顔写真

サイトウ ユウジ
齋藤 勇士
Yuji Saito
所属
高等研究機構学際科学フロンティア研究所 新領域創成研究部学際基盤研究分野 物質材料・エネルギー研究領域
職名
助教
学位
  • 博士(工学)(北海道大学)

  • 修士(工学)(北海道大学)

経歴 8

  • 2024年1月 ~ 継続中
    東北大学 グリーン未来創造機構(兼務)

  • 2021年7月 ~ 継続中
    東北大学プロミネントリサーチフェロー

  • 2021年4月 ~ 継続中
    東北大学 流体科学研究所(兼務)

  • 2021年4月 ~ 継続中
    東北大学 学際科学フロンティア研究所 新領域創成研究部 助教

  • 2019年1月 ~ 2021年3月
    東北大学 工学研究科 助教

  • 2018年4月 ~ 2018年12月
    東京大学 大学院新領域創成科学研究科 特任研究員

  • 2017年4月 ~ 2018年3月
    北海道大学 大学院工学院 日本学術振興会特別研究員(DC2)

  • 2017年11月 ~ 2017年12月
    Sapienza, University of Rome Research Intern

︎全件表示 ︎最初の5件までを表示

学歴 4

  • 北海道大学 大学院工学院 機械宇宙工学専攻(博士後期課程)

    2016年4月 ~ 2018年3月

  • 北海道大学 大学院工学院 機械宇宙工学専攻(博士前期課程)

    2014年4月 ~ 2016年3月

  • 北海道大学 工学部 機械知能工学科

    2012年4月 ~ 2014年3月

  • 国立沼津工業高等専門学校 機械工学科

    2007年4月 ~ 2012年3月

委員歴 1

  • International Astronautical Federation (IAF) Space Propulsion Committee

    2023年4月 ~

所属学協会 4

  • 日本燃焼学会

    2021年5月 ~ 継続中

  • AIAA

  • 日本機械学会

  • 日本航空宇宙学会

研究キーワード 4

  • 宇宙推進

  • スパースセンシング

  • 拡散火炎

  • ハイブリッドロケット

研究分野 1

  • フロンティア(航空・船舶) / 航空宇宙工学 /

受賞 10

  1. 第16回宇宙科学奨励賞

    2024年3月 公益財団法人宇宙科学振興会 端面燃焼式ハイブリッドロケットの燃焼特性および推力制御特性の解明

  2. 2018 AIAA Hybrid Rockets Best Paper

    2019年8月 American Institute of Aeronautics and Astronautics Investigation of Graphite Nozzle Erosion in Hybrid Rockets Using O2/C2H4

  3. 奨励賞

    2019年4月 日本航空宇宙学会 端面燃焼式ハイブリッドロケットの推力制御特性に関する研究

  4. 2016 AIAA Best Hybrid Rockets Student Paper

    2017年7月 American Institute of Aeronautics and Astronautics Experimental and Analytical Investigation of Effect of Pressure on Regression Rate of Axial-Injection End-Burning Hybrid Rockets

  5. 学会賞(論文賞)

    2022年8月 可視化情報学会 非定常せん断応力の可視化計測にむけた蛍光油膜法の開発

  6. 第 7 回東北大学若手アンサンブルワークショップ優秀ポスター賞

    2021年5月 東北大学附置研究所若手アンサンブルプロジェクト アルミニウムと水燃焼による革新的宇宙推進システム実現に向けて

  7. 第48回日本航空宇宙学会年会講演会 優秀発表賞

    2017年4月 日本航空宇宙学会

  8. 北部支部2016年講演会 Good Presentation Award for Student

    2016年3月 日本航空宇宙学会

  9. The Second Prize -International Students Symposium and Competition-

    2014年5月 14th International Space Conference of Pacific-basin Societies

  10. 畠山賞

    2012年3月 日本機械学会

︎全件表示 ︎最初の5件までを表示

論文 47

  1. Simplified Data-Reduction Method for Hybrid Propulsion 国際誌 査読有り

    Yuji Saito, Shota Kameyama, Toshinori Kuwahara

    Journal of Propulsion and Power 1-7 2024年2月29日

    出版者・発行元:American Institute of Aeronautics and Astronautics (AIAA)

    DOI: 10.2514/1.b39387  

    ISSN:0748-4658

    eISSN:1533-3876

  2. Sensor Selection with Cost Function using Nondominated-Solution-based Multi-objective Greedy Method 国際誌 査読有り

    Yuji Saito, Kumi Nakai, Takayuki Nagata, Keigo Yamada, Taku Nonomura, Kazuki Sakaki, Yoshio Nunome

    IEEE Sensors Journal 23 (24) 1-1 2023年12月14日

    出版者・発行元:Institute of Electrical and Electronics Engineers (IEEE)

    DOI: 10.1109/jsen.2023.3328005  

    ISSN:1530-437X

    eISSN:1558-1748 2379-9153

  3. High Pressure Fuel Regression Characteristics of Axial-Injection End-Burning Hybrid Rockets 査読有り

    Yuji Saito, Masaya Kimino, Ayumu Tsuji, Yushi Okutani, Kentaro Soeda, Harunori Nagata

    JOURNAL OF PROPULSION AND POWER 35 (2) 328-341 2019年3月

    出版者・発行元:AMER INST AERONAUTICS ASTRONAUTICS

    DOI: 10.2514/1.B37135  

    ISSN:0748-4658

    eISSN:1533-3876

    詳細を見る 詳細を閉じる

    This study is an investigation of axial-injection end-burning hybrid rockets aimed at revealing fuel regression characteristics under relatively high-pressure conditions. Firing tests are conducted using gaseous oxygen as the oxidizer at chamber pressures and oxidizer port velocities ranging from 0.22 to 1.05 MPa and 31 to 103 m/s, respectively. The results of 15 static firing tests show that the fuel regression rate increases as the chamber pressure increases, and regression rates range from approximately 1.1 mm/s at 0.25 MPa to 5.5 mm/s at 0.90 MPa. Furthermore, it is observed that the pressure exponent of the fuel regression rate is 1.05 and the fuel regression rate is not influenced by the oxidizer port velocity in this study. The model explains that the backfiring problem tends to occur in relatively high-pressure conditions, and it leads to the conclusion that increasing the nozzle throat diameter is an effective means of preventing backfiring from occurring.

  4. Fuel Regression Characteristics of a Novel Axial-Injection End-Burning Hybrid Rocket 査読有り

    Yuji Saito, Toshiki Yokoi, Hiroyuki Yasukochi, Kentaro Soeda, Tsuyoshi Totani, Masashi Wakita, Harunori Nagata

    JOURNAL OF PROPULSION AND POWER 34 (1) 247-259 2018年1月

    出版者・発行元:AMER INST AERONAUTICS ASTRONAUTICS

    DOI: 10.2514/1.B36369  

    ISSN:0748-4658

    eISSN:1533-3876

    詳細を見る 詳細を閉じる

    The regression characteristics of axial-injection end-burning hybrid rocket were experimentally investigated using a laboratory-scale motor. The axial-injection end-burning type fuel grains were made by high-accuracy three-dimensional printing. Firing tests were conducted using gaseous oxygen as the oxidizer at a chamber pressure range of 0.10 to 0.43MPa. Results of 15 static firings tests show that fuel regression rate increases as the chamber pressure rises, and fuel regression rate decreases as the oxidizer port velocity increases. A data reduction method was developed to avoid the difficulty in calculating oxidizer-to-fuel ratio. A simplified fuel regression model based on the granular diffusion flame model is developed to investigate regression characteristics. The trend in results as calculated using the granular diffusion flame model agrees with that in experimentally observe values. However, this does not hold true in tests with varying oxidizer port velocity. A granular diffusion flame model only takes into account simple solid propellant regression. Therefore, modification of the model is needed for calculating the fuel regression rate of an end-burning hybrid rocket.

  5. Sensor Selection by Greedy Method for Linear Dynamical Systems: Comparative Study on Fisher-Information-Matrix, Observability-Gramian and Kalman-Filter-Based Indices 国際誌 査読有り

    Shun Takahashi, Yasuo Sasaki, Takayuki Nagata, Keigo Yamada, Kumi Nakai, Yuji Saito, Taku Nonomura

    IEEE Access 11 67850-67864 2023年6月3日

    出版者・発行元:Institute of Electrical and Electronics Engineers (IEEE)

    DOI: 10.1109/access.2023.3291415  

    eISSN:2169-3536

  6. Randomized Group-Greedy Method for Large-Scale Sensor Selection Problems 国際誌 査読有り

    Takayuki Nagata, Keigo Yamada, Kumi Nakai, Yuji Saito, Taku Nonomura

    IEEE Sensors Journal 23 (9) 9536-9548 2023年5月1日

    出版者・発行元:None

    DOI: 10.1109/jsen.2023.3258223  

    ISSN:1530-437X

    eISSN:1558-1748 2379-9153

  7. Observation site selection for physical model parameter estimation towards process-driven seismic wavefield reconstruction 国際誌 査読有り

    K Nakai, T Nagata, K Yamada, Y Saito, T Nonomura, M Kano, S Ito, H Nagao

    Geophysical Journal International 234 (3) 1786-1805 2023年4月18日

    出版者・発行元:None

    DOI: 10.1093/gji/ggad165  

    ISSN:0956-540X

    eISSN:1365-246X

  8. Seismic wavefield reconstruction based on compressed sensing using data-driven reduced-order model 国際誌 査読有り

    T Nagata, K Nakai, K Yamada, Y Saito, T Nonomura, M Kano, S Ito, H Nagao

    Geophysical Journal International 233 (1) 33-50 2023年4月

    出版者・発行元:Oxford University Press (OUP)

    DOI: 10.1093/gji/ggac443  

    ISSN:0956-540X

    eISSN:1365-246X

  9. Nondominated-Solution-Based Multi-Objective Greedy Sensor Selection for Optimal Design of Experiments 国際誌 査読有り

    Kumi Nakai, Yasuo Sasaki, Takayuki Nagata, Keigo Yamada, Yuji Saito, Taku Nonomura

    IEEE Transactions on Signal Processing 70 5694-5707 2022年12月

    出版者・発行元:Institute of Electrical and Electronics Engineers (IEEE)

    DOI: 10.1109/tsp.2022.3224643  

    ISSN:1053-587X

    eISSN:1941-0476

  10. Simultaneous measurement of pressure and temperature on the same surface by sensitive paints using the sensor selection method 国際誌 国際共著 査読有り

    Neetu Tiwari, Kazuki Uchida, Ryoma Inoba, Yuji Saito, Keisuke Asai, Taku Nonomura

    Experiments in Fluids 63 (11) 2022年11月

    出版者・発行元:Springer Science and Business Media LLC

    DOI: 10.1007/s00348-022-03501-x  

    ISSN:0723-4864

    eISSN:1432-1114

  11. Data-Driven Sensor Selection Method Based on Proximal Optimization for High-Dimensional Data With Correlated Measurement Noise 国際誌 査読有り

    Takayuki Nagata, Keigo Yamada, Taku Nonomura, Kumi Nakai, Yuji Saito, Shunsuke Ono

    IEEE Transactions on Signal Processing 70 1-13 2022年10月

    出版者・発行元:None

    DOI: 10.1109/tsp.2022.3212150  

    ISSN:1053-587X

    eISSN:1941-0476

  12. Proof-of-concept study of sparse processing particle image velocimetry for real time flow observation 国際誌 査読有り

    Naoki Kanda, Chihaya Abe, Shintaro Goto, Keigo Yamada, Kumi Nakai, Yuji Saito, Keisuke Asai, Taku Nonomura

    Experiments in Fluids 63 (9) 2022年9月

    出版者・発行元:Springer Science and Business Media LLC

    DOI: 10.1007/s00348-022-03471-0  

    ISSN:0723-4864

    eISSN:1432-1114

  13. Feasibility Study of Controlling Supersonic Boundary-layer Flows Using Jets Flapping at Several Tens of Kilohertz 査読有り

    Rui AOKI, Ikuhiro FUJIMURA, Taro HANDA, Chungil LEE, Yuta OZAWA, Yuji SAITO, Taku NONOMURA, Keisuke ASAI

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 65 (5) 221-229 2022年9月

    出版者・発行元:Japan Society for Aeronautical and Space Sciences

    DOI: 10.2322/tjsass.65.221  

    ISSN:0549-3811

    eISSN:2189-4205

  14. Optimal gate selection method for simultaneous lifetime-based measurement of PSP and TSP 国際誌 査読有り

    Miku Kasai, Takayuki Nagata, Taku Nonomura, Yuji Saito, Keisuke Asai

    Measurement Science and Technology 33 (9) 095203-095203 2022年9月1日

    出版者・発行元:None

    DOI: 10.1088/1361-6501/ac769b  

    ISSN:0957-0233

    eISSN:1361-6501

  15. Optimization of sparse sensor placement for estimation of wind direction and surface pressure distribution using time-averaged pressure-sensitive paint data on automobile model 査読有り

    Ryoma Inoba, Kazuki Uchida, Yuto Iwasaki, Takayuki Nagata, Yuta Ozawa, Yuji Saito, Taku Nonomura, Keisuke Asai

    Journal of Wind Engineering and Industrial Aerodynamics 227 105043-105043 2022年8月

    出版者・発行元:Elsevier BV

    DOI: 10.1016/j.jweia.2022.105043  

    ISSN:0167-6105

  16. Evaluation of Optimization Algorithms and Noise Robustness of Sparsity-Promoting Dynamic Mode Decomposition 国際誌 査読有り

    Yuto Iwasaki, Taku Nonomura, Kumi Nakai, Takayuki Nagata, Yuji Saito, Keisuke Asai

    IEEE Access 10 80748-80763 2022年7月

    出版者・発行元:Institute of Electrical and Electronics Engineers (IEEE)

    DOI: 10.1109/access.2022.3193157  

    eISSN:2169-3536

  17. Greedy Sensor Selection for Weighted Linear Least Squares Estimation Under Correlated Noise 国際誌 査読有り

    Keigo Yamada, Yuji Saito, Taku Nonomura, Keisuke Asai

    IEEE Access 10 79356-79364 2022年7月

    出版者・発行元:Institute of Electrical and Electronics Engineers (IEEE)

    DOI: 10.1109/access.2022.3194250  

    eISSN:2169-3536

  18. Time-resolved particle image velocimetry and pressure sensitive paint measurements of afterbody flow dynamics 国際共著 査読有り

    Fernando Zigunov, Prabu Sellappan, Farrukh Alvi, Yuta Ozawa, Yuji Saito, Taku Nonomura, Keisuke Asai

    Physical Review Fluids 7 (2) 2022年2月1日

    出版者・発行元:American Physical Society (APS)

    DOI: 10.1103/physrevfluids.7.024701  

    eISSN:2469-990X

  19. Single-pixel correlation applied to background-oriented schlieren measurement 国際誌 査読有り

    Hikaru Sugisaki, Chungil Lee, Yuta Ozawa, Kumi Nakai, Yuji Saito, Taku Nonomura, Keisuke Asai, Yu Matsuda

    Experiments in Fluids 63 (1) 2022年1月

    出版者・発行元:Springer Science and Business Media LLC

    DOI: 10.1007/s00348-021-03373-7  

    ISSN:0723-4864

    eISSN:1432-1114

  20. Aeroacoustic Fields of Supersonic Twin Jets at the Ideally Expanded Condition 査読有り

    Yuta OZAWA, Taku NONOMURA, Yuji SAITO, Keisuke ASAI

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 64 (6) 312-324 2021年11月4日

    出版者・発行元:None

    DOI: 10.2322/tjsass.64.312  

    ISSN:0549-3811

    eISSN:2189-4205

  21. Proposal and verification of optical flow reformulation based on variational method for skin-friction-stress field estimation from unsteady oil film distribution 査読有り

    Kanta Endo, Takumi Ambo, Yuji Saito, Taku Nonomura, Lin Chen, Keisuke Asai

    Journal of Visualization 25 (2) 263-280 2021年9月28日

    出版者・発行元:None

    DOI: 10.1007/s12650-021-00794-8  

    ISSN:1343-8875

    eISSN:1875-8975

  22. Fast greedy optimization of sensor selection in measurement with correlated noise 査読有り

    Keigo Yamada, Yuji Saito, Koki Nankai, Taku Nonomura, Keisuke Asai, Daisuke Tsubakino

    Mechanical Systems and Signal Processing 158 107619-107619 2021年9月

    出版者・発行元:None

    DOI: 10.1016/j.ymssp.2021.107619  

    ISSN:0888-3270

    eISSN:1096-1216

  23. Data-Driven Determinant-Based Greedy Under/Oversampling Vector Sensor Placement 国際誌 査読有り

    Yuji Saito, Keigo Yamada, Naoki Kanda, Kumi Nakai, Takayuki Nagata, Taku Nonomura, Keisuke Asai

    Computer Modeling in Engineering & Sciences 129 (1) 1-30 2021年8月

    出版者・発行元:Computers, Materials and Continua (Tech Science Press)

    DOI: 10.32604/cmes.2021.016603  

    ISSN:1526-1506

    eISSN:1526-1506

  24. Feasibility Study on Real-time Observation of Flow Velocity Field using Sparse Processing Particle Image Velocimetry 査読有り

    Naoki KANDA, Kumi NAKAI, Yuji SAITO, Taku NONOMURA, Keisuke ASAI

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 64 (4) 242-245 2021年7月4日

    出版者・発行元:None

    DOI: 10.2322/tjsass.64.242  

    ISSN:0549-3811

    eISSN:2189-4205

  25. Data-Driven Sparse Sensor Selection Based on A-Optimal Design of Experiment With ADMM 査読有り

    Takayuki Nagata, Taku Nonomura, Kumi Nakai, Keigo Yamada, Yuji Saito, Shunsuke Ono

    IEEE Sensors Journal 21 (13) 15248-15257 2021年7月1日

    出版者・発行元:None

    DOI: 10.1109/jsen.2021.3073978  

    ISSN:1530-437X

    eISSN:2379-9153

  26. Analysis of transonic buffet on ONERA-M4 model with unsteady pressure-sensitive paint 査読有り

    Kazuki Uchida, Yosuke Sugioka, Miku Kasai, Yuji Saito, Taku Nonomura, Keisuke Asai, Kazuyuki Nakakita, Yusuke Nishizaki, Yoshiyuki Shibata, Seiichi Sonoda

    Experiments in Fluids 62 (6) 2021年6月

    出版者・発行元:None

    DOI: 10.1007/s00348-021-03228-1  

    ISSN:0723-4864

    eISSN:1432-1114

  27. Data-Driven Sparse Sampling for Reconstruction of Acoustic-Wave Characteristics Used in Aeroacoustic Beamforming 査読有り

    Sayumi Kaneko, Yuta Ozawa, Kumi Nakai, Yuji Saito, Taku Nonomura, Keisuke Asai, Hiroki Ura

    Applied Sciences 11 (9) 4216-4216 2021年5月6日

    出版者・発行元:None

    DOI: 10.3390/app11094216  

    eISSN:2076-3417

  28. Determinant-Based Fast Greedy Sensor Selection Algorithm 査読有り

    Yuji Saito, Taku Nonomura, Keigo Yamada, Kumi Nakai, Takayuki Nagata, Keisuke Asai, Yasuo Sasaki, Daisuke Tsubakino

    IEEE Access 9 68535-68551 2021年4月

    出版者・発行元:None

    DOI: 10.1109/access.2021.3076186  

    eISSN:2169-3536

  29. Effect of Objective Function on Data-Driven Greedy Sparse Sensor Optimization 査読有り

    Kumi Nakai, Keigo Yamada, Takayuki Nagata, Yuji Saito, Taku Nonomura

    IEEE Access 9 46731-46743 2021年3月

    出版者・発行元:None

    DOI: 10.1109/access.2021.3067712  

    ISSN:2169-3536

    eISSN:2169-3536

  30. Effect of Oxygen Mole Fraction on Static Properties of Pressure-Sensitive Paint 査読有り

    Tomohiro Okudera, Takayuki Nagata, Miku Kasai, Yuji Saito, Taku Nonomura, Keisuke Asai

    21 (4) 1062-1062 2021年2月4日

    出版者・発行元:None

    DOI: 10.3390/s21041062  

    eISSN:1424-8220

  31. Randomized Subspace Newton Convex Method Applied to Data-Driven Sensor Selection Problem 査読有り

    Taku Nonomura, Shunsuke Ono, Kumi Nakai, Yuji Saito

    IEEE Signal Processing Letters 28 284-288 2021年1月

    出版者・発行元:None

    DOI: 10.1109/lsp.2021.3050708  

    ISSN:1070-9908

    eISSN:1558-2361

  32. Stabilized combustion of circular fuel duct with liquid oxygen 査読有り

    Ayumu Tsuji, Yuji Saito, Landon Kamps, Masashi Wakita, Harunori Nagata

    Proceedings of the Combustion Institute 38 (3) 4845-4855 2020年7月

    出版者・発行元:Elsevier BV

    DOI: 10.1016/j.proci.2020.07.001  

    ISSN:1540-7489

  33. Data-Driven Vector-Measurement-Sensor Selection Based on Greedy Algorithm 査読有り

    Yuji Saito, Taku Nonomura, Koki Nankai, Keigo Yamada, Keisuke Asai, Yasuo Sasaki, Daisuke Tsubakino

    IEEE Sensors Letters 4 (7) 1-4 2020年7月

    出版者・発行元:Institute of Electrical and Electronics Engineers (IEEE)

    DOI: 10.1109/lsens.2020.2999186  

    eISSN:2475-1472

  34. Investigation of Graphite Nozzle Erosion in Hybrid Rockets Using Oxygen/High-Density Polyethylene

    Landon Kamps, Shota Hirai, Kazuhito Sakurai, Tor Viscor, Yuji Saito, Raymond Guan, Hikaru Isochi, Naoto Adachi, Mitsunori Itoh, Harunori Nagata

    Journal of Propulsion and Power 36 (3) 423-434 2020年5月

    出版者・発行元:American Institute of Aeronautics and Astronautics (AIAA)

    DOI: 10.2514/1.b37568  

    eISSN:1533-3876

  35. Mission to Earth–Moon Lagrange Point by a 6U CubeSat: EQUULEUS 査読有り

    Ryu Funase, Satoshi Ikari, Kota Miyoshi, Yosuke Kawabata, Shintaro Nakajima, Shunichiro Nomura, Nobuhiro Funabiki, Akihiro Ishikawa, Kota Kakihara, Shuhei Matsushita, Ryohei Takahashi, Kanta Yanagida, Daiko Mori, Yusuke Murata, Toshihiro Shibukawa, Ryo Suzumoto, Masahiro Fujiwara, Kento Tomita, Hiroki Aohama, Keidai Iiyama, Sho Ishiwata, Hirotaka Kondo, Wataru Mikuriya, Hiroto Seki, Hiroyuki Koizumi, Jun Asakawa, Keita Nishii, Akihiro Hattori, Yuji Saito, Kosei Kikuchi, Yuta Kobayashi, Atsushi Tomiki, Wataru Torii, Taichi Ito, Stefano Campagnola, Naoya Ozaki, Nicola Baresi, Ichiro Yoshikawa, Kazuo Yoshioka, Masaki Kuwabara, Reina Hikida, Shogo Arao, Shinsuke Abe, Masahisa Yanagisawa, Ryota Fuse, Yosuke Masuda, Hajime Yano, Takayuki Hirai, Kazuyoshi Arai, Ritsuko Jitsukawa, Eigo Ishioka, Haruki Nakano, Toshinori Ikenaga, Tatsuaki Hashimoto

    IEEE Aerospace and Electronic Systems Magazine 35 (3) 30-44 2020年3月1日

    出版者・発行元:None

    DOI: 10.1109/maes.2019.2955577  

    ISSN:0885-8985

    eISSN:1557-959X

  36. Experimental Investigation of the Continuous Transition of Flame-Spreading near the Blow-Off Limit 査読有り

    K. Komizu, Y. Saito, A. Tsuji, H. Nagata

    Journal of Combustion 2020 2020年2月

    DOI: 10.1155/2020/3187694  

    ISSN:2090-1968

    eISSN:2090-1976

  37. Investigation of Graphite Nozzle Erosion in Hybrid Rockets Using O2/HDPE 査読有り

    Landon Kamps, , Shota Hirai, Kazuhito Sakurai, Tor Viscor, Yuji Saito, Raymond Guan, Hikaru Isochi, Naoto Adachi, Mitsunori Itoh, Harunori Nagata

    Journal of Propulsion and Power 2020年

    DOI: 10.2514/6.2019-4264  

  38. Data-driven Vector-measurement-sensor Selection based on Greedy Algorithm for Particle-image-velocimetry Measurement

    Yuji Saito, Taku Nonomura, Koki Nankai, Keisuke Asai, Yasuo Sasaki, Daisuke Tsubakino

    arXiv 2019年5月

    詳細を見る 詳細を閉じる

    A reduced-order modelling for fluid analysis and flow control gathers a lot of attentions. With regard to reduced order modelling, proper orthogonal decomposition (POD) is one of the effective methods to decompose the high-dimension fluid data into several significant mode of flow fields. Previous studies show that the limited sensor placed at appropriate positions gives us the approximated full state information. In this study, the extension of the vector-measurement sensor selection of the greedy algorithm was conducted in addition to that of convex approximation. This applied to test and PIV data to reconstruct the full state based on the information given by the sparse vector-measurement sensors.

  39. Comprehensive Data Reduction for N2O/HDPE Hybrid Rocket Motor Performance Evaluation 査読有り

    Landon Kamps, Kazuhito Sakurai, Yuji Saito, Harunori Nagata

    AEROSPACE 6 (4) 2019年4月

    出版者・発行元:MDPI

    DOI: 10.3390/aerospace6040045  

    ISSN:2226-4310

    eISSN:2226-4310

    詳細を見る 詳細を閉じる

    Static firing tests of a hybrid rocket motor using liquid nitrous oxide (N2O) as the oxidizer and high-density polyethylene (HPDE) as the fuel are analyzed using a novel approach to data reduction that allows histories for fuel mass consumption, nozzle throat erosion, characteristic exhaust velocity (c) efficiency, and nozzle throat wall temperature to be determined experimentally. This is done by firing a motor under the same conditions six times, varying only the burn time. Results show that fuel mass consumption was nearly perfectly repeatable, whereas the magnitude and timing of nozzle throat erosion was not. Correlations of the fuel regression rate result in oxidizer port mass flux exponents of 0.62 and 0.76. There is a transient time in the c efficiency histories of around 2.5 s, after which c efficiency remains relatively constant, even in the case of excessive nozzle throat erosion. Although nozzle erosion was not repeatable, the erosion onset factors were similar between tests, and greater than values in previous research in which oxygen was used as the oxidizer. Lastly, nozzle erosion rates exceed 0.15 mm/s for chamber pressures of 4 to 5 MPa.

  40. 端面燃焼式ハイブリッドロケットの推力制御時におけるヒステリシス特性に関する研究 査読有り

    君野 正弥, 齋藤 勇士, 奥谷 勇士, 津地 歩, 添田 建太郎, 永田 晴紀

    日本航空宇宙学会論文集 67 (4) 119-125 2019年

    出版者・発行元:一般社団法人 日本航空宇宙学会

    DOI: 10.2322/jjsass.67.119  

    ISSN:1344-6460

    詳細を見る 詳細を閉じる

    <p>In this study, the authors conduced ten firings to investigate a hysteresis characteristics in Axial-Injection End-Burning hybrid rockets under throttling operation. Oxidizer mass flow rate and chamber pressure were throttled by two methods, actuating valves in a fluid circuit consisting of two oxidizer supply lines and a motor controlling. Chamber pressure and oxidizer mass flow rate were measured during each firing. The results show that two types of hysteresis characteristics were observed when throttling operation is repeated. One is a hysteresis with respect to increase and decrease of the oxidizer mass flow rate. Another is a hysteresis for the cycle. It is considered that the former hysteresis has the influence of a chamber pressure response time. In addition, the latter hysteresis is not necessarily observed even in the same chamber pressure region. </p>

  41. 端面燃焼式ハイブリッドロケットの燃焼機構の解明

    齋藤 勇士

    北海道大学 2018年3月

    DOI: 10.14943/doctoral.k13203  

  42. Investigation of Throttling Response Characteristics of Axial-Injection End-Burning Hybrid Rockets 査読有り

    Yuji SAITO, Masaya KIMINO, Ayumu TSUJI, Kazunobu OMURA, Hiroyuki YASUKOCHI, Kentaro SOEDA, Tsuyoshi TOTANI, Masashi WAKITA, Harunori NAGATA

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 16 (1) 9-18 2018年

    DOI: 10.2322/tastj.16.9  

  43. Method for Determining Nozzle-Throat-Erosion History in Hybrid Rockets 査読有り

    Landon Kamps, Yuji Saito, Ryosuke Kawabata, Masashi Wakita, Tsuyoshi Totani, Yusuke Takahashi, Harunori Nagata

    JOURNAL OF PROPULSION AND POWER 33 (6) 1369-1377 2017年11月

    出版者・発行元:AMER INST AERONAUTICS ASTRONAUTICS

    DOI: 10.2514/1.B36390  

    ISSN:0748-4658

    eISSN:1533-3876

    詳細を見る 詳細を閉じる

    The authors of this paper introduce a new reconstruction technique titled nozzle-throat reconstruction technique to estimate nozzle-throat-erosion history and oxidizer-to-fuel-mass-ratio history in hybrid rockets. Nine static-firing tests were carried out on a 2kN-class cascaded multistage impinging-jet-type hybrid-rocket motor under varying oxidizer-flow rates to evaluate the accuracy of reconstructed results. Nozzle-throat-erosion histories calculated by the nozzle-throat reconstruction technique agreed well with measured values for initial nozzle-throat radius, and successfully reconstructed the case, in which no measurable amount of nozzle-throat erosion occurred. For equivalence ratios 0.6-1.4, the relationship between nozzle-throat-erosion rate and equivalence ratio of reconstructed results displays a trend consistent with chemical-kinetic-limited heterogeneous-combustion theory, as well as predictions made by previous researchers.

  44. Verification Firings of End-Burning Type Hybrid Rockets 査読有り

    Harunori Nagata, Hayato Teraki, Yuji Saito, Ryuichiro Kanai, Hiroyuki Yasukochi, Masashi Wakita, Tsuyoshi Totani

    JOURNAL OF PROPULSION AND POWER 33 (6) 1473-1477 2017年11月

    出版者・発行元:AMER INST AERONAUTICS ASTRONAUTICS

    DOI: 10.2514/1.B36359  

    ISSN:0748-4658

    eISSN:1533-3876

    詳細を見る 詳細を閉じる

    The authors have previously proposed the concept of end-burning-type hybrid rockets, which would use cylindrical fuel grains consisting of an array of many small ports running in the axial direction, through which oxidizer gas would flow. Because of difficulty in manufacturing a fuel grain that satisfied requirements such as high volumetric filling rate (above 0.95) and microsized port intervals, the end-burning hybrid rocket had yet to be achieved. This paper reports the results of verification firing tests of a novel end-burning-type hybrid rocket made possible for the first time by recent progress in three-dimensional printing technology. The results clearly distinguish the initial transient and steady periods of the end-burning mode and prove that no oxidizer-to-fuel ratio shift occurs during firing. Because the initial transient is a period for the exit end face to attain a steady-state shape, an initial end-face shape being close to the steady-state shape can shorten this period. A firing test with fuel having tapered ports is shown to attain a steady-state shape in less than 1s, which is much shorter than the nontapered case of about 6 s.

  45. Investigation of axial-injection end-burning hybrid rocket motor regression 査読有り

    Yuji Saito, Toshiki Yokoi, Lukas Neumann, Hiroyuki Yasukochi, Kentaro Soeda, Tsuyoshi Totani, Masashi Wakita, Harunori Nagata

    ADVANCES IN AIRCRAFT AND SPACECRAFT SCIENCE 4 (3) 281-296 2017年5月

    出版者・発行元:TECHNO-PRESS

    DOI: 10.12989/aas.2017.4.3.281  

    ISSN:2287-528X

    eISSN:2287-5271

    詳細を見る 詳細を閉じる

    The axial-injection end-burning hybrid rocket proposed twenty years ago by the authors recently recaptured the attention of researchers for its virtues such as no xi (oxidizer to fuel mass ratio) shift during firing and good throttling characteristics. This paper is the first report verifying these virtues using a laboratory scale motor. There are several requirements for realizing this type of hybrid rocket: 1) high fuel filling rate for obtaining an optimal xi ; 2) small port intervals for increasing port merging rate; 3) ports arrayed across the entire fuel section. Because these requirements could not be satisfied by common manufacturing methods, no previous researchers have conducted experiments with this kind of hybrid rocket. Recent advances in high accuracy 3D printing now allow for fuel to be produced that meets these three requirements. The fuel grains used in this study were produced by a high precision light polymerized 3D printer. Each grain consisted of an array of 0.3 mm diameter ports for a fuel filling rate of 98%. The authors conducted several firing tests with various oxidizer mass flow rates and chamber pressures, and analysed the results, including xi history, using a new reconstruction technique. The results show that xi remains almost constant throughout tests of varying oxidizer mass flow rates, and that regression rate in the axial direction is a nearly linear function of chamber pressure with a pressure exponent of 0.996.

  46. 端面燃焼式ハイブリッドロケットの推力制御特性に関する研究 査読有り

    齋藤 勇士, 横井 俊希, 津地 歩, 尾村 和信, 安河内 裕之, 添田 建太郎, 戸谷 剛, 脇田 督司, 永田 晴紀

    日本航空宇宙学会論文集 65 (4) 157-167 2017年

    出版者・発行元:一般社団法人 日本航空宇宙学会

    DOI: 10.2322/jjsass.65.157  

    ISSN:1344-6460

    詳細を見る 詳細を閉じる

    In this study, the authors conducted twice experiments to verify the throttling characteristics of axial-injection end-burning hybrid rockets. Oxidizer mass flow rate and chamber pressure were throttled by actuating valves in a fluid circuit consisting of two oxidizer supply lines. Chamber pressure and oxidizer mass flow rate were measured during each firing. The results show that oxidizer to fuel ratio remains constant for similar values of oxidizer mass flow rate. However, two weak points were identified in these throttling firing tests. First, a pressure transient was observed when oxidizer mass flow rate was increased (turn-up operation). The pressure transient consisted of two distinguishable first order lags, a fast lag followed by a slow lag, which are treated by separate curve fitting functions. The fast response is explained by a thermal lag in the solid fuel, whereas the slow response requires further inquiry. Second, the chamber pressure history exhibited hysteresis characteristics of oxidizer mass flow rate due to the increasing fuel regression rate. Therefore, in the throttling tests where oxidizer flow rate was turned-up and returned to the initial condition twice back-to-back, the chamber pressure history was higher in the second iteration than in the first.

  47. Estimation of Hybrid Rocket Nozzle Throat Erosion History 査読有り

    Yuji SAITO, Tsutomu UEMATSU, Hikaru ISOCHI, Masashi WAKITA, Tsuyoshi TOTANI, Harunori NAGATA

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 14 (ists30) Pa_145-Pa_151 2016年

    DOI: 10.2322/tastj.14.Pa_145  

︎全件表示 ︎最初の5件までを表示

MISC 10

  1. データ駆動型スパースセンシングによる航空宇宙開発の飛躍 招待有り

    齋藤勇士

    日本ロボット学会誌 41 (8) 665-668 2023年10月25日

    DOI: 10.7210/jrsj.41.665  

  2. Development of Hybrid Thruster Ignition System with Low-Toxicity Fuel and Catalytic Reaction 国際誌

    Yuji Saito, Alejandro Taiki, Padilla Torres, Ikeda Hirohide, Taiichi Nagata, Yoshiki Matsuura, Shinji Igarashi, Hironori Chiba, Kosuke Kida, Toshinori Kuwahara

    Proceedings of the 74th International Astronautical Congress IAC-23,C4,4,11,x79623 2023年10月

  3. データ駆動型スパースセンシングのためのセンサ位置最適化

    齋藤 勇士, 野々村 拓, 浅井 圭介

    計測と制御 59 (8) 559-564 2020年8月

    DOI: 10.11499/sicejl.59.559  

  4. ラボスケール端面燃焼式ハイブリッドロケットの点火装置の模索

    齋藤 勇士

    日本航空宇宙学会誌 68 (2) 31-31 2020年2月5日

    DOI: 10.14822/kjsass.68.2_31  

  5. Investigation of graphite nozzle erosion in hybrid rockets using o2/c2h4

    Landon Kamps, Shota Hirai, Kazuhito Sakurai, Tor Viscor, Yuji Saito, Raymond Guan, Hikaru Isochi, Naoto Adachi, Mitsunori Itoh, Harunori Nagata

    2018 Joint Propulsion Conference 2018年1月1日

    DOI: 10.2514/6.2018-4531  

    詳細を見る 詳細を閉じる

    © 2018 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. A recently developed reconstruction technique titled nozzle-throat reconstruction technique is used to investigate graphite nozzle-throat-erosion in two scales of hybrid rocket motors, 30N-thrust class and 2000N-thrust class, using oxygen as the oxidizer and high density polyethylene as the fuel. Thirty seven static firing tests were conducted under varying experimental conditions to confirm the validity of the reconstruction technique results, investigate the conditions at the onset of erosion and to formulate an empirical predictive model of nozzle erosion rate. Results show that nozzle erosion increases the convective heat transfer coefficient to upwards of 2-4 times the value predicted by Bartz correlation. Furthermore, an empirical model is introduced that treats the combustion gas as a single oxidizing agent with heterogeneous rate constants that are distributions of equivalence ratio of the bulk fluid flow. This empirical model predicts the nozzle throat erosion histories in multiple tests to within ± 5%.

  6. The accuracy of reconstruction techniques for determining hybrid rocket fuel regression rate

    Yuji Saito, Landon Kamps, Kodai Komizu, Kentaro Soeda, Daniele Bianchi, Francesco Nasuti, Harunori Nagata

    2018 Joint Propulsion Conference 2018年1月1日

    DOI: 10.2514/6.2018-4923  

    詳細を見る 詳細を閉じる

    © 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. This study is an investigation of the accuracy of reconstruction techniques for determining instantaneous fuel regression rate. Results of reconstruction techniques are compared with results obtained through the measurement of the pressure drop across the fuel in an Axial-Injection End-Burning hybrid rocket (EBHR). The results of numerous firing tests show that this method allows for the evaluation of the accuracy of the instantaneous fuel regression rates obtained by reconstruction techniques. The error bias of O/F values calculated by the reconstruction techniques were around ±10%, and were mainly caused by uncertainties in the measured values of oxidizer mass flowrate and the definition of firing duration. The instantaneous length of an EBHR-type fuel can be calculated from the measurement of the pressure drop across the fuel. However, the calculated fuel length history obtained by the pressure drop in a port does not coincide with that obtained by the reconstruction technique because of an underestimation in pressure drop.

  7. 端面燃焼式ハイブリッドロケットの超小型衛星への応用

    齋藤 勇士, 君野 正弥, 添田 建太郎, 戸谷 剛, 永田 晴紀

    日本航空宇宙学会誌 66 (10) 291-295 2018年

    出版者・発行元:一般社団法人 日本航空宇宙学会

    DOI: 10.14822/kjsass.66.10_291  

    ISSN:0021-4663

    詳細を見る 詳細を閉じる

    <p>超小型衛星の運用の高機能化および深宇宙探査には,推進器がますます不可欠な存在となる.化学エネルギを用いて大推力を得ることのできる化学ロケットは数km/sの増速が与えられるキックモータになる.主衛星に相乗りする形で打ち上げられる超小型衛星には厳格な安全基準が求められるため,プラスチック等を燃料とするハイブリッドロケットが注目を浴びている.その中でも,端面燃焼式ハイブリッドロケットは,従来型ハイブリッドロケットを凌駕する燃焼特性および推力制御特性が期待されてきた.端面燃焼式ハイブリッドロケットは,燃料製作に困難さを有していたが,高精度3Dプリンタの台頭によって,2014年に実証に成功した.これまでの間,筆者らは数多くの燃焼実験を実施し,研究成果を国内外の学会で発表してきた.本論文では今まで得られた端面燃焼式ハイブリッドロケットの知見をまとめ,今後の課題を紹介する.</p>

  8. Investigation of regression characteristics under relatively high-pressure in Axial-injection End-Burning Hybrid Rockets

    Yuji Saito, Masaya Kimino, Tsuji Ayumu, Yushi Okutani, Kazunobu Omura, Hiroyuki Yasukochi, Kentaro Soeda, Tsuyoshi Totani, Masashi Wakita, Harunori Nagata

    53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017 2017年1月1日

    詳細を見る 詳細を閉じる

    This study is an investigation of Axial-Inection End-Burning Hybrid Rockets aimed at revealing fuel regression characteristics under relatively high pressure conditions. Firing tests were conducted using gaseous oxygen as oxidizer at chamber pressures and oxidizer port velocities ranging from 0.22 MPa to 1.05 MPa and 31 m/s to 103 m/s, respectively. The results of fifteen static firing tests show that fuel regression rate increases as the chamber pressure increases, and regression rates ranged from approximately 1.1 mm/s at 0.25 MPa to 5.4 mm/s at 0.71 MPa. Furthermore, it is observed that the fuel regression rate is not influenced by oxidizer port velocity. The athours encountered a problem refered to as backfiring in this paper, and developed a calculation model to investigate this problemanalytically. The calculation model explains why the back-firing problem tends to occur in relatively high-pressure conditions, and leads to the conclusion that increasing nozzle throat diameter is an effective means of preventing back-firing from occuring.

  9. Experimental and analytical investigation of effect of pressure on regression rate of axial-injection end-burning hybrid rockets

    Yuji Saito, Toshiki Yokoi, Harunori Nagata, Hiroyuki Yasukochi, Kentaro Soeda, Tsuyoshi Totani, Masashi Wakita

    52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016 47 9p 2016年1月1日

    出版者・発行元:日本航空宇宙学会

    詳細を見る 詳細を閉じる

    © 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. The regression characteristics of axial-injection end-burning hybrid rocket (EBHR) fuels having numerous small ports were experimentally investigated for the first time using a laboratory scale motor. In this paper, three requirements for EBHR fuel grains are explained in detail. High accuracy 3D printing allows for the production of fuel that satisfies the requirements for EBHR as defined in this paper. A data reduction method that overcomes the problem of multiple solutions to the c* equation is used to determine fuel regression rate with less than 10% error. Results of fifteen static firings tests show that fuel regression rate increases as the chamber pressure increases, which agrees with the trend revealed in previous studies (pressure exponent n is close to unity). No difference in combustion characteristics was found by comparing results of multi-port and single port fuel firing tests conducted in this and previous studies. A fuel regression model based on the Granular Diffusion Flame (GDF) model and Matthew and Frederick’s method is developed to investigate regression characteristics. Results calculated with this model agree with experimentally observed values, as well as the results calculated by Matthew and Frederick. However, this does hold true in tests with varying oxidizer port velocity. A GDF model only takes into account solid propellant regression, neglecting the effects of oxidizer velocity, and is shown in this study to be inappropriate for evaluating EBHR regression characteristics.

  10. Verification of the throttling characteristics of axial-injection end-burning type hybrid rockets

    Yuji Saito, Toshiki Yokoi, Hiroyuki Yasukochi, Kentaro Soeda, Tsuyoshi Totani, Masashi Wakita, Harunori Nagata

    Proceedings of the International Astronautical Congress, IAC 2016 S1920202 2016年1月1日

    出版者・発行元:一般社団法人 日本機械学会

    DOI: 10.1299/jsmemecj.2016.s1920202  

    ISSN:0074-1795

    eISSN:2424-2667

    詳細を見る 詳細を閉じる

    Copyright © 2016 by the International Astronautical Federation (IAF). All rights reserved. The axial-injection end-burning type hybrid rocket originally proposed twenty years ago by Nagata and Hashimoto et al. recently recaptured the attention of researchers for its virtues such as constant ξ (oxidizer to fuel mass ratio) during firing and throttling operations. Previous studies revealed that, for combustion in a single-port fuel grain, the end-face regression rate in the axial direction is proportional to pressure, with a pressure exponent of 0.95. Accordingly, these rockets were expected to display good throttling characteristics. Given that no ξ shift occurs, keeping the oxidizer mass flow rate within 1% of its initial design point ensures specific impulse will remain within 97% of its design point. There are several requirements for realizing this type of hybrid rocket: 1) high fuel filling rate for obtaining an optimal ξ 2) small port intervals for increasing port merging rate; 3) ports arrayed across the entire fuel section. Because common manufacturing methods were unable to produce a fuel that satisfied these requirements, no previous researchers have conducted experiments with this kind of hybrid rocket. Recent advances in high-accuracy 3D printing have enabled such fuels to be produced for the first time. The fuel grains used in this study were produced by a high-precision light polymerized 3D printer. Each grain consisted of an array of 0.3 mm diameter ports for a fuel filling rate of 98%. Last year, the authors reported the results of multiple firing tests of an axial-injection end-burning type hybrid rocket using 3D printed fuel grains and verified that solid fuel regression rate is linearly dependent on pressure. In this study, the authors conducted a unique set of experiments to verify the throttling characteristics of the axial-injection end-burning type hybrid rocket. Oxidizer mass flow rate and chamber pressure were throttled during firings by actuating valves in a fluid circuit consisting of four oxidizer supply lines. Chamber pressure and oxidizer mass flow rate were measured during each firing. These experimental data were analyzed by a reconstruction technique to obtain ξ history. The results show that ξ remains almost constant during firing, even during throttling operations. Therefore, this study verifies that the axial-injection end-burning type hybrid rocket has superb throttling characteristics. Additionally, the study supports findings in previous research that indicate the pressure exponent is close to unity.

︎全件表示 ︎最初の5件までを表示

講演・口頭発表等 53

  1. 燃料後退を伴う固体燃料上を燃え拡がる拡散火炎を計算可能とするコード開発

    齋藤勇士, 森井雄飛

    第61回燃焼シンポジウム 2023年11月17日

  2. Reconstruction Technique for Hybrid Rocket Fuel Regression towards Overcoming Multiple Solutions 国際会議

    Alejandro Taiki, Padilla Torres, Yuji Saito, Toshinori Kuwahara

    Twentieth International Conference on Flow Dynamic 2023年11月7日

  3. Development of Hybrid Thruster Ignition System with Low-Toxicity Fuel and Catalytic Reaction 国際会議

    Yuji Saito, Alejandro Taiki, Padilla Torres, Ikeda Hirohide, Taiichi Nagata, Yoshiki Matsuura, Shinji Igarashi, Hironori Chiba, Kosuke Kida, Toshinori Kuwahara

    74th International Astronautical Congress 2023年10月4日

  4. Lunar Orbit Mission using Spatial-resolved Fuel Regression Rate of Hybrid Thrusters 国際会議

    Alejandro Taiki Padilla, Torres, Tomoya Takuma, Yuji Saito, Toshinori Kuwahara

    34th International Symposium on Space Technology and Science 2023年6月8日

  5. ダブルパルスシュリーレン計測画像に基づく遷音速域ベース流れの解析

    山田 圭吾, 杉崎 光, 本多 陽敬, 神田 直樹, 李 忠日, 齋藤 勇士, 小澤 雄太, 野々村 拓, 大山 聖

    第66回宇宙科学技術連合講演会 2022年11月4日

  6. 軸方向噴射端面燃焼型ハイブリッドロケット最適設計法の開発と強度可変酸化剤流旋回型との性能比較

    原口 徹, 金崎 雅博, 齋藤 勇士

    第66回宇宙科学技術連合講演会 2022年11月4日

  7. 小型回収カプセル技術実証衛星ELS-R100の再突入軌道の設計解析

    高岡 光希, 桒原 聡文, 藤田 伸哉, 佐藤 悠司, 齋藤 勇士, 斉藤 拓実, Alice Violaine Saletta

    第66回宇宙科学技術連合講演会 2022年11月3日

  8. Applying single-pixel ensemble correlation to process of calculating displacements in background oriented schlieren 国際会議

    Hikaru Sugisaki, Chungil Lee, Yuta Ozawa, Kumi Nakai, Yuji Saito, Taku Nonomura, Keisuke Asai, Yu Matsuda

    AIAA AVIATION 2022 Forum 2022年6月27日

  9. Optimizing Sparse Sensor Placement for Flow Field Estimation Using Time-Averaged Pressure-Sensitive Paint Data: Application to Ground Vehicle 国際会議

    Ryoma Inoba, Kazuki Uchida, Yuto Iwasaki, Takayuki Nagata, Yuta Ozawa, Yuji Saito, Taku Nonomura, Keisuke Asai

    AIAA AVIATION 2022 Forum 2022年6月27日

  10. 「塊状アルミニウム-水」ハイブリッド燃焼を用いた推進系の開発

    齋藤勇士, 小泉宏之, 浅川純

    JAXA 宇宙探査オープンイノベーションフォーラム 2022年1月21日

  11. 革新的宇宙輸送実現に向けた燃焼研究 招待有り

    齋藤勇士

    第8回東北大学若手アンサンブルワークショップ 2021年11月17日

  12. Reconstruction techniques for determining O/F in hybrid rockets

    Yuji Saito, Landon T. Kamps, Ayumu Tsuji, Harunori Nagata

    AIAA Propulsion and Energy 2021 Forum 2021年8月9日

  13. 観測ノイズを考慮したスパースセンサ位置最適化 招待有り

    齋藤勇士

    第1回設計と運用に活かすデータ同化研究会 2021年2月19日

  14. A new position and attitude measurement method for complex shape models with non-circular cross section in Magnetic Suspension and Balance System

    Masatoshi Horiguchi, Yuji Saito, Taku Nonomura, Keisuke Asai, Hideo Sawada, Yasfumi Konishi, Hiroyuki Okuizumi, Shigeru Obayashi

    AIAA Scitech 2021 Forum 2021年1月11日

  15. 寿命法感圧・感温塗料計測における最適ゲート選定法

    笠井美玖, 永田貴之, 野々村拓, 齋藤勇士, 浅井圭介

    可視化情報シンポジウム(CD-ROM) 2021年

  16. 自動車模型周りの時間平均感圧塗料データを用いた風向予測のためのスパースセンサ位置最適化

    井野塲遼馬, 内田和樹, 小澤雄太, 永田貴之, 齋藤勇士, 野々村拓, 浅井圭介

    流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 2021年

  17. Initial Firing Tests of Aluminum Rod/Water Hybrid Rockets

    Yuji Saito, Landon T. Kamps, Ayumu Tsuji, Masashi Wakita, Koizumi Hiroyuki, Keisuke Asai, Harunori Nagata

    AIAA Propulsion and Energy 2020 Forum 2020年8月24日

  18. データ駆動型スパースセンシングのためのセンサ位置最適化

    齋藤 勇士, 野々村 拓, 浅井 圭介

    計測と制御 2020年8月

  19. ハイブリッドロケットにおける燃焼データ解析手法の開発

    永田晴紀, KAMPS Landon, 齋藤勇士

    燃焼シンポジウム講演論文集(CD-ROM) 2020年

  20. 酸素濃度が感圧塗料の特性に与える影響の評価

    奥寺智弘, 永田貴之, 笠井美玖, 齋藤勇士, 野々村拓, 浅井圭介

    可視化情報シンポジウム(CD-ROM) 2020年

  21. 寿命法によるローターブレード表面の感圧・感温塗料計測

    笠井美玖, 小澤雄太, 齋藤勇士, 野々村拓, 浅井圭介

    可視化情報シンポジウム(CD-ROM) 2020年

  22. Feasibility Study on Sparse Processing Particle Image Velocimetry 国際会議

    Naoki Kanda, Koki Nankai, Yuji Saito, Taku Nonomura, Keisuke Asai

    72nd Annual Meeting of the APS Division of Fluid Dynamics 2019年11月26日

  23. Determinant based Fast Greedy Optimization on Sparse Sensor Selection 国際会議

    Yuji Saito, Keigo Yamada, Taku Nonomura, Keisuke Asai, Daisuke Tsubakino, Yasuo Sasaki

    72nd Annual Meeting of the APS Division of Fluid Dynamics 2019年11月25日

  24. Fast Greedy Optimization of Sensor Selection in Measurement with Correlated Noise 国際会議

    Keigo Yamada, Yuji Saito, Taku Nonomura, Keisuke Asai, Tomohiro Okudera

    72nd Annual Meeting of the APS Division of Fluid Dynamics 2019年11月25日

  25. Response Mechanisms in Axial-Injection End-Burning Hybrid Rockets 国際会議

    Yuji Saito, Ayumu Tsuji, Ai Yamada, Harunori Nagata

    AIAA Propulsion and Energy 2019 Forum 2019年8月

  26. 6UCubeSat:EQUULEUS推進システムAQUARIUSフライトモデルのシステムインテグレーション

    秋山茉莉子, 西井啓太, 菊池航世, 室原昌弥, WANG Qihang, 安宅泰穂, 齋藤勇士, 服部旭大, 浅川純, 小泉宏之, 柿原浩太, 柳田幹太, 鈴本遼, 飯山敬大, 船瀬龍, 小紫公也

    日本航空宇宙学会年会講演会講演集(CD-ROM) 2019年

  27. Flight Model Development of the Water Resistojet Propulsion System for Deep Space Exploration by the CubeSat: EQUULEUS 国際会議

    Asakawa, J, Nishii, K, Hattori, A, Koizumi, H, Saito, Y, Kikuchi, K, Akiyama, M, Wang, Q, Ataka, Y, Komurasaki, K

    69th International Astronautical Congress 2018年9月

  28. Investigation of Regression Rate under High-Pressure in Axial-Injection End-Burning Hybrid Rockets 国際会議

    Yushi Okutani, Yuji Saito, Masaya Kimino, Ayumu Tsuji, Kentaro Soeda, Harunori Nagata

    54th AIAA/SAE/ASEE Joint Propulsion Conference 2018年7月

  29. Investigation of Graphite Nozzle Erosion in Hybrid Rockets Using O2/C2H4 国際会議

    Landon Kamps, Shota Hirai, Kazuhito Sakurai, Tor Viscor, Yuji Saito, Raymond Guan, Hikaru Isochi, Naoto Adachi, Mitsunori Itoh, Harunori Nagata

    54th AIAA/SAE/ASEE Joint Propulsion Conference 2018年7月

  30. The Accuracy of Reconstruction Techniques for Determining Hybrid Rocket Fuel Regression Rate 国際会議

    Yuji Saito, Landon Kamps, Kodai Komizu, Kentaro Soeda, Daniele Bianchi, Francesco Nasuti, Harunori Nagata

    54th AIAA/SAE/ASEE Joint Propulsion Conference 2018年7月

  31. 水レジストジェットスラスタの気液分離部における蒸発への重力の影響

    服部旭大, 西井啓太, 浅川純, 齋藤勇士, 菊池航世, 小泉宏之, 小紫公也

    宇宙科学技術連合講演会講演集(CD-ROM) 2018年

  32. The accuracy of reconstruction techniques for determining hybrid rocket fuel regression rate

    Yuji Saito, Landon Kamps, Kodai Komizu, Kentaro Soeda, Daniele Bianchi, Francesco Nasuti, Harunori Nagata

    2018 Joint Propulsion Conference 2018年1月1日

    詳細を見る 詳細を閉じる

    © 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. This study is an investigation of the accuracy of reconstruction techniques for determining instantaneous fuel regression rate. Results of reconstruction techniques are compared with results obtained through the measurement of the pressure drop across the fuel in an Axial-Injection End-Burning hybrid rocket (EBHR). The results of numerous firing tests show that this method allows for the evaluation of the accuracy of the instantaneous fuel regression rates obtained by reconstruction techniques. The error bias of O/F values calculated by the reconstruction techniques were around ±10%, and were mainly caused by uncertainties in the measured values of oxidizer mass flowrate and the definition of firing duration. The instantaneous length of an EBHR-type fuel can be calculated from the measurement of the pressure drop across the fuel. However, the calculated fuel length history obtained by the pressure drop in a port does not coincide with that obtained by the reconstruction technique because of an underestimation in pressure drop.

  33. Investigation of regression rate under high-pressure in axial-injection end-burning hybrid rockets

    Yushi Okutani, Yuji Saito, Masaya Kimino, Ayumu Tsuji, Kentaro Soeda, Harunori Nagata

    2018 Joint Propulsion Conference 2018年1月1日

    詳細を見る 詳細を閉じる

    © 2018 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. This study is an investigation of preeminent fuel regression rate in Axial-injection End-burning hybrid rockets under high pressure conditions. The authors overcame a back firing problem at high pressure conditions by redesigning and optimizing the fuel port diameter. The fuel grain outer diameter was 38 mm and the port diameter was 0.4 mm. Firing tests were conducted using gaseous oxygen as oxidizer at chamber pressures range from 0.98 MPa to 1.44 MPa. The results of four static firing tests show that fuel regression rate increases as the chamber pressure increases, which is consistent with previous research results. Fuel regression rate reached approximately 12.6 mm/s at 1.44 MPa. The authors reformulated the relationship between fuel regression rate and chamber pressure based on the results of high chamber pressure region, and showed that the pressure exponent increased from 1.09 to 1.20.

  34. Investigation of graphite nozzle erosion in hybrid rockets using o2/c2h4

    Landon Kamps, Shota Hirai, Kazuhito Sakurai, Tor Viscor, Yuji Saito, Raymond Guan, Hikaru Isochi, Naoto Adachi, Mitsunori Itoh, Harunori Nagata

    2018 Joint Propulsion Conference 2018年1月1日

    詳細を見る 詳細を閉じる

    © 2018 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. A recently developed reconstruction technique titled nozzle-throat reconstruction technique is used to investigate graphite nozzle-throat-erosion in two scales of hybrid rocket motors, 30N-thrust class and 2000N-thrust class, using oxygen as the oxidizer and high density polyethylene as the fuel. Thirty seven static firing tests were conducted under varying experimental conditions to confirm the validity of the reconstruction technique results, investigate the conditions at the onset of erosion and to formulate an empirical predictive model of nozzle erosion rate. Results show that nozzle erosion increases the convective heat transfer coefficient to upwards of 2-4 times the value predicted by Bartz correlation. Furthermore, an empirical model is introduced that treats the combustion gas as a single oxidizing agent with heterogeneous rate constants that are distributions of equivalence ratio of the bulk fluid flow. This empirical model predicts the nozzle throat erosion histories in multiple tests to within ± 5%.

  35. VERIFICATION OF THE THROTTLING CHARACTERISTICS OF AXIAL-INJECTION END-BURNING TYPE HYBRID ROCKETS 国際会議

    Y. Saito, T. Yokoi, H. Yasukochi, K. Soeda, T. Totani, M. Wakita, H. Nagata

    67th International Astronautical Congress 2017年10月

  36. Investigation of Regression Characteristics under Relatively High-Pressure in Axial-Injection End-Burning Hybrid Rockets 国際会議

    Yuji Saito, Masaya Kimino, Ayumu Tstuji, Yushi Okutani, Hiroyuki Yashukochi, Kentaro Soeda, Harunori Nagata

    53rd AIAA/SAE/ASEE Joint Propulsion Conference 2017年7月

  37. Investigation of Throttling Response Characteristics of Axial-Injection End-Burning Hybrid Rockets 国際会議

    Yuji SAITO, Masaya KIMINO, Ayumu TSUJI, Kazunobu OMURA, Hiroyuki YASUKOCHI, Kentaro SOEDA, Tsuyoshi TOTANI, Masashi WAKITA, Harunori NAGATA

    31st International Symposium on Space Technology and Science 2017年6月

  38. 端面燃焼式ハイブリッドロケットの推力制御時における時間応答性に関する研究

    齋藤 勇士, 君野 正弥, 津地 歩, 尾村 和信, 安河内 裕之, 添田 建太郎, 戸谷 剛, 脇田 督司, 永田 晴紀

    年会講演会講演集 2017年4月13日

  39. 液体酸素を用いた端面燃焼式ハイブリッドロケットの実現可能性

    津地歩, 齋藤勇士, 尾村和信, 君野正弥, 戸谷剛, 脇田督司, 永田晴紀

    宇宙科学技術連合講演会講演集(CD-ROM) 2017年

  40. 端面燃焼式ハイブリッドロケットの推力制御時におけるヒステリシス特性に関する研究

    君野正弥, 齋藤勇士, 津地歩, 尾村和信, 安河内裕之, 添田建太郎, 戸谷剛, 脇田督司, 永田晴紀

    宇宙科学技術連合講演会講演集(CD-ROM) 2017年

  41. 気体亜酸化窒素を酸化剤とした端面燃焼式ハイブリッドロケットの燃料後退特性

    尾村和信, 津地歩, 齋藤勇士, 君野正弥, 奥谷勇士, 小水弘大, 戸谷剛, 脇田督司, 永田晴紀

    宇宙科学技術連合講演会講演集(CD-ROM) 2017年

  42. 燃料微小管内を燃え拡がる火炎への雰囲気圧力の影響

    横井俊希, 齋藤勇士, 尾村和信, 津地歩, 安河内裕之, 添田建太郎, 脇田督司, 戸谷剛, 永田晴紀

    燃焼シンポジウム講演論文集 2016年11月26日

  43. 端面燃焼式ハイブリッドロケットの燃料後退モデルに関する考察

    齋藤勇士, 横井俊希, 津地歩, 尾村和信, 安河内裕之, 添田建太郎, 戸谷剛, 脇田督司, 永田晴紀

    燃焼シンポジウム講演論文集 2016年11月26日

  44. 液体酸素を用いた固体燃料管内燃え拡がりに関する研究

    津地歩, 齋藤勇士, 横井俊希, 尾村和信, 嶋田泰三, 戸谷剛, 脇田督司, 永田晴紀

    燃焼シンポジウム講演論文集 2016年11月26日

  45. ハイブリッドロケットにおけるノズルスロート浸食取得方法の精度と適用性に関する研究

    ケンプス ランドン, 齋藤 勇士, 平井 翔大, 永田 晴紀

    宇宙科学技術連合講演会講演集 2016年9月6日

  46. Method for Determining Nozzle Throat Erosion History in Hybrid Rockets 国際会議

    Landon T. Kamps, Yuji Saito, Ryosuke Kawabata, Yusuke Takahashi, Harunori Nagata

    52nd AIAA/SAE/ASEE Joint Propulsion Conference 2016年7月

  47. Experimental and Analytical Investigation of Effect of Pressure on Regression Rate of Axial-Injection End-Burning Hybrid Rockets 国際会議

    Yuji Saito, Toshiki Yokoi, Harunori Nagata, Hiroyuki Yasukochi, Kentaro Soeda, Tsuyoshi Totani, Masashi Wakiata

    52nd AIAA/SAE/ASEE Joint Propulsion Conference 2016年7月

  48. 端面燃焼式ハイブリッドロケットにおける燃料後退特性の圧力依存性に関する実験的および解析的考察

    齋藤 勇士, 横井 俊希, 嶋田 泰三, 安河内 裕之, 添田 建太郎, 戸谷 剛, 脇田 督司, 永田 晴紀

    年会講演会講演集 2016年4月14日

  49. Verification of the throttling characteristics of axial-injection end-burning type hybrid rockets

    Yuji Saito, Toshiki Yokoi, Hiroyuki Yasukochi, Kentaro Soeda, Tsuyoshi Totani, Masashi Wakita, Harunori Nagata

    Proceedings of the International Astronautical Congress, IAC 2016年1月1日

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    Copyright © 2016 by the International Astronautical Federation (IAF). All rights reserved. The axial-injection end-burning type hybrid rocket originally proposed twenty years ago by Nagata and Hashimoto et al. recently recaptured the attention of researchers for its virtues such as constant ξ (oxidizer to fuel mass ratio) during firing and throttling operations. Previous studies revealed that, for combustion in a single-port fuel grain, the end-face regression rate in the axial direction is proportional to pressure, with a pressure exponent of 0.95. Accordingly, these rockets were expected to display good throttling characteristics. Given that no ξ shift occurs, keeping the oxidizer mass flow rate within 1% of its initial design point ensures specific impulse will remain within 97% of its design point. There are several requirements for realizing this type of hybrid rocket: 1) high fuel filling rate for obtaining an optimal ξ 2) small port intervals for increasing port merging rate; 3) ports arrayed across the entire fuel section. Because common manufacturing methods were unable to produce a fuel that satisfied these requirements, no previous researchers have conducted experiments with this kind of hybrid rocket. Recent advances in high-accuracy 3D printing have enabled such fuels to be produced for the first time. The fuel grains used in this study were produced by a high-precision light polymerized 3D printer. Each grain consisted of an array of 0.3 mm diameter ports for a fuel filling rate of 98%. Last year, the authors reported the results of multiple firing tests of an axial-injection end-burning type hybrid rocket using 3D printed fuel grains and verified that solid fuel regression rate is linearly dependent on pressure. In this study, the authors conducted a unique set of experiments to verify the throttling characteristics of the axial-injection end-burning type hybrid rocket. Oxidizer mass flow rate and chamber pressure were throttled during firings by actuating valves in a fluid circuit consisting of four oxidizer supply lines. Chamber pressure and oxidizer mass flow rate were measured during each firing. These experimental data were analyzed by a reconstruction technique to obtain ξ history. The results show that ξ remains almost constant during firing, even during throttling operations. Therefore, this study verifies that the axial-injection end-burning type hybrid rocket has superb throttling characteristics. Additionally, the study supports findings in previous research that indicate the pressure exponent is close to unity.

  50. 端面燃焼式ハイブリッドロケットの推力制御特性

    永田 晴紀, 齋藤 勇士, 横井 俊希, 嶋田 泰三, 安河内 裕之, 添田 建太郎, 戸谷 剛, 脇田 督司

    年次大会 2016年

    詳細を見る 詳細を閉じる

    <p>The authors have previously proposed the concept of end burning type hybrid rockets which would use cylindrical fuel grains consisting of an array of many small ports running in the axial direction through which oxidizer gas would flow. Because of difficulty in manufacturing a fuel grain that satisfied requirements such as high volumetric filling rate (above 0.97) and micro-sized port intervals, the end burning hybrid rocket had yet to be achieved. The authors succeeded to verify the novel end burning type hybrid rocket for the first time owing recent progress in 3D printing technology. This paper reports throttling firing tests to verify the excellent throttling characteristic of end-burning type hybrid rockets, that is, virtually no O/F shift during throttling.</p>

  51. Verification Firings of End-burning Type Hybrid Rockets 国際会議

    H. Nagata, H.Teraki, Y. Saito, R.Kanai, H. Yasukochi, M.Wakiata, T. Totani

    51st AIAA/SAE/ASEE Joint Propulsion Conference 2015年7月

  52. Estimation of Hybrid Rocket Nozzle Throat Erosion History 国際会議

    Yuji SAITO, Tsutomu UEMATSU, Hikaru ISOCHI, Masashi WAKITA, Tsuyoshi TOTANI, Harunori NAGATAYuji SAITO, Tsutomu UEMATSU, Hikaru ISOCHI, Masashi WAKITA, Tsuyoshi TOTANI, Harunori NAGATA

    30th International Symposium on Space Technology and Science 2015年7月

  53. Evaluations of Data Reduction Methods for Hybrid Rockets 国際会議

    H.Nagata, Y.Saito, T.Ishiyama, Y.Inaba, M.Wakita, T.Totani

    65th International Astronautical Congress 2014年9月

︎全件表示 ︎最初の5件までを表示

産業財産権 4

  1. 宇宙機搭載の推進装置

    川口 淳一郎, 齋藤 勇士

    産業財産権の種類: 特許権

  2. 固体燃料トーチ装置、ハイブリッドロケット燃焼システムおよびハイブリッドロケット燃焼方法

    Kamps Landon, 永田 晴紀, 池田 華子, 平井 翔大, 齋藤 勇士, 高梨 知広

    産業財産権の種類: 特許権

  3. ハイブリッドロケットエンジンの固体燃料の時空間解析方法、時空間解析システム、および時空間解析プログラム

    齋藤勇士, 桒原聡文, 小林稜平

    産業財産権の種類: 特許権

  4. ハイブリッドロケットエンジンの燃焼状態解析方法、燃焼状態解析システム、および燃焼状態解析プログラム

    齋藤勇士, 桒原聡文, 小林稜平

    産業財産権の種類: 特許権

共同研究・競争的資金等の研究課題 15

  1. ハイブリッド推進機の固体燃料後退高時空間解像と燃焼機構解明

    齋藤 勇士

    提供機関:Japan Society for the Promotion of Science

    制度名:Grants-in-Aid for Scientific Research

    研究種目:Grant-in-Aid for Scientific Research (B)

    研究機関:Tohoku University

    2023年4月 ~ 2027年3月

  2. 小型宇宙機モビリティ確保に向けた6自由度運動制御可能なハイブリッドスラスタの宇宙実証 競争的資金

    提供機関:New Energy and Industrial Technology Development Organization

    研究機関:Tohoku University

    2021年3月 ~ 2026年3月

  3. 持続的な宇宙開発に向けたバイオマス燃焼推進装置の開発

    齋藤勇士, 中安祐太, 小林加代子

    提供機関:Tohoku University

    制度名:Creative Interdisciplinary Collaboration Program

    研究機関:Frontier Research Institute for Interdisciplinary Sciences

    2023年4月 ~ 2025年3月

  4. 宇宙軌道上長時間マヌーバを実現する低O/Fハイブリッドスラスタ 競争的資金

    提供機関:New Energy and Industrial Technology Development Organization

    研究機関:Tohoku University

    2023年8月 ~ 2024年2月

  5. データ駆動科学による超音速乱流大規模構造の超時空間解像計測

    野々村 拓, 芳賀 臣紀, 浅井 圭介, 齋藤 勇士

    提供機関:Japan Society for the Promotion of Science

    制度名:Grants-in-Aid for Scientific Research

    研究種目:Grant-in-Aid for Scientific Research (A)

    研究機関:Tohoku University

    2020年4月1日 ~ 2023年3月31日

    詳細を見る 詳細を閉じる

    本年度は,実験計測に関して,高速度カメラ・高繰り返しレーザーの購入を行い,測定装置の拡充を行った.コロナ感染症に対して当初感染防止を考慮しながら実験作業を進めたため若干の遅れがでている.平板に衝突する超音速噴流に対して,シュリーレンおよびマイクロフォンの同期計測を行った.ダブルパルスシュリーレンとすることにより,動的モード分解が実施できることを実証し,その精度を議論するとともに特徴的な現象を明らかにした.次に,超音速自由噴流に対して,粒子画像速度計測法とマイクロフォンの同時計測を行うことに成功した.これらのデータに対して,最も単純な時空間超解像のアルゴリズムを適用することで,予備的ではあるが,時空間超解像の結果を得ることができた.特に大規模構造から卓越周波数を持つ音響波の発生させるスクリーチ現象に対して,これを適用することで,ヘリカルモードで振動する超音速噴流の非定常挙動を明らかにすることができた.さらに高速狭画角と低速広画角の2つのシュリーレン計測を組み合わせた同時計測を実施し,さらなる時空間超解像計測のためのデータセットを構築することができた.数値解析に関しては,実験結果と数値解析結果の比較を行うことで,お互いの信頼性を確認した.合わせて時空間超解像の際の変動モードの推定の際にデータ同化した数値解析結果に基づくリゾルベントモードの活用を検討し,一部試験的にこれらの解析を実施した.

  6. データ駆動型スパースセンシングによる航空宇宙開発の飛躍

    2020年12月 ~ 2023年3月

  7. 非定常先進流体計測に基づく低次元モデルを利用した次世代流体制御

    浅井 圭介, 野々村 拓, 齋藤 勇士, 小室 淳史, 安養寺 正之

    提供機関:Japan Society for the Promotion of Science

    制度名:Grants-in-Aid for Scientific Research

    研究種目:Fund for the Promotion of Joint International Research (Fostering Joint International Research (B))

    研究機関:Tohoku University

    2019年10月7日 ~ 2022年3月31日

    詳細を見る 詳細を閉じる

    本共同研究は,大規模な渦構造や衝撃波の振動を伴う流れを動的フィードバックにより制御する新しい概念の流体制御理論の確立を目的とした.米国フロリダ州立大学(FSU)の研究グループと協働し,双方の知識と技術を持ち寄って,高精度な先進計測に基づく非定常流体データベースの構築,流れ場の低次元モデルに基づく流体現象の把握,高速応答アクチュエータの駆動という3つのキーテクノロジーの研究開発に取り組んだ.後胴模型における剥離流れと超音速衝突噴流を対象にFSUの大型実験設備を用いた実証実験を行うことで,従来の方法論では不可能とされていた流体制御能力の飛躍的な向上を実現するための研究基盤を構築した.

  8. 変形する物体が生む非定常流れの計測とロコモーション原理の解明

    浅井 圭介, 青野 光, 齋藤 勇士, 野々村 拓, 小澤 雄太, 澤田 惠介

    提供機関:Japan Society for the Promotion of Science

    制度名:Grants-in-Aid for Scientific Research

    研究種目:Grant-in-Aid for Scientific Research (A)

    研究機関:Tohoku University

    2019年4月1日 ~ 2022年3月31日

    詳細を見る 詳細を閉じる

    本研究は,運動を伴う翼面の非定常流体力によるロコモーションの空気力学的メカニズムの解明とそのために必要となる実験手法を確立することを目的に実施した.酸素消光性を有する色素分子からなる感圧塗料に寿命計測法とデータ同化を利用した3次元形状変形計測を組み合わせ,変形する翼面上の非定常圧力分布を画像に捉える技術を開発し,回転翼と羽ばたき翼を対象にした評価試験でその有効性を実証した.これらの新手法を用いて,大規模剥離渦と翼面に働く流体力の関係を調べ,運動する翼面が揚力や推力を効率的に生むメカニズムに関する多くの知見を得,理論だけは解決できなかった設計上の諸問題の解決に道を拓いた.

  9. 「アルミニウム-水」ハイブリッド燃焼を用いた推進系の開発

    2020年12月 ~ 2022年3月

  10. 金属/水を用いたハイブリッドスラスタの燃焼機構の解明 競争的資金

    齋藤 勇士

    2018年10月 ~ 2020年3月

  11. 革新的ハイブリッドロケットの燃焼機構の解明 競争的資金

    齋藤 勇士

    提供機関:TEPCO Memorial Foundation

    制度名:Support for International Technological Interaction

    2019年8月 ~ 2019年8月

  12. 拡大流路内を燃え拡がる対向流拡散火炎の吹き飛び限界に関する研究 競争的資金

    齋藤 勇士

    2017年10月 ~ 2018年10月

  13. 端面燃焼式ハイブリッドロケットの燃焼機構の解明 競争的資金

    齋藤 勇士

    2017年4月 ~ 2018年3月

  14. 端面燃焼式ハイブリッドロケットの燃料後退特性に関する研究 競争的資金

    齋藤 勇士

    2016年4月 ~ 2017年3月

  15. 平成28年度若手研究者海外渡航助成 競争的資金

    齋藤 勇士

    2016年 ~ 2016年

︎全件表示 ︎最初の5件までを表示

担当経験のある科目(授業) 2

  1. 機械知能・航空実験Ⅱ 東北大学

  2. 機械知能・航空実験Ⅰ 東北大学

社会貢献活動 3

  1. 沼津工業高等専門学校「社会と産業」

    オンライン

    2023年10月19日 ~ 2023年10月19日

  2. 東北大学講演会-流体科学ってなんだろう?-

    オンライン

    2022年2月22日 ~ 2022年2月22日

  3. 沼津高専機械工学科4年生進路決定を控えた学生向けへのオンライン説明会

    オンライン

    2021年12月15日 ~ 2021年12月15日

メディア報道 6

  1. 世界初の宇宙実証へ向け、小型人工衛星を地球に帰還させるための高推力&経済性&安全性を兼ね備える"ハイブリッドスラスタ"、軌道離脱に必要な長時間燃焼に成功

    東北大学

    2023年8月25日

    メディア報道種別: インターネットメディア

  2. ハイブリッドスラスタへの着火技術に関する三者間共同研究契約の締結および燃焼実験の実施について

    株式会社ElevationSpace

    2023年3月23日

    メディア報道種別: インターネットメディア

  3. 高速な空気の流れをリアルタイム計測 従来比20倍速を実現 ~変化する流体に呼応するアクティブ制御に期待~

    科学技術振興機構(JST)

    2022年8月30日

    メディア報道種別: インターネットメディア

  4. 自動車表面の風圧分布を瞬時に推定する技術を開発 ~自動運転車の安全性向上と燃費削減に期待~

    科学技術振興機構(JST)

    2022年6月24日

    メディア報道種別: インターネットメディア

  5. 2023年の軌道上実証を目指し、世界最高性能の小型推進装置の開発を加速 株式会社ElevationSpaceと東北大学の共同研究がNEDO「若サポ」に採択

    東北大学

    2022年4月21日

    メディア報道種別: インターネットメディア

  6. 世界初の小型宇宙利用プラットフォームを開発するElevationSpaceが東北大学と共同で世界最高性能の小型推進装置の開発を開始

    株式会社ElevationSpace

    2021年9月21日

    メディア報道種別: インターネットメディア

︎全件表示 ︎最初の5件までを表示

その他 1

  1. 高圧ガス製造保安責任者(乙種機械)