@techreport{oai:jaxa.repo.nii.ac.jp:00044951,
 author = {新岡, 嵩 and 三谷, 徹 and 高橋, 守 and 泉川, 宗男 and NIIOKA, Takashi and MITANI, Toru and TAKAHASHI, Mamoru and IZUMIKAWA, Muneo},
 month = {Jan},
 note = {Ignition experiments of the solid propellant rocket motor were made to obtain fundamental aspects of the aft-end ignition performance. First, flame propagation phenomenon on the propellant surface (15 mm wide and 100 mm long) were investigated by changing the external gas-flow velocity, composition and temperature. Secondly, the pressure histories during ignition of the 100mm diameter rocket motor were measured for the fore-end and the aft-end igniter system. It is confirmed by these two experiments that the pressure output rate in the ignition transient of the rocket motor is closely related to the flame propagation speed, but not to the ignition, which is inherent in the propellant and is determined only by the amount of heat-flux. The reason why the pressure rise of the aft-end ignition is a low rate compared with the fore-end ignition is explained by the difference of the propagation mechanism which may control the ignition performance of the motor. That is to say, flame propagation in the fore-end ignition system is performed by a forward (streamwise) propagation in which the directions of propagation and combustion gas flow are the same, but that in the aft-end ignition is done by a backward (opposite) propagation. Moreover, the ignition transient of the radial slot grain is compared with that of an axial slot grain, using both igniter systems., 資料番号: NALTR0694000, レポート番号: NAL TR-694},
 title = {Experiments on the Aft-end Ignition of Solid Propellant Rocket},
 year = {1982}
}