Experimental research on rotating detonation with liquid hypergolic propellants

Abstract This paper describes experimental research into the initiation and propagation of rotating detonationfor liquid Nitrogen TetrOxide(NTO) and liquid MonoMethylHydrazine(MMH). An annular rocket-type combustorwithout nozzle was designed to investigate detonationcombustion. The propellants were injected through unlike impingement injectors. The combustion flame fronts and pressure waves were detected using optical diagnostics and dynamic pressuresensors, respectively. The propagation of rotating detonationwas established spontaneously by increasing the mass flow rate of propellants. The velocity of propagation of the flame fronts and pressure waves was nearly equal and reaches supersonic speed. Two different detonationcombustion patterns are present, single wave mode and double waves mode. And in double waves mode, the two detonationwaves are always counter-rotating. The possibility of rotating detonationinitiation in a combustorwith nozzle was also checked. Stable rotating detonationcan be initialized and sustained at similar operating conditions.