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

Antonietta Conte, Jason Rabinovitch, Elizabeth Jens, Ashley Chandler Karp, Barry Nakazono, David A. Vaughan

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

9 Scopus citations

Abstract

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.

Original languageEnglish
Title of host publication2018 Fluid Dynamics Conference
DOIs
StatePublished - 2018
Event48th AIAA Fluid Dynamics Conference, 2018 - Atlanta, United States
Duration: 25 Jun 201829 Jun 2018

Publication series

Name2018 Fluid Dynamics Conference

Conference

Conference48th AIAA Fluid Dynamics Conference, 2018
Country/TerritoryUnited States
CityAtlanta
Period25/06/1829/06/18

Fingerprint

Dive into the research topics of 'Design, modeling and testing of a O2/CH4 igniter for a hybrid rocket motor'. Together they form a unique fingerprint.

Cite this