Study on a Long-time Operation Towards Rotating Detonation Rocket Engine Flight Demonstration

Propulsive Performance and Heating Environment of Rotating Detonation Engine with Various Nozzles

“…Mass decrease was determined by electric balance or the decrease in internal tank pressure. For some longer-duration tests, mass flow rate calibration was done [19,29,30]. Actual mass flow rate _ m could be calculated by…”

“…The propulsive performance of RDE and PDE have been widely investigated by many institutions [6,7,9,[12][13][14][15][16][17][18][19][20][21][22][23]29,30]. Kindracki et al [12] measured the thrust and specific impulse of RDE under 0.5 bar.…”

“…Even though an RDE could be operated without a throat, highheat-load problems were not inevitable. High-frequency analysis of heat flux [24] and steady-state analysis [25,26,28,29] of RDE have been conducted. Theuerkauf et al [24] developed a high-frequency response heat-flux gauge and revealed periodic heat flux in RDE caused by the rotating detonation wave.…”

“…Ishihara et al [29] conducted RDE combustion tests without cooling for 6-10 s using heat-resistant material, a carbon-carbon composite (C/C). They measured heat flux and thrust simultaneously, but after the test, they observed C/C damage caused by oxidization [29].…”

“…Ishihara et al [29] conducted RDE combustion tests without cooling for 6-10 s using heat-resistant material, a carbon-carbon composite (C/C). They measured heat flux and thrust simultaneously, but after the test, they observed C/C damage caused by oxidization [29]. Using heat-resistant material is one possible solution for protecting the combustor wall, but the problem could hinder longer combustion and potentially reduce RDE performance due to the loss of oxidizer entering the combustor.…”