Design, modeling and testing of a O2/CH4 igniter for a hybrid rocket motor

Heightened interest in capable, inexpensive, small satellites has lead to the desire to develop a propulsion system compatible with these small systems. A hybrid rocket propulsion system is currently being developed at JPL for an interplanetary SmallSat application (e.g. orbit insertion with multiple trajectory or orbit correction maneuvers). Hybrids are being considered due to their multiple re-start capabilities, high performance (Isp of about 300 s), and inherent safety (the oxidizer and fuel are separated both physically and by state). This paper focuses on the design of an ignition system to enable multiple starts on the main propulsion system. The ignition system utilizes the main hybrid oxidizer, in this case gaseous oxygen, and gaseous methane (a secondary fuel). Heat from a commercially available spark plug initiates the combustion.