stabilized ODW supported by the projectile velocity and the ringed shape detonation wave originating in the re-initiation. We modeled the spatial evolution of stabilized ODW after the re-initiation based on its C–J velocity and angle. The model qualitatively reproduced the measured development rate of stabilized ODW. We also discussed about the detonation stability for the curvature effect arising from the three-dimensional nature of stabilized ODW around the projectile. The curvature effect attenuated the detonation wave below its C–J velocity at the vicinity of projectile. The propagation limits of curvature effect will be responsible for the criticality to attain the stabilized ODWs. By accessing the detailed distributions of propagation velocities and curvature radiuses, the critical curvature radiuses normalized by the cell sizes experimentally revealed to be 8–10 or 15–18 for mixtures diluted with each 50% argon or 75% argon/krypton.

著者

Nagura Yuto Kasahara Jiro Sugiyama Yuta Matsuo Akiko

出版者

Elsevier Inc.

雑誌

Proceedings of the Combustion Institute (ISSN:15407489)

巻号頁・発行日

vol.34, no.2, pp.1949-1956, 2013

被引用文献数

26

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The geometry and characteristic length of diffraction and re-initiation during a two-dimensional detonation propagation were revealed by visualization. C2H4 + 3O2 (unstable), 2C2H2 + 5O2 + 7Ar (stable) and 2C2H2 + 5O2 + 21Ar (stable) were used as the test mixtures. Experiments were performed over the deviation angle range from 30° to 150° and the initial pressure range from 15.8 to 102.3 kPa. By self-emitting photography, we confirmed that the geometry and the characteristic length of diffraction are not different among test gases, with the exception of the fan-like structure of re-initiation that occurred regardless of whether the mixture was unstable or stable. We conducted a compensative experiment by changing the deviation angle and initial pressure, and summarized the detonation diffraction by shadowgraph. At deviation angles larger than 60°, we measured the distances from the vertex of the channel corner to the point where the transverse detonation wave reflected on the under wall (= wall reflection distance) and confirmed that wall reflection distances are approximately in the range of 10–15 times the cell width, whether the mixture is unstable or stable.

著者

Nakayama Hisahiro Kasahara Jiro Matsuo Akiko Funaki Ikkoh

出版者

Elsevier Inc.

雑誌

Proceedings of the Combustion Institute (ISSN:15407489)

巻号頁・発行日

vol.34, no.2, pp.1939-1947, 2013

被引用文献数

61

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The propagation of curved detonation waves of gaseous explosives stabilized in rectangular-cross-section curved channels is investigated. Three types of stoichiometric test gases, C2H4 + 3O2, 2H2 + O2, and 2C2H2 + 5O2 + 7Ar, are evaluated. The ratio of the inner radius of the curved channel (ri) to the normal detonation cell width (λ) is an important factor in stabilizing curved detonation waves. The lower boundary of stabilization is around ri/λ = 23, regardless of the test gas. The stabilized curved detonation waves eventually attain a specific curved shape as they propagate through the curved channels. The specific curved shapes of stabilized curved detonation waves are approximately formulated, and the normal detonation velocity (Dn)−curvature (κ) relations are evaluated. The Dn nondimensionalized by the Chapman–Jouguet (CJ) detonation velocity (DCJ) is a function of the κ nondimensionalized by λ. The Dn/DCJ−λκ relation does not depend on the type of test gas. The propagation behavior of the stabilized curved detonation waves is controlled by the Dn/DCJ−λκ relation. Due to this propagation characteristic, the fully-developed, stabilized curved detonation waves propagate through the curved channels while maintaining a specific curved shape with a constant angular velocity. Self-similarity is seen in the front shock shapes of the stabilized curved detonation waves with the same ri/λ, regardless of the curved channel and test gas.

著者

Yamashita Hiroki Kasahara Jiro Sugiyama Yuta Matsuo Akiko

出版者

Elsevier Inc.

雑誌

Combustion and flame (ISSN:00102180)

巻号頁・発行日

vol.159, no.9, pp.2954-2966, 2012-09

被引用文献数

47 1

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This study was a numerical and experimental investigation of low-temperature auto-ignitions behindreflected shock waves in which a shock tube was employed as the experimental system. We used ahigh-speed video camera and the Schlieren method to visualize the ignition phenomena. Experimentswere performed over a temperature range from 549 ± 10 to 1349 ± 11 K and a pressure range from56 ± 2 to 203 ± 13 kPa, and a non-diluted stoichiometric acetylene–oxygen mixture was chosen as thecombustible gas. We introduced a numerical simulation to help us understand the disturbed temperaturedistribution behind bifurcated shock waves due to interference between reflected shock waves and theboundary layer developed behind incident shock waves. Additionally, we experimentally observed andevaluated quantitatively a tendency for ignition positions to be located farther from the reflecting wallas the temperature decreased behind reflected shock waves. To focus our attention on the ignition positions,we classified the ignition types behind reflected shock waves as near-wall ignition and far-wallignition by 4.7 mm distance from reflecting wall. The criterion for these ignition types was estimatedto be -1.0≦(∂ti/∂T5t)p5t≦-0.5. As a main object in this manuscript, we proposed an ignition modelin which local ignition is induced at some distance from reflecting wall based on the numerical simulationand results; the local ignitions at a point distant from the reflecting wall are induced by the temperaturerise, with the distance from the reflecting wall, immediately behind concave reflected shock wavesdue to developing of bifurcated shock waves. We confirmed that there is no discrepancy between the proposedmodel and experimental results.