TY - JOUR
T1 - Flight validation of a rotary-valved four-cylinder pulse detonation rocket
AU - Matsuoka, Ken
AU - Morozumi, Tomohito
AU - Takagi, Syunsuke
AU - Kasahara, Jiro
AU - Matsuo, Akiko
AU - Funaki, Ikkoh
PY - 2016
Y1 - 2016
N2 - A rotary-valved four-cylinder pulse detonation rocket engine system, Todoroki II, was developed, in which two novel techniques, the use of an inflow-driven motor and an inverted oxidizer cylinder, were introduced. The total length of the system was 1910 mm; its total weight when filled with ethylene-nitrous-oxide propellant and helium purge gas was 32.5 kg; and the engine weight was 9.6 kg.In aground firing test withadurationof 1500 ms, a thrust-toengine-weight ratio of 2.7 was achieved. Thus, it was demonstrated that a multicylinder pulse detonation rocket engine system can be used as a practical thrust mechanism. Using a launch and recovery system, a flight-simulating test was conducted to evaluate the features and viability of the engine design. The launch and recovery system operated perfectly, and Todoroki II reached a height of about 9.7 m. The operation of the pulse detonation rocket engine under conditions simulating real vertical flight without constraint forces with a duration of about 1200ms and a thrust-to-engine-weight ratio of 2.5 was demonstrated. No serious impact of the vibration caused by the pulse detonation rocket engine operation or the rotation of the rotary valve on the flight was observed.
AB - A rotary-valved four-cylinder pulse detonation rocket engine system, Todoroki II, was developed, in which two novel techniques, the use of an inflow-driven motor and an inverted oxidizer cylinder, were introduced. The total length of the system was 1910 mm; its total weight when filled with ethylene-nitrous-oxide propellant and helium purge gas was 32.5 kg; and the engine weight was 9.6 kg.In aground firing test withadurationof 1500 ms, a thrust-toengine-weight ratio of 2.7 was achieved. Thus, it was demonstrated that a multicylinder pulse detonation rocket engine system can be used as a practical thrust mechanism. Using a launch and recovery system, a flight-simulating test was conducted to evaluate the features and viability of the engine design. The launch and recovery system operated perfectly, and Todoroki II reached a height of about 9.7 m. The operation of the pulse detonation rocket engine under conditions simulating real vertical flight without constraint forces with a duration of about 1200ms and a thrust-to-engine-weight ratio of 2.5 was demonstrated. No serious impact of the vibration caused by the pulse detonation rocket engine operation or the rotation of the rotary valve on the flight was observed.
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U2 - 10.2514/1.B35739
DO - 10.2514/1.B35739
M3 - Article
AN - SCOPUS:84962839117
VL - 32
SP - 383
EP - 391
JO - Journal of Propulsion and Power
JF - Journal of Propulsion and Power
SN - 0748-4658
IS - 2
ER -