Propellant Flow Actuated Piezoelectric Rocket Engine Igniter

Award Information
National Aeronautics and Space Administration
Award Year:
Phase II
Agency Tracking Number:
Solicitation Year:
Solicitation Topic Code:
Solicitation Number:
Small Business Information
Innovative Engineering Solutions
CA, Murrieta, CA, 92562-7060
Hubzone Owned:
Minority Owned:
Woman Owned:
Principal Investigator:
Mark Wollen
Principal Investigator
(619) 593-7750
Business Contact:
Michael Gruszczynski
Business Official
(951) 951-7600
Research Institution:

Under a Phase 1 effort, IES successfully developed and demonstrated a spark ignition concept where propellant flow drives a very simple fluid mechanical oscillator to excite a piezoelectric crystal. The Phase 1 effort exceeded expectations, with the device demonstrating reliable ignition of both hydrogen and propane fuels, and achieving in excess of 1 million impact cycles (40,000 start cycles) during fatigue testing without measureable degradation. Several spin-off concepts were also identified that provide additional options for improving spark ignition system design. For Phase 2, IES proposes an accelerated, 18 month effort to refine design concepts and analysis tools, and then develop specific ignition system designs for two customer applications, with the intention of having these ignition systems demonstrated in engine ground testing during Phase 2 and ready to start flight qualification immediately following the Phase 2 effort. Both customers (United Launch Alliance and Pratt Whitney Rocketdyne) have expressed interest and commitment in participating in the Phase 2 activity, making engines and facilities available for development testing, and integrating any resulting viable products into their flight engines. The ULA application is a new gaseous bipropellant H2/O2 attitude control thruster, for which the piezoelectric igniter is ideal as a simple, direct ignition source. The PWR application is for an evolved RL-10 study currently underway, for which the piezoelectric system might be scaled up or used as a pilot igniter for a torch, or make use of another spin-off concept that was identified during the Phase 1 effort. The timing of this Phase 2 effort coincides perfectly with near term needs of both these customers, as well as for other small engine applications in work to replace catalytic hydrazine engines with bi-propellant engines that will require a simple and reliable ignition source.

* information listed above is at the time of submission.

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