Resonance Igniter for Rocket Engine Ignition
Agency / Branch:
DOD / USAF
The goal of this SBIR is the design and demonstration of an opposed flow acoustic resonance igniter concept that can be applied to a range of rocket propellant combinations. Along with the hardware demonstration, we plan to exercise the analytical tools necessary to model the transient ignition phenomena in both the igniter and the main chamber. The Phase I effort will address several of the key capabilities necessary to complete this demonstration - ignition characteristics of an opposed flow acoustic igniter, transient CFD modeling of heating and ignition in the resonance tube, and CFD modeling of the transient ignition of the main combustor by the igniter exhaust.
Small Business Information at Submission:
SIERRA ENGINEERING, INC.
603 East Robinson Street Suite 7 Carson City, NV 89701
Number of Employees: