Propellant Flow Actuated Piezoelectric Rocket Engine Igniter

Spark ignition of a bi-propellant rocket engine is a classic, proven, and generally reliable process. However, timing can be critical, and the control logic, additional electronic components and wiring adds complexity, cost and weight. These factors can be especially undesirable for small attitude or reaction control engines. The proposed innovation uses a novel method to excite a piezo-ceramic crystal using the initiation of propellant flow to the engine. When the propellant valves are opened, the precise timing of the spark relative to propellant flow, as well as the flow start transient, are governed by the geometry of the device. Hence, precise, repeatable start conditions should be achieved with no additional control logic or complexity. Furthermore, the piezo-ceramic crystal is integral to (and embedded in) the igniter body, thereby completely eliminating external wiring and associated complexity. A bench-top demonstration of one manifestation of the device (incorporating only one very simple moving part) has already demonstrated basic feasibility. Other manifestations with no moving parts what-so-ever (at the macroscopic scale) may also be viable, and will be investigated. Phase 1 TLR advancement goal is from 3 to 5, with Phase 2 goal of 7.

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.

This is early/mid-stage (TRL 5) — the most realistic path in is NASA SBIR/STTR, which funds small businesses and research institutions to develop technology aligned with NASA's needs (equity-free, phased funding). Check whether a current SBIR/STTR solicitation topic overlaps with this project's technology area, or contact the project directly (above) to ask.

None of these are guaranteed paths for this specific project — TechPort itself doesn't have an "apply" button. Reaching out to the contact(s) above with a specific question is usually the fastest way to find out what's actually open.