Very High Altitude Propulsion System (HDAT)

Award Information
Agency:
Department of Defense
Branch
Defense Advanced Research Projects Agency
Amount:
$809,718.00
Award Year:
2008
Program:
SBIR
Phase:
Phase II
Contract:
W31P4Q-09-C-0066
Agency Tracking Number:
07SB2-0645
Solicitation Year:
2007
Solicitation Topic Code:
SB072-045
Solicitation Number:
2007.2
Small Business Information
AURORA FLIGHT SCIENCES CORP.
9950 Wakeman Drive, Manassas, VA, 20110
Hubzone Owned:
N
Socially and Economically Disadvantaged:
N
Woman Owned:
N
Duns:
604717165
Principal Investigator:
Timothy Dawson-Townsend
Program Manager
(617) 500-4812
tdt@aurora.aero
Business Contact:
Diana Eichfeld
Contracts Manager
(703) 396-6329
deichfeld@aurora.aero
Research Institution:
n/a
Abstract
TBDThere is interest in unmanned aircraft that can be deployed to a target via unconventional means and operate at high altitudes for extended periods. A key technology required for such an aircraft is a propulsion system capable of providing the required thrust while meeting stringent requirements. Due to method for deployment, the propulsion system is required to meet several additional requirements including; ability to be stored for long durations, the need to deploy, and remain on station for at least seven hours. Due to the hostile locations the UAV will operate under the ability to fly at higher altitudes and at higher Mach increases the overall survivability and military utility of the vehicle. In the execution of the Phase I program Aurora showed the feasibility of the Hydrazine Decomposition Air Turbine engine to meet the requirements of a HALE aircraft while providing the required additional features. The HDAT engine can provide over any of the other systems evaluated the ability to operate at higher altitudes and at higher vehicle Mach numbers. Phase II intends to build directly upon this success by delving in to the subsystems that make up the HDAT engine, and reducing technical risk through testing and analysis.

* information listed above is at the time of submission.

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