Combustion characteristics of ADN-based solid propellants

Material type: 文書・図像類

Author: 藤里, 公司ほか

Publisher: 宇宙航空研究開発機構

Publication date: 2012-03-30

Material Format: Digital

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Note (General)：: Ammonium perchrolate (AP) is the most useful oxidizer for the solid rocket motors (SRMs) under the present situation, however it is also the source of...

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Material Type: 文書・図像類
Title: Combustion characteristics of ADN-based solid propellants
Author/Editor: 藤里, 公司
羽生, 宏人
芝本, 秀文
于, 秀超
三宅, 淳巳
堀, 恵一
Fujisato, Koji
Habu, Hiroto
Shibamoto, Hidefumi
Yu, Xiuchao
Miyake, Atsumi
Hori, Keiichi
Author Heading: 藤里, 公司
羽生, 宏人
芝本, 秀文
于, 秀超
三宅, 淳巳
堀, 恵一
Fujisato, Koji
Habu, Hiroto
Shibamoto, Hidefumi
Yu, Xiuchao
Miyake, Atsumi
Hori, Keiichi
Publication, Distribution, etc.: 宇宙航空研究開発機構
Publication Date: 2012-03-30
Publication Date (W3CDTF): 2012-03-30
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: 平成23年度研究成果研究成果報告書 = JAXA Research and Development Report: Collaborative Research Activity on Energetic Materials Research Report FY2011
No. or year of volume/issue: JAXA-RR-11-005
Volume: JAXA-RR-11-005
Pages: 1-7
ISSN (Periodical Title): ISSN : 1349-1113
Text Language Code: eng
Target Audience: 一般
Note (General): Ammonium perchrolate (AP) is the most useful oxidizer for the solid rocket motors (SRMs) under the present situation, however it is also the source of the environmental pollution close to the launch site. It is well known that HCI is exhausted through the firing of SRMs and its concentration reaches approximately 10 to 20 mole percent of the total exhaust. "Environmentaly friendly" and "High performance" are required for the next-generation SRMs. In this study, ammonium dinitramide (ADN), which has recently attracted attentions as a halogen-free oxidizer was employed for a substitution of AP and the combustion properties of the composite propellants were investigated. Thermoplastic elastomer (TP) and hydroxyl-terminated butadiene polymer (HTPB) were used as a binder for this research. Pyrotechnic sensitivity analysis was conducted to estimate the safety of TP/ADN propellants. Strand burning tests were also carried out for all samples and the burning rate and temperature profile were obtained through these experiments. It was found that the burning rate characteristics of ADN-based propellants were influenced by the binders.
形態: カラー図版あり
Physical characteristics: Original contains color illustrations
資料番号: AA0065204001
レポート番号: JAXA-RR-11-005
Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=2045&item_no=1&attribute_id=31&file_no=1
https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=2045&item_no=1&attribute_id=31&file_no=1
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