@article{oai:jaxa.repo.nii.ac.jp:00031806,
 author = {大島, 耕一 and 中山, 晴美 and 大島, 裕子 and OSHIMA, Koichi and NAKAYAMA, Harumi and OSHIMA, Yuko},
 issue = {2_A},
 journal = {東京大学宇宙航空研究所報告},
 month = {Apr},
 note = {一様外被-集中熱容量方式とでも呼ばれるべき宇宙船の温度設計方式を検討し,スペース・シミュレーターによる小型模型による実験によって,この解析法の有用性を論じた.この設計方式は薄い金属外披に包まれ,自身のまわりにスピンしながら,比較的低高度を飛ぶ人工衛星の温度設計に有用である.またこの設計方式を適用する際に必要な一様温度外被と,内部の集中した熱容量をもった諸計測器群との結合係数を実験的に定める方法も述べられる., A new thermal design concept of an artificial satellite, "uniform skin temperature-lumped heat mass method", is presented, which is especially useful for the satellite with a metal-covered skin and spinning around its own axis. At first, the temperature of a single skin body under cyclic heating and cooling is analysed, and a time constant which determines the temperature variation of the body is found out. Secondly, the effect of the internal compartments is analysed, which results in a correction to the time constant of the single skin body. Finally, using this skin temperature modified by the above-mentioned correction and the coupling constants between the skin and the internal compartments, the temperature of the whole system is calculated. Triple cylinders, which consist of three cylinders with different sizes successively hanged inside the each bigger one so as to be thermally coupled with each adjacent cylinder only through radiation, are tested in the space simulator. The outermost, biggest cylinder is heated cyclically in various way by an electric heater. Then this temperature variation gradually penetrates into the inner cylinders through radiation. This provides the simplest model of the above analysis and the results obtained strongly confirmed the usefulness of the above analysis., 資料番号: SA0124859000},
 pages = {453--466},
 title = {宇宙船の温度設計についての基礎的な研究},
 volume = {2},
 year = {1966}
}