Oblique Detonation Wave Hy-Scram Engine for Hypersonic Propulsion Applications

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: N/A
Agency Tracking Number: 22754
Amount: $70,000.00
Phase: Phase I
Program: SBIR
Awards Year: 1994
Solicitation Year: N/A
Solicitation Topic Code: N/A
Solicitation Number: N/A
Small Business Information
Advanced Projects Research,
5301 North Commerce Avenue,, Suite A, Moorpark, CA, 93021
DUNS: N/A
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Joseph W. Humphrey
 (805) 523-2585
Business Contact
Phone: () -
Research Institution
N/A
Abstract
The Oblique Detonation Wave Hypervelocity Scramjet (ODW Hy-Scram) Engine is applicable to hypersonic flight vehicles that require high Mach Scramjet operation. This project will implement a unique new analysis capability to analyze and assess a novel propulsion device that could greatly enhance applications in the hypersonic class of flight vehicles. The ODW Hy-Scram Engine is configured to use gas dynamic wave interactions to provide inlet stream primary compression (after vehicle forebody compression), bulk ignition, and rapid combustion. The major advantages over previous Scramjet engines are: 1) use of the vehicle forebody for fuel injection and complete mixing (due to longer distances, lower temperatures and lower pressures than is typical in the inlet fuel injection systems of Scramjet Engines), 2) simpler and shorter inlet design due to lower Mach range through which the flow must be decelerated (typically incorporated into the vehicle forebody), and 3) shorter and simpler combustor design. The primary benefit of this approach is the reduction of the weight associated with the propulsion system for a given combustion efficiency. The secondary benefit is stabilized combustion due to the bulk ignition of the fuel and oxidizer in the stable over driving of the oblique detonation wave.

* information listed above is at the time of submission.

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