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Hot/Wet Open Hole Compression Strength of Carbon/Epoxy Laminates for Launch Vehicle Applications
| AUTHOR | Administration (Nasa), National Aeronaut |
| PUBLISHER | Independently Published (08/05/2020) |
| PRODUCT TYPE | Paperback (Paperback) |
Description
This Technical Memorandum examines the effects of heat and absorbed moisture on the open hole compression strength of carbon/epoxy laminates with the material and layup intended for the Ares I composite interstage. The knockdown due to temperature, amount of moisture absorbed, and the interaction between these two are examined. Results show that temperature is much more critical than the amount of moisture absorbed. The environmental knockdown factor was found to be low for this material and layup and thus obtaining a statistically significant number for this value needs to be weighed against a program s cost and schedule since basis values, damage tolerance, and safety factors all contribute much more to the overall knockdown factor. Nettles, Alan T. Marshall Space Flight Center NASA/TM-2009-215900, M-1259 EPOXY MATRIX COMPOSITES; TEMPERATURE EFFECTS; COMPRESSIVE STRENGTH; LAUNCH VEHICLES; SAFETY FACTORS; COSTS; DAMAGE; MOISTURE; TOLERANCES (MECHANICS)
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Product Format
Product Details
ISBN-13:
9798672044316
Binding:
Paperback or Softback (Trade Paperback (Us))
Content Language:
English
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Page Count:
36
Carton Quantity:
113
Product Dimensions:
8.50 x 0.07 x 11.02 inches
Weight:
0.24 pound(s)
Country of Origin:
US
Subject Information
BISAC Categories
Reference | Research
Reference | Space Science - General
Descriptions, Reviews, Etc.
publisher marketing
This Technical Memorandum examines the effects of heat and absorbed moisture on the open hole compression strength of carbon/epoxy laminates with the material and layup intended for the Ares I composite interstage. The knockdown due to temperature, amount of moisture absorbed, and the interaction between these two are examined. Results show that temperature is much more critical than the amount of moisture absorbed. The environmental knockdown factor was found to be low for this material and layup and thus obtaining a statistically significant number for this value needs to be weighed against a program s cost and schedule since basis values, damage tolerance, and safety factors all contribute much more to the overall knockdown factor. Nettles, Alan T. Marshall Space Flight Center NASA/TM-2009-215900, M-1259 EPOXY MATRIX COMPOSITES; TEMPERATURE EFFECTS; COMPRESSIVE STRENGTH; LAUNCH VEHICLES; SAFETY FACTORS; COSTS; DAMAGE; MOISTURE; TOLERANCES (MECHANICS)
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