@techreport{oai:jaxa.repo.nii.ac.jp:00044791,
 author = {五代, 富文 and 清水, 盛生 and 伊藤, 克弥 and 種村, 利春 and 藤原, 勉 and GODAI, Tomifumi and SHIMIZU, Morio and ITO, Katsuya and TANEMURA, Toshiharu and FUJIWARA, Tsutomu},
 month = {Jul},
 note = {The decrease in pressure exponent in the burning rate rule of solid propellants was observed when the propellants having high values of pressure exponent in strand burning tests were fired in motors. The size and configuration of propellant grain also influenced the pressure exponent. The phenomena are due to the facts that the burning rate is faster in motor tests over the entire range of pressures than in strand tests; at lower pressures the burning rate is considerably lower in strand tests than in motor tests; and the resultant increase in pressure exponent appears in strand tests. Assuming that the pressure exponents of a specified propellant in strand and various types of motors differ, because of difference in flame temperature, two kinds of burning tests were performed for investigating the heat loss effect on the burning rate. In the first test, the kinds of pressurized gases in strand bomb had a negligible effect on the burning rates of propellants. In the second tests, the temperature of chamber wall in motor firing tests had no effects on the propellant burning rate. Those two tests could not explain that the heat loss mechanism was a dominant factor for change in the pressure exponent. Scortia’s experiment shows the decrease in specific impulse efficiency with decreasing the stay time of combustion gas in rocket chambers. Analyzing the relations among the stay time, propellant type and grain shape, the behavior of pressure exponent can be explained qualitatively. Experimental result on characteristic velocity efficiency as a function of pressure and stay time supports the analysis., 資料番号: NALTR0537000, レポート番号: NAL TR-537},
 title = {推力中断型固体ロケット用プロペラントの圧力指数への寸法効果},
 year = {1978}
}