A liquid bipropellant rotating detonation rocket engine was successfully test fired. The 6.5-in.-diam engine operates on a mixture of rocket-grade hydrogen peroxide and triglyme. Ignition is accomplished hypergolically, with the addition of a promoter to the fuel. Eight cases of spontaneously initiated, single-wave, rotating detonations were observed. Detonation wave speeds were near or exceeding Chapman–Jouguet calculations. Evidence of condensed-phase reactions was also seen, damaging hardware in short order. Both a rotating detonation and a bulk-slapping mode characterized the engine operation.
Experimental Study of a Hypergolically Ignited Liquid Bipropellant Rotating Detonation Rocket Engine
Journal of Propulsion and Power ; 36 , 6 ; 851-861
2020-11-01
Conference paper , Article (Journal)
Electronic Resource
English