An investigation on a novel coaxial micro-rocket injector.

摘要

The development process of sub kilogram class missile interceptors will greatly benefit from the advancement of power MEMS based propulsion systems. The envisioned concept and technology for this class of interceptors are a package of 20--40 miniature kill vehicles (MKVs) each the size of a softball and weighing less than two kilograms. Suggested MKV design could be utilized with liquid bipropellant propulsion systems because of higher effectiveness, better range, maneuverability, and kill performance. Successful miniaturization of liquid propulsion components demands a more complete and broader understanding of micro-fluid dynamics and micro-combustion phenomena associated with the micro-injector design.; This thesis numerically investigated novel coaxial micro-rocket injector phenomena with changing physical variables such as inlet pressure changes, different orifice size and number by fixing the injector area, and various impinging angles. Non-turbulent streamlines (particles paths) and mixing behavior have been studied through the use of STAR-CD. Similar streamline behavior was observed when inlet pressure varied, however orifice configuration highly influenced the streamline behavior. The diversified streamlines occurring at the end of combustion chamber were further investigated where it was observed that diversification increased with smaller orifice diameter. The penetration length of both oxygen and RP1 increased greatly when the inlet pressure rose, where oxygen always traveled further than RP1 in the chamber. Conversely, by increasing the number of orifices, spray penetration decreased for both RP1 and oxygen in the chamber.