The igniter proposed is applicable to virtually any non-NASA rocket engine application, as well as having application as an ignition source for commercial or military gas turbine engines, or anywhere that an ignition source is required to coincide with the initiation of fuel flow (e.g. flame throwers, flare stacks, industrial gas heaters).
Reliable and simplified ignition sources are critical for virtually all bi-propellant rocket engines. The proposed innovation has the potential to provide a reliable, properly timed ignition source for new rocket engines, as well as being a potential retrofit option to replace costly or complex igniters on currently operational engines. The technology is applicable to virtually any size engine, from attitude control to main booster engine scale. For small RCS engines, it is particularly suitable due to its simplicity, potentially very small size, and ability to repetitively generate a reliable, well timed ignition source.