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
Agency Tracking Number:
B2-0646
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
IN SPACE, L.L.C.
P.O. Box 3874, West Lafayette, IN, 47996
Hubzone Owned:
N
Socially and Economically Disadvantaged:
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.

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