文献一覧: 山口敬之 (著者)

9 0 0 0 歴史的スクープ韓国軍にベトナム人慰安婦がいた! : 米機密公文書が暴く朴槿恵の"急所"

著者: 山口敬之
出版者: 文芸春秋
雑誌: 週刊文春
巻号頁・発行日: vol.57, no.13, pp.30-35, 2015-04-02

2022-03-31 12:14:02
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https://ci.nii.ac.jp/naid/40020405625

3 0 0 0 パルスデトネーションエンジン用入口流体駆動バルブに関する研究

著者: 山口敬之松岡健八桁純笠原次郎
出版者: 一般社団法人日本航空宇宙学会
雑誌: 日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences (ISSN:13446460)
巻号頁・発行日: vol.57, no.663, pp.141-147, 2009-04-05
参考文献数: 22
被引用文献数: 2

In the present study, a dynamics model of an inflow-drive valve for pulse detonation engines (PDEs) is proposed, in which system the inflow of the valve periodically drives the valve piston. Since the inflow-drive valve needs no energy source to drive the piston, the mass flow rate divided by the valve mass is relatively large, and the response time for the mass-flow-rate change can be short. Moreover, the inflow-state condition for the stable valve operation is not restricted. The two-cylinder three-fluid type inflow-drive valve was fabricated. The maximum mass flow rate for one valve was evaluated as 6.3g/s, in which system the mass of the piston, the spring constant, and the supplied pressure were 3.8kg, 9800N, and 1.0MPa, respectively. The total mass flow rate using propellant was evaluated as 12g/s. The PDE system was constructed by using these inflow-drive valves. This system was stably operated in the frequency of 17.52Hz.

2022-01-25 16:50:44
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1 0 0 0 アラスカ大学との学生共同ロケット実験計画(S68-1 ロケットおよびインフレータブル構造,S68 学生による宇宙活動)

著者: 山口敬之遠山文雄 Hawkins Joe 学生ロケットプロジェクトチーム
出版者: 一般社団法人日本機械学会
雑誌: 年次大会講演論文集 : JSME annual meeting
巻号頁・発行日: vol.2004, no.5, pp.463-464, 2004-09-04
被引用文献数: 2

We have collaborated a student rocket project with the University of Alaska Fairbanks (UAF) since 1995 and two student sounding rockets were launched in 2000 and in 2002. The student rocket is designed and made by students during from the planning to analysis. The third launch will be at Alaska in March 2005. The apogee altitude of rocket is designed to 100 km. Tokai student team has made a UV. sensor, a digital sun sensor and a 3-axial fluxgate magnetometer on this rocket. We have a plan to measure ultraviolet ray in the polar region. By UV measuring, we may estimate the ozone density and total ozone quantity as a scientific mission. We also can measure a rocket attitude performance by a magnetometer and a sun sensor as the second task.