TRANSTRAIN: A program to compute strain transformations in composite materials
Over the years, the solid rocket motor community has made increasing use of composite materials for thermal and structural applications. This is particularly true of solid rocket nozzles, which have used carbon phenolic and, increasingly, carbon-carbon materials to provide structural integrity and thermal protection at the high temperatures encountered during motor burn. To evaluate the degree of structural performance of nozzles and their materials and to verify analysis models, many subscale and full-scale tests are run. These provide engineers with valuable data needed to optimize design and to analyze nozzle hardware. Included among these data are strains, pressures, thrust, temperatures, and displacements. Recent nozzle test hardware has made increasing use of strain gauges embedded in the carbon composite material to measure internal strains. In order to evaluate strength, these data must be transformed into strains along the fiber directions. The fiber-direction stresses can then be calculated. A computer program written to help engineers correctly manipulate the strain data into a form that can be used to evaluate structural integrity of the nozzle is examined.
- Research Organization:
- National Aeronautics and Space Administration, Huntsville, AL (USA). George C. Marshall Space Flight Center
- OSTI ID:
- 6194319
- Report Number(s):
- N-90-27877; NASA-TM-103509; NAS-1.15:103509
- Country of Publication:
- United States
- Language:
- English
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