HYBRID COWL LEADING EDGE FOR HYPERSONIC FLIGHT SYSTEMS

Award Information
Agency:
Department of Defense
Branch
Air Force
Amount:
$70,000.00
Award Year:
1990
Program:
SBIR
Phase:
Phase II
Contract:
n/a
Agency Tracking Number:
9488
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
Atss Inc.
625 E Carnegie Dr Ste 115, San Bernardino, CA, 92408
Hubzone Owned:
N
Socially and Economically Disadvantaged:
N
Woman Owned:
N
Duns:
n/a
Principal Investigator:
Henry L Moody
(714) 889-2562
Business Contact:
() -
Research Institution:
n/a
Abstract
ENGINE INLETS FOR HYPERSONIC VEHICLES ARE CRITICAL TECHNOLOGY AREAS BECAUSE OF THE POSSIBLE OCCURANCE OF SHOCKWAVE IMPINGEMENT, THE NEED FOR SHARP LEADING EDGE RADII AND THE REQUIREMENT OF MULTIMISSION USE. THIS STUDY PROPOSES THE DESIGN AND DEVELOPMENT OF AN ENGINE INLET LEADING EDGE CONCEPT THAT CAN ACCOMMODATE THE HIGH HEAT FLUXES INDUCED BY HYPERSONIC ASCENT/REENTRY HEATING AND THE OCCURANCE OF AUGMENTED HEATING INDUCED BY THE IMPINGEMENT OF A FOREBODY-GENERATED SHOCKWAVE. THE DESIGN IS BASED ON A HYBRID CONCEPT THAT UTILIZES BOTH TRANSPIRATION AND INTERNAL IMPINGEMENT COOLING TO MINIMIZE THE AMOUT OF COOLANT THAT IS INJECTED INTO THE EXTERNAL BOUNDARY LAYER THAT COULD OTHERWISE BE USED IN THE PROPULSION SYSTEM. INNOVATIVE DESIGN AND MATERIAL CONSTRUCTION METHODS ARE USED TO GENERATE A LEADING EDGE WITH THE STRENGTH AND INTERNAL POROSITY NECESSARY TO ACCOMMODATE THE AEROHEATING AND STRUCTURAL LOADS.

* information listed above is at the time of submission.

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