EFFECT OF BOOSTER ACCELERATION ON INSULATOR EROSION

Award Information
Agency:
Department of Defense
Branch
Air Force
Amount:
$207,000.00
Award Year:
1990
Program:
SBIR
Phase:
Phase II
Contract:
n/a
Award Id:
9471
Agency Tracking Number:
9471
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
130 Kifer Ct, Sunnyvale, CA, 94086
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
n/a
Principal Investigator:
Charles Powars
(408) 245-3200
Business Contact:
() -
Research Institute:
n/a
Abstract
DATA FROM RECOVERED ROCKET MOTORS HAS CONVINCINGLY SHOWN THAT MORE CHARRING/EROSION OCCURS ON FORWARD DOME INSULATION DURING FLIGHT THAN IN STATIC FIRING. THE PROBLEM OF FLIGHT AMPLIFICATION OF CHARRING/EROSION HAS GREATLY INCREASED TO COMPLEXITY OF THE DESIGN PROCESS FOR FUTURE ROCKET MOTORS, ESPECIALLY THOSE SUBJECTED TO HIGH ACCELERATION. LARGE SAFETY FACTORSMUST OFTEN BE APPLIED RESULTING IN THICK, HEAVY INSULATION WITH UNCERTAIN RELIABILITY. A MECHANISTIC MODEL COUPLED WITH NEW LABORATORY TEST METHODS ARE NEEDED TO PROVIDE A METHODOLOGY WHICH CAN BE RELIABLY USED TO SCREEN NEW METHODS. THIS PHASE I PROGRAM WILL DEMONSTRATE A RELATIVELY SIMPLE LABORATORY TEST TECHNIQUE WHICH PROMISES TO CLARIFY THE DOMINANT MECHANISMS GOVERNING THE FLIGHT AMPLIFICATION PROBLEM. THE TECHNIQUE EMPLOYS A SMALL WIND TUNNEL COMBINING RADIATIVE HEATING AND OSCILLATORY ACCELERATION OF THE TEST SAMPLE TO ALLOW INDEPENDENT VARIATION OF EACH CRITICAL PARAMETER. BY INDEPENDENTLY VARYING EACH PARAMETER WE CAN DETERMINE THE RELATIVE IMPORTANCE OF EACH ONE, AND WHICH ONES ARE DOMINANT. ULTIMATELY DATA FROM THESE SIMPLE TESTS, PULSE DATA FROM MORE COMPREHENSIVE TESTS, CAN BE COUPLED TO WELL VALIDATED COMPUTER MODELS, SUCH AS THE CHARRING MATERIALS ABLATOR (CMA) CODE, TO PRODUCE A RELIABLE PREDICTIVE TOOL.

* information listed above is at the time of submission.

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