THERMO-CHEMICAL-STRUCTURAL ANALYSIS OF CARBON-PHENOLICS WITHPORE PRESSURE AND PYROLYSIS EFFECTS

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$50,000.00
Award Year:
1991
Program:
SBIR
Phase:
Phase I
Contract:
n/a
Agency Tracking Number:
16896
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
Pda Engineering
2975 Redhill Ave, Costa Mesa, CA, 92626
Hubzone Owned:
N
Socially and Economically Disadvantaged:
N
Woman Owned:
N
Duns:
n/a
Principal Investigator:
() -
Business Contact:
() -
Research Institution:
n/a
Abstract
CARBON-PHENOLIC (C/PH) COMPOSITES HAVE BEEN WIDELY USED IN SOLID ROCKET MOTORS DESPITE THE FACT THAT THEIR HIGH-TEMPERATURE, THERMOSTRUCTURAL BEHAVIOR IS NOT WELL UNDERSTOOD. MANY OF THE FAILURE MODES (E.G., WEDGE-OUT, PLY-LIFT, DELAMINATION, POCKETING) COMMONLY SEEN IN THE C/PHCOMPONENTS OF FIRED SRM NOZZLES CAN ONLY BE EXPLAINED AS PORE-PRESSURE-INDUCED PHENOMENA THAT OCCUR DURING PYROLYSIS. YET, CURRENT THERMOSTRUCTURAL ANALYSIS METHODS ARE INCAPABLE OF ACCURATELY PREDICTING THE HIGH HEATING RATE BEHAVIOR OF SIMPLE C/PH TEST SPECIMENS, LET ALONE ACCURATELY CHARACTERIZING THE PORE PRESSURE AND PYROLYSIS BEHAVIOR OF AN ACTUAL MOTOR NOZZLE. THIS PROJECT ADDRESSES THE PROBLEM OF ACCURATELY CHARACTERIZING THE THERMOSTRUCTURAL BEHAVIOR OF C/PH SUBJECTED TO A HIGH-TEMPERATURE AND HEATING-RATE ENVIRONMENT AS TYPICALLY FOUND IN A SOLID ROCKET MOTOR. THIS WILL BE ACCOMPLISHED BYUSING A VOLUME-BASED CONTINUITY MODEL TO COUPLE THE THERMO-CHEMICAL TO THE THERMOSTRUCTURAL ANALYSIS. THIS UNIQUE APPROACH MODELS THE PORE-PRESSURE DEVELOPMENT DURING PYROLYSIS MORE ACCURATELY THAN CURRENT ANALYTICAL METHODS SINCE IT COUPLES THE PORE-PRESSURE LEVEL DIRECTLY TO THE STRUCTURAL DEFORMATIONS. CARBON-PHENOLIC (C/PH) COMPOSITES HAVE BEEN WIDELY USED IN SOLID ROCKET MOTORS DESPITE THE FACT THAT THEIR HIGH-TEMPERATURE, THERMOSTRUCTURAL BEHAVIOR IS NOT WELL UNDERSTOOD. MANY OF THE FAILURE MODES (E.G., WEDGE-OUT, PLY-LIFT, DELAMINATION, POCKETING) COMMONLY SEEN IN THE C/PHCOMPONENTS OF FIRED SRM NOZZLES CAN ONLY BE EXPLAINED AS PORE-PRESSURE-INDUCED PHENOMENA THAT OCCUR DURING PYROLYSIS. YET, CURRENT THERMOSTRUCTURAL ANALYSIS METHODS ARE INCAPABLE OF ACCURATELY PREDICTING THE HIGH HEATING RATE BEHAVIOR OF SIMPLE C/PH TEST SPECIMENS, LET ALONE ACCURATELY CHARACTERIZING THE PORE PRESSURE AND PYROLYSIS BEHAVIOR OF AN ACTUAL MOTOR NOZZLE. THIS PROJECT ADDRESSES THE PROBLEM OF ACCURATELY CHARACTERIZING THE THERMOSTRUCTURAL BEHAVIOR OF C/PH SUBJECTED TO A HIGH-TEMPERATURE AND HEATING-RATE ENVIRONMENT AS TYPICALLY FOUND IN A SOLID ROCKET MOTOR. THIS WILL BE ACCOMPLISHED BYUSING A VOLUME-BASED CONTINUITY MODEL TO COUPLE THE THERMO-CHEMICAL TO THE THERMOSTRUCTURAL ANALYSIS. THIS UNIQUE APPROACH MODELS THE PORE-PRESSURE DEVELOPMENT DURING PYROLYSIS MORE ACCURATELY THAN CURRENT ANALYTICAL METHODS SINCE IT COUPLES THE PORE-PRESSURE LEVEL DIRECTLY TO THE STRUCTURAL DEFORMATIONS.

* information listed above is at the time of submission.

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