Injector Stability Screening Technique (ISST)

Award Information
Agency:
Department of Defense
Amount:
$100,000.00
Program:
SBIR
Contract:
FA9300-09-M-3005
Solitcitation Year:
2008
Solicitation Number:
2008.3
Branch:
Air Force
Award Year:
2009
Phase:
Phase I
Agency Tracking Number:
F083-112-0551
Solicitation Topic Code:
AF083-112
Small Business Information
Orbital Technologies Corporation (ORBITE
Space Center, 1212 Fourier Drive, Madison, WI, 53717
Hubzone Owned:
N
Woman Owned:
N
Socially and Economically Disadvantaged:
N
Duns:
196894869
Principal Investigator
 Ryan Cavitt
 Propulsion Engineer
 (608) 229-2807
 cavittr@orbitec.com
Business Contact
 Eric Rice
Title: President and CEO
Phone: (608) 229-2730
Email: knaufs@orbitec.com
Research Institution
N/A
Abstract
ORBITEC proposes to demonstrate and validate a laboratory scale experimental injector stability screening technique which will quantify injector element stability characteristics.  The experimental approach promises to dramatically reduce development cost by utilizing a gaseous single element test facility which presents savings in hardware manufacturing, consumables such as propellant and test personnel.  The simple test facility will allow rapid stability characterization of multiple candidate injectors which will be unobtrusive to schedule requirements.  The key cost and time savings will be fewer full scale hardware configurations that must be manufactured which will in turn reduce the number of full scale tests required for qualification.  The Phase 1 effort will evaluate the DoD plans for next generation engine development.  The scaling technique will be applied to establish operating conditions for the laboratory scale burner and large-scale thrust chamber.  Correlation between laboratory scale and full scale experimental data will be conducted subsequently.  Upon validation, Phase 2 work plans will be developed to improve the screening technique. BENEFITS: The end product of this overall research and validation effort will create an experimental test facility and technique which will decrease engine development time at a reduced cost.  The scaling technique will have application to virtually all high pressure liquid rocket engine development programs and existing engine upgrades for the Air Force, Navy, MDA, NASA and their contractors as well as commercial satellite launch companies.  Development may reveal application to the screech phenomenon in air-breathing engines which will significantly open the commercial aircraft sector.

* information listed above is at the time of submission.

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