著者

波多 英寛 日南川 英明 平山 寛 花田 俊也 藤原 和人 廣江 哲幸

出版者

一般社団法人日本機械学会

雑誌

スペース・エンジニアリング・コンファレンス講演論文集 : Space Engineering Conference (ISSN:09189238)

巻号頁・発行日

vol.2009, no.18, pp.107-110, 2010-01-28

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This study was bursting test of lithium-ion battery using small satellite by overcharge. As a result, the lithium-ion battery exploded by overcharge and confirmed that a flame occurred. The temperature at the time of the bursting was measured, and it was around 150 degrees Celsius. As for the collection fragments, it was measured dimensions, and the distribution of the collection fragments was provided.

著者

吉田 哲二 金山 秀樹 山本 亘 向山 澄夫 金森 洋史 青木 滋

出版者

一般社団法人日本機械学会

雑誌

スペース・エンジニアリング・コンファレンス講演論文集 : Space Engineering Conference (ISSN:09189238)

巻号頁・発行日

vol.2009, no.18, pp.67-70, 2010-01-28

被引用文献数

1

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月太陽発電「ルナリング」構想は,工ネルギを化石燃料に依存するパラダイムから,月からの無限に近いクリーンエネルギを自由に使うという発想へ転換するものである.本構想では月の赤道を周回する太陽電池を設置し,発電した電力をマイクロ波などで地上へ伝送する-人類が使う工ネルギの全部の量を月から送り電力供給と水素製造を行う.食糧・水の確保や水素社会が促進されると同時に化石燃料の燃焼を停止させ炭酸ガスの排出を低下させる.実現には宇宙太陽発電システムや月資源探査,月面での製造技術が必要.月面口ポットや有人施設だけでなく,国際的な協定・合意など法制面の確立も必要.清水建設の20余年にわたる宇宙建設研究をべ-スに夢のある将来像を描いた.

著者

廣松 卓真 小清水 孝夫 WIDYAPARAGA Adhika 河野 正道 高田 保之

出版者

一般社団法人日本機械学会

雑誌

スターリングサイクルシンポジウム講演論文集 (ISSN:09189238)

巻号頁・発行日

vol.2014, no.17, pp.71-72, 2014-12-05

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We have constructed and tested a shell and tube heat exchanger with a dual speaker thermoacoustic device. We have tested a shell and tube heat exchanger by changing the phase between two speakers at both ends of the device. Five thermocouples are positioned within the regenerator and inlet and outlet water temperature were measured with two other thermocouples. Two pressure sensors are positioned each side of the device along the regenerator. We have measured the regenerator temperature and pressure at both sides of the regenerator with changing the mass flow rate of coolant water. The temperature distribution of regenerator and the acoustic power were gained from measured values.

著者

小野 顕正 黒木 聖司

出版者

一般社団法人日本機械学会

雑誌

スペース・エンジニアリング・コンファレンス講演論文集 (ISSN:09189238)

巻号頁・発行日

vol.2010, pp._D5-1_-_D5-4_, 2011

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A Soka University pico-satellite "Negai" measures mere 10cm cube and weights just one kilogram. Its orbit is 300km with inclination of 30 degrees. In 30 days or so after launch it will be dragged by the air and it is burnt out to become a manmade shooting star when reentering to the atmosphere. People believe wishing upon a shooting star makes their dreams come true. The main mission is to carry children's dreams recruited from the public microfilmed to be loaded on the satellite. Hence it is called "Negai" or "Wish." The technical mission is to space prove the high functional information system with inside triple-redundant fault-tolerant soft-core CPU embedded in an FPGA and reliable picture transmission system. This paper emphasized on the technical mission as well as how we operated so short mission life operation with 30 degrees inclination.

著者

永田 晴紀 渡辺 三樹生 伊藤 光範 前田 剛典 戸谷 剛 工藤 勲

出版者

一般社団法人日本機械学会

雑誌

スペース・エンジニアリング・コンファレンス講演論文集 : Space Engineering Conference (ISSN:09189238)

巻号頁・発行日

vol.2004, no.13, pp.1-4, 2005-01-20

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Small-scale reusable sounding rocket system is under development to provide means of stratosphere observation and three-minutes microgravity experiment. The propulsion system is a hybrid type that uses solid fuel (plastics) and liquid oxygen as propellants and free from explosives, resulting in the dramatically reduced launch cost. To enhance the burning rate of the solid fuel and to augment the thrust, the rocket has employed a new fuel grain design. This new design, named CAMUI as an abbreviation of "Cascaded Multistage Impinging-jet", allows mixing and combustion to occur around stagnation points on fuel surfaces. Successful launch experiments using a 50-kgf CAMUI engine have proved the feasibility of the basic idea of the system. Finally, possible configurations of the stratosphere observation vehicle and the microgravity test vehicle are presented.

著者

白坂 成功 石橋 金徳 中須賀 真一

出版者

一般社団法人日本機械学会

雑誌

スペース・エンジニアリング・コンファレンス講演論文集 : Space Engineering Conference (ISSN:09189238)

巻号頁・発行日

vol.2010, no.19, pp."F4-1"-"F4-4", 2011-01-27

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Under the current development of mid-to-large size satellites, the high reliability is mandatory to avoid failures and their development cost increases enormously to achieve the high reliability. On the other hand, several universities develop and launch nano-satellites with low cost for the purpose of education from around 2000. To generate new market for satellite utilization, low cost and fast development are key points. The balance of cost and reliability is one of the very important points to realize the markets. The theoretical research toward the balance of cost and reliability is being conducted through the governmental first program "New Space Development and Utilization Paradigm by Nano-satellites Introducing Japan-oriented Reasonable Reliable Systems Engineering". This paper presents the concept of the way to realize the reasonably reliable systems engineering. Current reliability is based on the assumption that there is no miss-design and it only depends on the random failure of parts. However, many of real on-orbit failures were caused by design errors. We propose the new reliability which includes design error and the definition of the reasonably reliable Systems Engineering. The realization concept consists of re-use of design, reduction of complexity, functional redundancy and simple organization to develop nano-satellites.