Lightweight Liquid Target Booster Thrust Chamber Assembly

Award Information
Agency: Department of Defense
Branch: Missile Defense Agency
Contract: FA9300-04-C-0039
Agency Tracking Number: B2-0646
Amount: $479,572.00
Phase: Phase II
Program: STTR
Awards Year: 2004
Solicitation Year: 2003
Solicitation Topic Code: MDA03T-005
Solicitation Number: N/A
Small Business Information
IN SPACE, L.L.C.
P.O. Box 3874, West Lafayette, IN, 47996
DUNS: 132073946
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Benjamin Austin
 General Manager
 (765) 409-0456
 bjaustin@inspacellc.com
Business Contact
 Amy Austin
Title: Business Manager
Phone: (765) 409-0456
Email: 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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