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Rotating Detonation Rocket Engine

Award Information
Agency: Department of Defense
Branch: Defense Advanced Research Projects Agency
Contract: 140D0423C0065
Agency Tracking Number: D2-2782
Amount: $1,783,659.00
Phase: Phase II
Program: SBIR
Solicitation Topic Code: AF182-064
Solicitation Number: 18.2
Solicitation Year: 2018
Award Year: 2023
Award Start Date (Proposal Award Date): 2023-06-29
Award End Date (Contract End Date): 2025-06-30
Small Business Information
112 Mitchell Blvd
Tullahoma, TN 37388-1111
United States
DUNS: 144158677
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Eric Jacob
 (931) 455-7330
Business Contact
 Paul Gloyer
Phone: (931) 455-7333
Research Institution

Pressure gain combustion (PGC), such as in a rotating detonation engine (RDE), has the potential to increase combustor efficiency up to 10%. This improvement would be valuable to many DoD systems such as thrusters, engines, and power generation units. In an earlier AFRL funded Phase I effort, GTL designed and modeled conceptual liquid injection rotating detonation engine concepts.  By the end of the effort, preliminary hardware designs of these novel combustors had been completed.  In this proposed DARPA phase II effort, these pressure gain combustor designs (i.e., rotating detonation rocket engines) will be finalized, fabricated, and tested.  The results of this testing will provide critical data on pressure gain combustor operation and performance.  The testing will be performed at the University of Tennessee Space Institute (UTSI). This data will complement the RDE work being performed at AFRL, NASA, and others.

* Information listed above is at the time of submission. *

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