A Variable Thurst Detonation Wave Engine, DWE, for Mach 0 to 3 Applications

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: N/A
Agency Tracking Number: 20249
Amount: $59,986.00
Phase: Phase I
Program: SBIR
Awards Year: 1993
Solicitation Year: N/A
Solicitation Topic Code: N/A
Solicitation Number: N/A
Small Business Information
5301-a North Commerce Avenue, Moorpark, CA, 93021
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Joseph W. Humphrey
 (805) 523-2585
Business Contact
Phone: () -
Research Institution
This proposal describes a novel, high thrust density Detonation Wave Engine (DWE) applicable to the Mach range of 0 to 3. The geometry of this novel engine concept naturally provides for integration into a new Combined Cycle Engine with Ramjets. The concept is an intermittent combustion jet engine that harnesses travelling detonation waves to accomplish compression and chemical reaction. The goal is to obtain an engine which operates in the Mach 0 to 3 range, integrates well with Ramjets to form a high performance combined Cycle Engine, and has low weight penalty. The Detonation Wave Engine through the controlled use of the strong gasdynamic waves can be configured to provide both engine aspiration (i.e. static thrust) and relatively high charge compression. These result in several potential benefits from DWE's includng 1) high thrust density, 2) high specific impulse, 3) significant static thrust, 4) natural geometry for integration into a Combined Cycle Engine, and 5) low cost. This project will in Phase I develop the cycle analysis tools for analyzing this unsteady combustion device complete with finite rate chemistry, determine essential engine configuration, provide the necessary tool to design tools to determine a Proof of Concept demonstration, and define the Proof of Concept demonstration to show performance and feasibilty. Phase II will conduct the Proof of Concept demonstration.

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

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