- 一般社団法人 日本航空宇宙学会
- 航空宇宙技術 (ISSN:18840477)
- vol.10, pp.107-112, 2011 (Released:2012-01-17)
We conducted multi-cycle combustion experiments of a coaxial-rotary-valve pulse detonation engine (PDE) system. This PDE system showed a stable operation at the valve rotating frequencies of 5.0, 10, 15, 20, and 33 Hz. We successfully measured propellant mass flow rates, thrusts, and specific impulses in the 2-sec operation duration. The maximum thrust was 32 N at the operation frequency of 33 Hz and at the supply pressure of 0.98 MPa. The maximum specific impulse was 250 sec at the operation frequency of 33 Hz and at the supply pressure of 0.69 MPa. The partial fill ratio was varied from 0.07 to 1.14. The partial fill effect was almost identical to the previous model calculations.