Application of Detonation Waves to Rocket Engine Chamber

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

“…Thrust measurement of the RDE with A ch 640.4 mm 2 , shown in Fig. 2, was conducted by Kasahara et al [19]. This RDE was made of copper (C1100) for thermal conduction purposes.…”

“…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…”

“…We determined the uncertainty of the slope of load cell calibration result by the standard deviation of output voltage. Other mass flow rates and load cell calibration results are available in our other papers [19,29,30]. The testing conditions and the results in this study are summarized in Table 2.…”

“…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.…”

“…Thrust performance of an RDE with converging nozzle (i.e., geometric throat) has been also investigated [19][20][21][22][23]. Kasahara et al [19] explored the performance gain of an RDE with a converging-diverging nozzle and achieved almost the same characteristic exhaust velocity as that of constant-pressure combustion rockets. Frolov et al [20] conducted large-scale RDE thrust measurement and found that attaching a nozzle or reducing the air injection area could increase in the number of detonation waves and thrust.…”