Continuous Detonation Rocket and Air Breathing Engines

Award Information
Agency:
Department of Defense
Branch
Defense Advanced Research Projects Agency
Amount:
$1,123,929.00
Award Year:
2010
Program:
SBIR
Phase:
Phase II
Contract:
W31P4Q-11-C-0075
Award Id:
91852
Agency Tracking Number:
08SB2-0890
Solicitation Year:
n/a
Solicitation Topic Code:
DARPA 08-059
Solicitation Number:
n/a
Small Business Information
P.O. Box 2585, 16307 NE 83rd Street, Redmond, WA, -
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
089115922
Principal Investigator:
RIchardSmith
Principal Investigator
(425) 881-3635
ghkneng@verizon.net
Business Contact:
ThomasGroudle
Managing Director
(425) 881-3635
ghkneng@verizon.net
Research Institute:
n/a
Abstract
GHKN Engineering, LLC teamed with Aerojet Recmond, proposes to build and test a CDRE with a number of fuels and oxidizers. Included in the proposal test program is thrust measurement, which together with mass flow measurement will be used to evalute CDRE performance, (and efficiency), of detonation combustion in these devices. The engine planned for testing was designed by GHKN under the Phase I program and will be fabricated by GHKN and hot fire tested at Aerojet's Redmond, Washington rocket test facility. The innovative CDRE design allows testing of multiple injector and mixing configurations. The CDRE tests using pure oxygen or other oxidizers are viewed as a stepping stone to testing of larger air breathing CDE designs which require larger and more elaborate test facilities. The Phase II program is intended to require two years to complete.

* information listed above is at the time of submission.

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