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  • COMPOSITE MATERIALS  (4)
  • 1985-1989  (1)
  • 1980-1984  (3)
  • 1965-1969
  • 1
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    Application of Gr/PMR-15 to commercial aircraft (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Following from early experience with polyimides on the SST program and Shuttle aft flap studies the Boeing Company is now working on collaborative programs with its principal nacelle suppliers to pursue the development of Gr/PMR-15 nacelle components. Two programs are currently in effect. The first program is directed specifically towards the flight test and service evaluation at the earliest possible date of a 747 nacelle core cowl structure. The second program seeks to firmly establish the producibility and cost of a 757 thrust reverser C duct in a production environment. The near term objectives of these programs include: (1) the comparison of estimated cost and weight of Gr/PMR-15 versus metal structure, (2) the engine test of representative composite structure, (3) the preliminary design and analysis of the C duct structure, and (4) the preparation of cost data and time schedules for the development and producibility program. In addition to powerplant structure, the propulsion ducting system has shown to be a strong candidate for Gr/PMR-15 application. Currently, the Boeing 747 Organization is evaluating the use of PMR-15 matrix composites to replace nearly 800 lbs of titanium ducting per airplane.
    Keywords: COMPOSITE MATERIALS
    Type: NASA. Lewis Research Center High Temp. Polymer Matrix Composites; p 393-400
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Environmental effects on defect growth in composite materials (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Data for evaluating the effects of moisture and temperature on the integrity of fiber composite components was gathered. In particular, the static and cyclic performance of three composite laminates containing flaws was investigated at room temperature and at 422 K (300 F) in wet and dry conditions.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-CR-165213 , NAS 1.26:165213
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Environmental effects on composite fracture behavior (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An experimental program was carried out to investigate the effects of temperature and moisture on the damage development and fracture response of graphite/epoxy composites. Fracture response data were obtained for 20-ply laminates of different layup patterns for both room temperature and immediately after the application of a temperature transient causing the specimen to attain 150 C. It is found that elevated temperature degrades the notched strength of some laminates while not degrading others. The unnotched strength of all laminates tested at elevated temperatures was degraded. The effect of preloading on damage growth and moisture absorption, the effect of autoclave pressure during the laminate cure on fracture, and the variation of interlaminar shear properties with layup, moisture exposure, laminate material, and cure pressure are also discussed.
    Keywords: COMPOSITE MATERIALS
    Type: Symposium on Test methods and design allowables for fibrous composites; Oct 02, 1979 - Oct 03, 1979; Dearborn, MI
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Compression and compression fatigue testing of composite laminates (1982)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The effects of moisture and temperature on the fatigue and fracture response of composite laminates under compression loads were investigated. The structural laminates studied were an intermediate stiffness graphite-epoxy composite (a typical angle ply laimna liminate had a typical fan blade laminate). Full and half penetration slits and impact delaminations were the defects examined. Results are presented which show the effects of moisture on the fracture and fatigue strength at room temperature, 394 K (250 F), and 422 K (300 F). Static tests results show the effects of defect size and type on the compression-fracture strength under moisture and thermal environments. The cyclic tests results compare the fatigue lives and residual compression strength under compression only and under tension-compression fatigue loading.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-CR-168023 , NAS 1.26:168023 , D180-27619-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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