基本情報
研究分野
1論文
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Journal of Spacecraft and Rockets 60(1) 181-189 2023年1月A detonation engine system is successfully demonstrated for the first time in space using sounding rocket S-520-31 of the Japan Aerospace Exploration Agency/Institute of Space Astronautical Science. Detailed flight results of an S-shaped pulse detonation engine (PDE) installed in the rocket are presented herein. The flight is conducted to confirm that the PDE and its system operate at scheduled sequences in space, confirm the reproducibility of the PDE cycle, and despin the rocket around its axis. It is confirmed that the PDE operated successfully for 14 cycles in space. The experimental plateau pressure of 2.0 0.1 MPais 80 3% of the calculated plateau pressure, which suggests that detonation occurred in 14 cycles. The pressure profiles of the cycles are similar, and the pressure integrals are 2.0 0.1 kN⋅ s∕m2, confirming the excellent reproducibility of the PDE cycle. A probability statistical approach assuming a Gaussian distribution is applied to determine the average angular acceleration difference between processes of the PDE operation, mixture supply, and oxygen supply. The results suggested that the PDE despun the rocket via the thrust produced via detonation combustion, which is consistent with a quasi-steady-state model with an accuracy of 101 15%.
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Journal of Spacecraft and Rockets 60(1) 273-285 2023年1月To create a new flyable detonation propulsion system, a detonation engine system (DES) that can be stowed in sounding rocket S-520-31 has been developed. This paper focused on the first flight demonstration in the space environment of a DES-integrated rotating detonation engine (RDE) using S-520-31. The flight result was compared with ground-test data to validate its performance. In the flight experiment, the stable combustion of the annulus RDE with a plug-shaped inner nozzle was observed by onboard digital and analog cameras. With a time-averaged mass flow of 182 11 g∕s and an equivalence ratio of 1.2 0.2, the RDE generated a time-averaged thrust of 518 N and a specific impulse of 290 18 s, which is almost identical to the ideal value of constant pressure combustion. Due to the RDE combustion, the angular velocity increased by 5.7 deg ∕s in total, and the time-averaged torque from the rotational component of the exhaust during 6 s of operation was 0.26 N ⋅ m. The high-frequency sampling data identified the detonation frequency during the recorded time as 20 kHz in the flight, which was confirmed by the DES ground test through high-frequency sampling data analysis and high-speed video imaging.
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日本航空宇宙学会誌 70(11) 224-233 2022年11月5日2021年7月27日早朝5:30,JAXA内之浦宇宙空間観測所からデトネーションエンジンシステムを搭載した観測ロケットS-520-31号機が打ち上げられた.高度約200kmにてメタン–酸素推進剤による回転デトネーションエンジン(RDE)の6秒間作動およびパルスデトネーションエンジン(PDE)の2Hz作動を実施した.取得されたフライトデータから,RDE作動で時間平均推力518N,比推力290±18sおよび速度増速量8.0m/sを達成した.PDE作動では1サイクル当たりの圧力時間積分値が5%以内の高精度での繰り返しインパルス生成およびロケット機軸周りのスピンレート減少が確認された.本結果は,地上燃焼試験データとよく一致し,宇宙空間でのデトネーションエンジン作動が実証された.デトネーション波の判定に用いた圧力・加速度センサの高速サンプリングデータおよびRDEプルーム撮影用のデジタルカメラ画像は,JAXA/ISASで開発された再突入データ回収システムRATSにて回収することに成功した.
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AIAA SCITECH 2022 Forum 2022年1月3日
MISC
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第58回宇宙科学技術連合講演会講演集 = Proceedings of 58th Space Sciences and Technology Conference 2014年11月第58回宇宙科学技術連合講演会(2014年11月12日-15日. 長崎ブリックホール), 長崎市, 長崎県資料番号: AC1500019000レポート番号: JSASS-2014-4142
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大気球シンポジウム: 平成26年度 = Balloon Symposium: 2014 2014年11月大気球シンポジウム 平成26年度(2014年11月6-7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: 18名資料番号: SA6000021006レポート番号: isas14-sbs-006
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International Journal of Microgravity Science and Application 31(3) 130-130 2014年We performed microgravity experiments of homogeneous nucleation of iron from the vapor phase using the sounding rocket S-520-28 on December 17, 2012. The purpose is determination of a sticking probability of iron during the nucleation from the supersaturated vapor, because the sticking probability is one of the most uncertain physical quantities to understand the formation process of cosmic dust based on nucleation theories. We prepared the specially designed MachZehnder-type interferometers with an evaporation chamber and camera recording systems to fit the space and weight limitations of the rocket. Three same systems, named DUST 1 to 3, were installed into the rocket. Iron was evaporated in an argon gas and then it was cooled and nucleated to form nanoparticles. The temperature and concentration of iron vapor at the nucleation site are determined from the movement of the interference fringe. Here, we present the brief summary of the experiments and the preliminary results of the homogeneous nucleation from iron vapor under microgravity.
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日本惑星科学会秋期講演会予稿集 2013 "O12-05" 2013年11月20日
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平成24年度宇宙輸送シンポジウム: 講演集録 = Proceedings of Space Transportation Symposium: FY2012 2013年1月平成24年度宇宙輸送シンポジウム (2013年1月17日-1月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, 神奈川県形態: カラー図版あり形態: PDF著者人数: 18名資料番号: AA0061856051レポート番号: STCP-2012-051
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電子情報通信学会技術研究報告. SANE, 宇宙・航行エレクトロニクス 111(239) 53-56 2011年10月10日"Small space science Platform for Rapid INvestigation and Test", aka SPRINT - project is a new satellite series for scientific applications of Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (ISAS/JAXA). The design concept of the satellite bus is based on flexibility with alternative, and selectable options. SPRINT-A is the first satellite of the series, which aims to make scientific observations of planetary atmosphere at extreme-ultraviolet wavelength.
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Dynamics & Design Conference 2011 _105-1_-_105-7_ 2011年Our novel invention: "digital self-powered autonomous" vibration controller using a digital micro-processor is presented. The invented unit is a completely self-powered control system that does not require any external power-supply at all. Nevertheless, this digital, self-directive, and self-powered approach enables the system to be programmable and thus versatile in control scheme. The digital-autonomous controller is much more advanced and progressive than conventional analog-autonomous ones that are clumsy and awkward. This digital system can be implemented in multiple-input multiple-output systems to suppress even complicated structural vibrations. This is quite useful for various applications to energy-saving or energy-shortage systems, such as large space structures, artificial satellites, and isolated lunar bases, which all are vulnerable to long night-time without solar-power.
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日本航空宇宙学会論文集 58(681) 302-307 2010年This paper includes evaluations of composite tanks or pressure vessels based on fracture mechanics and an improved method for tank design. Problems of exfoliation between the mouthpiece and composite in current composite pressure vessels are shown, and the simple solution by inducing a slit into the mouthpiece near the bonding interface is proposed. The effect of the slit is evaluated using a geometrically simple model as well as a pressure vessel model designed for a rocket.
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日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences 56(651) 169-178 2008年4月5日Adhesive bonding structure around a metalic mouthpiece of a cryogenic composite tank was analyzed based on fracture mechanics. Energy release rate was analytically formulated considering difference in strain energies in tension and bending between before and after the crack growth based on a simplified mathematical model. The analytical results were compared with the calculated results by finite element method for five example tanks; they revealed fairly good match. This analysis gives a guideline of the initial optimal design of a cryogenic composite tank based on fracture mechanics.
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日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences 49(571) 255-261 2001年8月5日In this paper, a three-dimensional analysis of launching dynamics of a sounding rocket is investigated. In the analysis, the elastic vibration of the vehicle and launcher is considered. To estimate a trajectory dispersion including the effect of elasticity of the vehicle and launcher, a three-dimensional numerical simulation of a launch is performed. The accuracy of the numerical simulation is discussed and it is concluded that the simulation can estimate the maximum value of the trajectory dispersion properly. After that, the maximum value is estimated for the actual sounding rocket and the value is shown to be within the safty margin for this particular case.
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宇宙科学研究所報告 100(100) 1-34 1998年3月本報告では, 発射時に生じるロケット本体及びランチャーの弾性振動に起因する Viper ロケットの軌道分散について報告する。軌道分散の推定のために, ロケット及びランチャーの弾性を考慮した発射の三次元数値シミュレーションを行なった。実際の発射時に計測された振動データとの比較によりシミュレーションの精度を確認した後に, シミュレーションを用いて軌道分散の推定を行なった。その結果, 弾性振動に起因する軌道分散は実際の打ち上げミッションにおいて問題にならない値であることが確認された。資料番号: SA0165943000
講演・口頭発表等
1共同研究・競争的資金等の研究課題
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日本学術振興会 科学研究費助成事業 2019年4月 - 2022年3月
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日本学術振興会 科学研究費助成事業 2014年4月 - 2017年3月
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日本学術振興会 科学研究費助成事業 2004年 - 2005年