Resonance Igniter for Rocket Engine Ignition

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA9300-08-M-3018
Agency Tracking Number: F081-066-0999
Amount: $99,971.00
Phase: Phase I
Program: SBIR
Awards Year: 2008
Solicitation Year: 2008
Solicitation Topic Code: AF081-066
Solicitation Number: 2008.1
Small Business Information
603 East Robinson Street, Suite 7, Carson City, NV, 89701
DUNS: 006620553
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Jeffrey Muss
 Senior Staff
 (916) 363-6161
Business Contact
 Margo Hornung
Title: Corporate Secretary / Administrator
Phone: (775) 888-9122
Research Institution
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.

* Information listed above is at the time of submission. *

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