ADN系イオン液体の電圧印加型燃焼器を用いた燃焼試験

Material type: 文書・図像類

Author: 大森, 稜介ほか

Publisher: 宇宙航空研究開発機構 (JAXA)

Publication date: 2024-01-30

Material Format: Digital

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Note (General)：: Ammonium dinitramide (ADN) based energetic ionic liquids (EILs) has been expected as a next HEMs. Since ADN-based EILs are thermally stable, it is dif...

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Material Type: 文書・図像類
Title: ADN系イオン液体の電圧印加型燃焼器を用いた燃焼試験
Author/Editor: 大森, 稜介
伊東山, 登
塩田, 謙人
伊里, 友一朗
三宅, 淳巳
Author Heading: 大森, 稜介
伊東山, 登
塩田, 謙人
伊里, 友一朗
三宅, 淳巳
Publication, Distribution, etc.: 宇宙航空研究開発機構 (JAXA)
Publication Date: 2024-01-30
Publication Date (W3CDTF): 2024-01-30
Alternative Title: Combustion test of ADN based ionic liquids using electrolytic combustor
Periodical title: 宇宙航空研究開発機構研究開発報告: 高エネルギー物質研究会: 令和5年度研究成果報告書
No. or year of volume/issue: JAXA-RR-23-005
Volume: JAXA-RR-23-005
Pages: 17-20
ISSN (Periodical Title): EISSN : 2433-2216
Text Language Code: jpn
Alias of Author: ITOYAMA, Noboru
IZATO, Yuichiro
Subject Heading: High energetic materials
Ammonium dinitramide
Electrolysis
Ignition
Target Audience: 一般
Note (General): Ammonium dinitramide (ADN) based energetic ionic liquids (EILs) has been expected as a next HEMs. Since ADN-based EILs are thermally stable, it is difficult to control ignition phenomena using thermal ignition methods. Our research group focused on an ignition method of the EILs by applying a voltage. Previous Studies have theoretically reported the possibility of ignition of ADN-based EILs and experimentally demonstrated the ignition. In order to demonstrate the feasibility of the thruster, it is essential to design a voltage-applied combustor concept and to confirm the generation of thrust. In this report, a conceptual design of a voltage-applied combustor based on the voltage-applied ignition mechanism and combustion tests of EILs using this combustor were conducted. The phenomena that occurred in the voltage-applied combustor were discussed based on the existing voltage-applied ignition mechanism, and the changes over time of the current values obtained from the current measurements conducted simultaneously with the combustion test were also discussed. Furthermore, the feasibility of the thruster concept was discussed based on the thrust measurement results.
形態: カラー図版あり
Physical characteristics: Original contains color illustrations
レポート番号: JAXA-RR-23-005
DOI: 10.20637/0002000218
Access Restrictions: インターネット公開
Data Provider (Database): 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
https://irdb.nii.ac.jp
Original Data Provider (Database): 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ