@techreport{oai:jaxa.repo.nii.ac.jp:00044561,
 author = {五代, 富文 and 清水, 盛生 and 伊藤, 克弥 and 西村, 久男 and 種村, 利春 and 藤原, 勉 and GODAI, Tomifumi and SHIMIZU, Morio and ITO, Katsuya and NISHIMURA, Hisao and TANEMURA, Toshiharu and FUJIWARA, Tsutomu},
 month = {Apr},
 note = {Experimental investigation of the pressure exponent in burning rate rule was conducted in order to find desirable propellants for controllable solid rockets. In strand and motor firings, partial replacement of ammonium perchlorate with potassium perchlorate, unimodal size distribution and finer particle size of oxidizers, lower loading fraction of binder, polybutadiene binder, and limited addition of aluminium were effective in obtaining higher pressure exponent of the composite propellants. The compositional effect on pressure exponent was explained by combustion mechanism considerations and granular diffusion flame theory., 資料番号: NALTR0316000, レポート番号: NAL TR-316},
 title = {推力中断型固体ロケット用プロペラントの組成と圧力指数の関係},
 year = {1973}
}