研究者業績

山本 高行

ヤマモト タカユキ  (Takayuki Yamamoto)

基本情報

所属
国立研究開発法人宇宙航空研究開発機構 宇宙科学研究所 DESTINY+プロジェクトチーム 主幹研究開発員
学位
博士(工学)(2005年3月 東京大学)

研究者番号
60443280
J-GLOBAL ID
202001000370405138
researchmap会員ID
R000014112

論文

 63
  • Hiroyuki TOYOTA, Takeshi TAKASHIMA, Hiroshi IMAMURA, Kazutaka NISHIYAMA, Takayuki YAMAMOTO, Takeshi MIYABARA, Masayuki OHTA, Yoshitaka MOCHIHARA, Naoya OZAKI, Hiroyuki NAGAMATSU, Takakazu OKAHASHI, Junko TAKAHASHI, Toshiaki OKUDAIRA, Takayuki HIRAI, Masanori KOBAYASHI, Ko ISHIBASHI, Peng HONG, Osamu OKUDAIRA, Tomoko ARAI
    Journal of Evolving Space Activities 1 2023年12月  査読有り
  • Takuya Iwaki, Takayuki Yamamoto, Satoshi Nonaka, Takayuki Ogita, Yukie Sakoda
    2023 62nd Annual Conference of the Society of Instrument and Control Engineers (SICE) 2023年9月6日  
  • Naoya Ozaki, Takayuki Yamamoto, Ferran Gonzalez-Franquesa, Roger Gutierrez-Ramon, Nishanth Pushparaj, Takuya Chikazawa, Diogene Alessandro Dei Tos, Onur Çelik, Nicola Marmo, Yasuhiro Kawakatsu, Tomoko Arai, Kazutaka Nishiyama, Takeshi Takashima
    Acta Astronautica 2022年4月  
  • Shinichiro TOKUDOME, Tsuyoshi YAGISHITA, Ken GOTO, Naohiro SUZUKI, Takayuki YAMAMOTO, Yasuhiro DAIMOH
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 19(2) 186-192 2021年  
  • T. Ito, T. Yamamoto, T. Nakamura, H. Habu, H. Ohtsuka
    Acta Astronautica 170 206-223 2020年5月  
    © 2019 IAA This paper investigates the launch capability of the SS-520 as a CubeSat launch vehicle. The SS-520 was developed by JAXA originally as a two-stage, spin-stabilized, solid-propellant sounding rocket. With less than 2.6 tons in total mass and 10 m in length, the SS-520-5 successfully launched a single 3U-sized CubeSat into orbit on February 3, 2018. The SS-520-5 obtained its capability as a CubeSat launch vehicle by installing a 3rd stage solid motor in addition to the RCS between the 1st and 2nd stages. However, its launch capability was limited due to its rocket system configuration. In order to pursue the SS-520's launch capability, two effective modifications from the SS-520-5 are proposed: thrust enhancement of the 1st stage motor and installation of an additional RCS between the 2nd and 3rd stages. The framework of launch capability analysis is established by a multi-objective genetic algorithm (MOGA), where its two objectives are selected as the altitudes of perigee and apogee. The analysis reveals that the two proposed modifications to the SS-520-5 work effectively but differently. The 10% increase of the 1st stage enhancement is particularly effective when the target altitude of perigee is low (e.g., 200 km), whereas the installment of the additional RCS with 30 kg increases accessibility to a much higher altitude of perigee, even to circular orbit reaching altitudes of 550 km for a 1U-sized CubeSat and 280 km for a 6U-sized CubeSat. The simultaneous application of both modifications would result in launch capability able to deliver a 10-kg payload. From a more general perspective, the results in this paper suggest that it is possible for a very small launch vehicle (VSLV) of the 3-ton class and 10 m in length to deliver a 10-kg-class payload into low Earth orbit.

MISC

 58
  • 徳留真一郎, 餅原義孝, 三浦政司, 坂本勇樹, 森下直樹, 山本高行, 荒川聡, 竹内伸介, 竹前俊昭, 豊田裕之, 奥平俊暁, 太刀川純孝, 寺島啓太, 紙田徹, 今村裕志, 高島健
    宇宙科学技術連合講演会講演集(CD-ROM) 67th 2023年  
  • 三浦政司, 餅原義孝, 徳留真一郎, 荒川聡, 竹前俊昭, 森下直樹, 山本高行, 太刀川純孝, 竹内伸介, 豊田裕之, 奥平俊暁, 坂本勇樹, 寺島啓太, 紙田徹, 高島健
    宇宙科学技術連合講演会講演集(CD-ROM) 66th 2022年  
  • 後藤 健, 丸 祐介, 山田 和彦, 志田 真樹, 福島 洋介, 山本 高行, 徳留 真一郎, 野中 聡, 峯杉 賢治, 竹内 伸介, 佐藤 泰貴, 澤井 秀次郎, 羽生 宏人, 阿部 琢美
    2021年3月  
    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)著者人数: 14名資料番号: SA6000162017レポート番号: Ⅴ-3
  • 山本高行, 尾崎直哉, ALESSANDRO Dei Tos Diogene, FERRAN Gonzalez Franquesa, NISHANTH Pushparaj, ROGER Gutierrez-Ramon, 近澤拓弥, 川勝康弘, 高島健
    宇宙科学技術連合講演会講演集(CD-ROM) 65th 2021年  
  • 山本高行, 尾崎直哉, TOS Diogene Alessandro Dei, CELIK Onur, GONZALEZ-FRANQUESA Ferran, PUSHPARAJ Nishanth, 近澤拓弥, 川勝康弘
    宇宙科学技術連合講演会講演集(CD-ROM) 64th 2020年  

所属学協会

 1

産業財産権

 15