新規物質を適用した固体推進薬の理論推進性能検討

Material type: 文書・図像類

Author: 松本, 幸太郎ほか

Publisher: 宇宙航空研究開発機構(JAXA)

Publication date: 2023-02-03

Material Format: Digital

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Note (General)：: In this study, the application of novel materials to solid propellants was investigated to enhance the propulsion performance of solid rockets. The pr...

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Material Type: 文書・図像類
Title: 新規物質を適用した固体推進薬の理論推進性能検討
Author/Editor: 松本, 幸太郎
MATSUMOTO, Kotaro
Author Heading: 松本, 幸太郎
MATSUMOTO, Kotaro
Publication, Distribution, etc.: 宇宙航空研究開発機構(JAXA)
Publication Date: 2023-02-03
Publication Date (W3CDTF): 2023-02-03
Alternative Title: Theoretical Propulsion Performance of Solid Rocket Propellants using Novel Materials
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4年度研究成果報告書 = JAXA Research and Development Report: Technical Report of The Research Activity for High Energy Materials (2022)
No. or year of volume/issue: JAXA-RR-22-006
Volume: JAXA-RR-22-006
Pages: 29-31
ISSN (Periodical Title): ISSN : 2433-2216
Text Language Code: jpn
Subject Heading: Solid Propellant
Aluminum alloy
Nitro-HTPB
Lithium Perchlorate
Target Audience: 一般
Note (General): In this study, the application of novel materials to solid propellants was investigated to enhance the propulsion performance of solid rockets. The propulsion performances of ammonium perchlorate (AP) based composite propellants contained the alternative materials was calculated by the chemical equilibrium calculations. In the case where lithium perchlorate (LP) was applied as a alternative material for the oxidizer, the vacuum specific impulse (Ispv) decreased with increasing the amount of LP, but the density specific impulse increased. The specific impulse was increased with increasing Li addition for the case where Al-Li and Al-Mg alloys were used as the metal fuel. It was also obtained that the addition of Li suppressed the formation of HCl. Although the use of Nitro-HTPB as a binder did not improve the vacuum specific impulse, it is expected to reduce the viscosity of the solid propellant slurry because it increases the ratio of the binder component at the maximum specific impulse. Therefore, the results showed that various advantages can be obtained by changing the components of AP based composite propellants to the novel materials.
形態: カラー図版あり
Physical characteristics: Original contains color illustrations
資料番号: AA2230017007
レポート番号: JAXA-RR-22-006
DOI: 10.20637/00049039
Access Restrictions: 限定公開
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