Experimental investigations on detonability limits of pulse detonation rocket engine

The duty cycle for C₁₀H₁₉/oxygen injection and time sequence for injection, mixing and ignition to produce two-phase, fully-developed detonations are investigated in a pulse detonation rocket engine (PDRE) model. The The PDRE test model is 25mm in inner diameter and l.lm long. The solenoid valves are employed to control intermittent supplies of propellants and purge gas. The spark igniter has ignition energy of around 50mJ. The solenoid valves and igniter are controlled by a control system. Under some given supply conditions, the detonability limits in terms of injection duty cycle and the controlling method are obtained. From fundamental analysis, these factors influence the operation of PDRE essentially by appropriate equivalence ratio and mixing. The experimental results show that to gain reliable detonations, first of all, the injection duty cycles for C₁₀H₁₉ and oxygen should ensure sufficient filling and then the injection time phases and duty cycles should be kept as close as possible to attain effective mixing.