Thrust Validation of Rotating Detonation Engine System by Moving Rocket Sled Test

Abstract

This Paper presents the results of a rotating detonation engine rocket sled test demonstration on a 127 mm gauge rail at 100 m long high-speed running track test equipment to evaluate the thrust performance of a stand-alone rotating detonation engine propulsion system. The developed sled test demonstrator contained all onboard subsystems, including engine, gas cylinders, valves, controller, and a data logger. The sled test demonstrator successfully generated thrust, and three or four detonation waves of 1460 to 1800 m∕s were observed during the 2.0 s burn time. The measured specific impulse in the sled test was 144 s as estimated from the acceleration of the demonstrator and the mass decrease in the onboard cylinders. The test results were compared with the data from a laboratory-stand firing test using a load cell, and the specific impulses of the sled test were found to be comparable to the results of the stand firing test.

Numerical simulations of a hydrogen-air pre-detonator for detonation engines

“…As the reported thermal efficiency for the near constant volume combustion (in pressure gain combustor) is 20% more than the constant pressure combustion in a thermodynamic cycle such as Brayton cycle, detonation wave engines have become the natural choice for the futuristic systems. A moving rocket sled test has been performed by Goto et al 5 for a RDE integrated with a spike nozzle which generated a specific impulse of 144 s with 3-4 detonations waves of velocity 1460-1800 m/s. RDE is being evaluated for Rocketdyne's RL-10 rocket and upper stages of Delta IV and Atlas V rockets.…”

Sensors Layout Optimization Design of Rocket Sled Test System

“…Wang et al [ 13 ] found that in the flow field of the anti-D-shaped rocket sled, the unsteady large-scale vortex and shock motions appeared due to the strong momentum transfer, and the axisymmetric geometry was suitable for the rocket sled. A rocket sled test with a rotating detonation engine (RDE) was conducted by Goto et al [ 14 ]. The combustor pressure and the specific impulse of the sled test were comparable to the results of the laboratory stand firing test using a load cell.…”

Effects of inlet and secondary flow conditions on the flow field of rotating detonation engines with film cooling

“…In addition, Journell et al [12] analyzed the combustion process of the RDE operating at working conditions similar to gas turbines by means of chemiluminescence and particle image velocimetry (PIV). Goto et al [13] conducted a rocket sled test for the thrust performance assessment of an RDE with an inner diameter of 60.5 mm. Thrust was generated for 2 seconds and a specific impulse of 144 s was measured.…”