@techreport{oai:jaxa.repo.nii.ac.jp:00044587,
 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 = {Oct},
 note = {Low-pressure deflagration limit(Pdl) of controllable solid rocket propellants was experimentally investigated using low-pressure combustion chambers and micro video-recorder. Pdl was affected by the specimen size, and this scale effect is explained by heat losses from the burning propellant to the surroundings. The dependence of Pdl on specimen size and inert gas composition was observed and it would seem that the main heat loss should be by radiation in the extinguishment of propellant at subatmospheric pressures. Initial temperature of propellant had a minor effect on Pdl. The effect of compositional variables of propellant on subatmospheric combustion and Pdl was studied. These variables were oxidizer blend ratio, binder type, oxidizer-fuel mixture ratio, aluminium content, mean particle diameter of oxidizers and shape and size of aluminium powders. Pdl was not so much affected by compositional variablee as expected. Aluminium agglomeration resulted in larger variations in subatmospheric combustion and subsequent extinguishment. Behavior of combustion at subatmospheric pressures and Pdl trend can be explained by qualitative theoretical consideration., 資料番号: NALTR0341000, レポート番号: NAL TR-341},
 title = {推力中断型固体ロケット用プロペラントの消火圧力},
 year = {1973}
}