Continuous Detonation Rocket and Air Breathing Engines

Award Information
Agency: Department of Defense
Branch: Defense Advanced Research Projects Agency
Contract: W31P4Q-11-C-0075
Agency Tracking Number: 08SB2-0890
Amount: $1,475,020.00
Phase: Phase II
Program: SBIR
Awards Year: 2010
Solicitation Year: 2008
Solicitation Topic Code: SB082-059
Solicitation Number: 2008.2
Small Business Information
P.O. Box 2585, 16307 NE 83rd Street, Redmond, WA, -
DUNS: 089115922
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 RIchard Smith
 Principal Investigator
 (425) 881-3635
Business Contact
 Thomas Groudle
Title: Managing Director
Phone: (425) 881-3635
Research Institution
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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