Description: The technical innovation proposed here is the introduction of torch-augmented spark ignition for high performance liquid oxygen (LOX) / propylene rocket engines now in development for a future two-stage nanosat launch vehicle. Spark ignition is critical for reliably achieving multiple in-flight restarts of NLV upper stage engines. In addition, this new capability will generate immediate R&D benefits through the streamlining of ongoing LOX/propylene engine testing. By replacing pyrotechnic charges that are the current state-of-the-art method for LOX/propylene engine ignition, spark igniters eliminate the need to install fresh units after each test attempt (a manually intensive and tedious process). Additional operational benefits from eliminating a category of pyrotechnics and ordnance will accrue in logistics and safety.

Benefits: In the near-term, the application of this spark igniter technology to static fire testing to replace pyrotechnic devices will improve the efficiency of NASA-sponsored research investigating high performance LOX/propylene rocket engines. Subsequent application in the upper stages of nanosat launch vehicles will enable multiple in-flight engine restart, a necessity for optimizing orbit insertion for CubeSat-class payloads. Typical program users that will benefit from this capability include the CubeSat Launch Initiative and the Educational Launch of Nanosatellites (ELaNa) program.

A two-stage nanosat launch vehicle now in development by GSC which features LOX/propylene propulsion will benefit directly with the application of this spark ignition technology in both stages. Another candidate application is a derivative upper stage now in preliminary development for the DARPA XS-1 experimental space plane.