ADN 系イオン液体を用いた電圧印加型燃焼器の設計指針の提案と検証

Material type: 規格・テクニカルリポート類

Author: 大森, 稜介ほか

Publisher: 宇宙航空研究開発機構 (JAXA)

Publication date: 2025-02-28

Material Format: Digital

Capacity, size, etc.: -

NDC: -

View All

Notes on use

Note (General)：: 出版タイプ： VoRElectrical ignition enables easy decomposition and ignition of ammonium dinitramide based energetic ionic liquids (ADN-based EILs), which ar...

Search by Bookstore

Holdings of Libraries in Japan

This page shows libraries in Japan other than the National Diet Library that hold the material.

List of Cooperating Institutions and Databases

Please contact your local library for information on how to use materials or whether it is possible to request materials from the holding libraries.

other

JAXA Repository
Digital
You can check the holdings of institutions and databases with which Institutional Repositories DataBase(IRDB)(Institutional Repository) is linked at the site of Institutional Repositories DataBase(IRDB)(Institutional Repository).
JAXA Repository

Search by Bookstore

Bibliographic Record

You can check the details of this material, its authority (keywords that refer to materials on the same subject, author's name, etc.), etc.

Digital

Material Type: 規格・テクニカルリポート類
Title: ADN 系イオン液体を用いた電圧印加型燃焼器の設計指針の提案と検証
Author/Editor: 大森, 稜介
伊東山, 登
塩田, 謙人
三宅, 淳巳
伊里, 友一朗
Publication, Distribution, etc.: 宇宙航空研究開発機構 (JAXA)
Publication Date: 2025-02-28
Publication Date (W3CDTF): 2025
Alternative Title: Proposal and validation of design principle for electrolytic combustor using ammonium dinitramide-based energetic ionic liquids
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6年度研究成果報告書
No. or year of volume/issue: JAXA-RR-24-006
Volume: JAXA-RR-24-006
Pages: 19-23
ISSN (Periodical Title): EISSN : 2433-2216
Alias of Author: ITOYAMA, Noboru
IZATO, Yuichiro
Subject Heading: Ammonium dinitramide
Energetic ionic liquid
Electrolysis
combustor
Target Audience: 一般
Note (General): 出版タイプ： VoR
Electrical ignition enables easy decomposition and ignition of ammonium dinitramide based energetic ionic liquids (ADN-based EILs), which are promising alternatives to hydrazine-based monopropellants. We aim to develop an electrolytic ignition thruster. In this report, design principles for an electrolytic combustor are proposed, and combustion tests were conducted using the constructed combustor. The mass flow rate of the combustion gas was identified as a critical factor in achieving the desired thrust. Although the design combustion pressure was attained, the target thrust was not met due to the combustion of unburned gases remaining in the Ensuring propellant combustion while supplying it between the electrodes will facilitate achieving the intended pressure and validate this design principle.
形態: カラー図版あり
Physical characteristics: Original contains color illustrations
レポート番号: JAXA-RR-24-006
DOI: 10.20637/0002001440
https://doi.org/10.20637/0002001440
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