Lightweight Liquid Target Booster Thrust Chamber Assembly

Award Information
Agency:
Department of Defense
Branch
Missile Defense Agency
Amount:
$479,572.00
Award Year:
2004
Program:
STTR
Phase:
Phase II
Contract:
FA9300-04-C-0039
Award Id:
69447
Agency Tracking Number:
B2-0646
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
P.O. Box 3874, West Lafayette, IN, 47996
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
132073946
Principal Investigator:
Benjamin Austin
General Manager
(765) 409-0456
bjaustin@inspacellc.com
Business Contact:
Amy Austin
Business Manager
(765) 409-0456
aaustin@inspacellc.com
Research Institution:
Purdue University
William Anderson
315 N. Grant St.,
West Lafayette, IN, 47907
(765) 496-2658
Nonprofit college or university
Abstract
MDA is interested in the development of hydrogen peroxide/hydrocarbon engines for liquid target vehicles. A large reduction in engine weight (~75%) and technical risk are possible by eliminating the large catalyst beds that decompose the hydrogen peroxide before it enters the combustion chamber, providing temperatures that are sufficient for fuel autoignition. A Fastrack Phase II proposal to develop a flight-weight torch igniter design, that uses hydrogen peroxide and hydrocarbons, for a 70,000-lbf thrust liquid target booster engine is provided here. Design requirements will be flowed down from a notional booster engine design during a system requirements review task undertaken in conjunction with Northrop Grumman Space Technology. An existing test facility will be modified for a set of ignition verification tests and igniter optimization tests in a 10,000-lbf thrust subscale thrust chamber. Verification tests will substantiate igniter flowrate and igniter placement by measuring ignition delay in short duration tests using a low-cost expendable chamber. Optimal igniter design and thermal, stability, and performance characteristics will be determined in long-duration runs in an instrumented heat sink chamber. Finally, these data will be used as a basis for the detailed design of a flightweight torch ignition system for the 70,000-lbf thrust engine.

* information listed above is at the time of submission.

Agency Micro-sites


SBA logo

Department of Agriculture logo

Department of Commerce logo

Department of Defense logo

Department of Education logo

Department of Energy logo

Department of Health and Human Services logo

Department of Homeland Security logo

Department of Transportation logo

Enviromental Protection Agency logo

National Aeronautics and Space Administration logo

National Science Foundation logo
US Flag An Official Website of the United States Government