@techreport{oai:jaxa.repo.nii.ac.jp:00002008,
 author = {羽生, 宏人 and 加藤, 勝美 and 藤里, 公司 and 永山, 清一郎 and 田中, 邦翁 and 小駒, 益弘 and 徳留, 真一郎 and 堀, 恵一 and Habu, Hiroto and Kato, Katsumi and Fujisato, Koji and Nagayama, Seiichiro and Tanaka, Kunihito and Kogoma, Masuhiro and Tokudome, Shinichiro and Hori, Keiichi},
 month = {Mar},
 note = {The cost reduction is currently important for the development of space launch systems. The solid motor side jet system is loaded the low temperature gas generator propellant (GGP) which includes a special purpose material. The combustion gas temperature of GGP should be controlled up to 1400 K because of the system requirement. The objective of this research is to find the substitution of the composition for GGP to reduce the cost. That is why ammonium nitrate (AN) is selected as an oxidizer for GGP. The composition and combustion characteristics of AN based GGP for the launch vehicle side jet system were investigated. The burning rate was measured by the strand burner., 形態:カラー 図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0061907005, レポート番号: JAXA-RR-12-005},
 title = {低コストガスジェネレータ推進薬の研究},
 year = {2013}
}