@article{oai:tsukuba.repo.nii.ac.jp:00026935,
 author = {笠原, 次郎 and Kasahara, Jiro and Hirano, Masao and Matsuo, Akiko and Daimon, Yu and Endo, Takuma},
 issue = {6},
 journal = {Journal of propulsion and power},
 month = {Nov},
 note = {In the present research, we experimentally verified the partial-fill effect in a multicycle pulse detonation rocket
engine. The intermittent thrust of a pulse detonation rocket engine was measured by using a spring-damper
mechanism that smoothed this intermittent thrust in the time direction. The intermittent mass flow rates were
assessed by gas cylinder pressure or mass difference measurement. The maximum specific impulse was 305   9 s at
an ethylene and oxygen propellant fill fraction of 0:130   0:004. When the fill fraction was greater than 0.130, the
specific impulse was increased as the partial-fill fraction was decreased. When the fill fraction was less than 0.130, the
specific impulse was sharply decreased as the partial-fill fraction was decreased. This decrease was due to diffusion
between propellant and purge gases and the short length of the transition from deflagration to detonation. The
multicycle pulse detonation rocket engine had a partial-fill effect that may have been mainly due to the suctioned air
and was consistent with the single-cycle partial-fill model of Endo et al.},
 pages = {1281--1290},
 title = {Thrust Measurement of a Multicycle Partially Filled Pulse Detonation Rocket Engine},
 volume = {25},
 year = {2009}
}