@inproceedings{oai:jaxa.repo.nii.ac.jp:00003839,
 author = {宮谷, 聡 and 山田, 和彦 and 安部, 隆士 and Miyatani, Satoshi and Yamada, Kazuhiko and Abe, Takashi},
 book = {宇宙航空研究開発機構特別資料: 第46回流体力学講演会/第32回航空宇宙数値シミュレーション技術シンポジウム論文集, JAXA Special Publication: Proceedings of the 46th Fluid Dynamics Conference / 32nd Aerospace Numerical Simulation Symposium},
 month = {Mar},
 note = {第46回流体力学講演会/第32回航空宇宙数値シミュレーション技術シンポジウム (2014年7月3日-4日. 弘前文化センター), 弘前市, 青森県, 46th Fluid Dynamics Conference / 32nd Aerospace Numerical Simulation Symposium (July 3-4, 2014. Hirosaki Bunka Center), Hirosaki, Aomori, Japan, A low ballistic coefficient atmospheric re-entry system, which applies a flexible membrane aeroshell to a spacecraft, attracts attention recently as a next-generation technology for space transportation. In order to realize this innovative technology, one of the important subjects is heating resistance evaluation of the membrane material for this flexible aeroshell. Therefore, inductively coupled plasma (ICP) heater was newly developed which has the ability to simulate the heating environment of the low-ballistic-coefficient re-entry. This ICP heater has 10kW electric power supply and Φ75mm glass tube. In this paper, the operating range of ICP heater and the result of heat flux distribution and dynamic pressure of air plasma flow are introduced. It is confirmed that the plasma flow produced by this ICP heater is axisymmetric and its core flow has a diameter of 40mm. Furthermore, the heat flux is controllable from almost 100kW/m2 to 250kW/m2, which is enough to evaluate the durability of the membrane material for the atmospheric entry vehicle., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1530023004, レポート番号: JAXA-SP-14-010},
 pages = {17--22},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {10kW級Φ75mm大口径ICP加熱器の気流特性に関する研究},
 volume = {JAXA-SP-14-010},
 year = {2015}
}