加熱反応試験による低毒性推進剤に関する燃焼特性評価

Material type: 規格・テクニカルリポート類

Author: 尾松, 来基ほか

Publisher: 宇宙航空研究開発機構(JAXA)

Publication date: 2021-02-10

Material Format: Digital

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Note (General)：: 出版タイプ： VoRHydrazine has been used as a propellant in monopropellant thrusters for the spacecraft attitude control, but due to its high toxicity, resea...

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Material Type: 規格・テクニカルリポート類
Title: 加熱反応試験による低毒性推進剤に関する燃焼特性評価
Author/Editor: 尾松, 来基
半澤, 佳祐
伊藤, 尚義
勝身, 俊之
門脇, 敏
OMATSU, Raiki
HANZAWA, Keisuke
ITO, Hisayoshi
KATSUMI, Toshiyuki
KADOWAKI, Satoshi
Author Heading: 尾松, 来基
半澤, 佳祐
伊藤, 尚義
勝身, 俊之
門脇, 敏
OMATSU, Raiki
HANZAWA, Keisuke
ITO, Hisayoshi
KATSUMI, Toshiyuki
KADOWAKI, Satoshi
Publication, Distribution, etc.: 宇宙航空研究開発機構(JAXA)
Publication Date: 2021-02-10
Publication Date (W3CDTF): 2021-02-10
Alternative Title: Evaluation of Green Monopropellant Combustion Characteristics by Heat Reaction Test
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2年度研究成果報告書 = JAXA Research and Development Report: Technical Report of The Research Activity for High Energy Materials (2020)
No. or year of volume/issue: JAXA-RR-20-007
Volume: JAXA-RR-20-007
Pages: 9-13
ISSN (Periodical Title): ISSN : 2433-2216
Text Language Code: jpn
Target Audience: 一般
Note (General): 出版タイプ： VoR
Hydrazine has been used as a propellant in monopropellant thrusters for the spacecraft attitude control, but due to its high toxicity, research on low-toxic monopropellants based on Ammonium Dinitramide (ADN) and Hydroxylammonium Nitrate (HAN) has become active in recent years. Since these low-toxicity propellants contain oxidant components and have high combustion temperatures, there is an urgent need to develop a catalyst and combustion control technologies with high thermal resistance. Therefore, we wondered if the kick-off temperature could be controlled by using a catalyst. In this study, combustion tests of ADN-based low toxicity propellants (from now on will be referred as AMU-based) were carried out to understand the basic combustion characteristics of the propellants using a droplet heating and combustion tester. In the test, we designed and manufactured a droplet heating combustion test device, and worked on the acquisition of combustion characteristics using a catalyst to confirm the reactivity of the propellant in each temperature range.
形態: カラー図版あり
Physical characteristics: Original contains color illustrations
資料番号: AA2030016003
レポート番号: JAXA-RR-20-007
DOI: 10.20637/00047349
https://doi.org/10.20637/00047349
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