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  • 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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  • 2
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    Core design for use with precision composite reflectors (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A uniformly flexible core, and method for manufacturing the same, is disclosed for use between the face plates of a sandwich structure. The core is made of a plurality of thin corrugated strips, the corrugations being defined by a plurality of peaks and valleys connected to one another by a plurality of diagonal risers. The corrugated strips are orthogonally criss-crossed to form the core. The core is particularly suitable for use with high accuracy spherically curved sandwich structures because undesirable stresses in the curved face plates are minimized due to the uniform flexibility characteristics of the core in both the X and Y directions. The core is self venting because of the open geometry of the corrugations. The core can be made from any suitable composite, metal, or polymer. Thermal expansion problems in sandwich structures may be minimized by making the core from the same composite materials that are selected in the manufacture of the curved face plates because of their low coefficients of thermal expansion. Where the strips are made of a composite material, the core may be constructed by first cutting an already cured corrugated sheet into a plurality of corrugated strips and then secondarily bonding the strips to one another or, alternatively, by lying a plurality of uncured strips orthogonally over one another in a suitable jig and then curing and bonding the entire plurality of strips to one another in a single operation.
    Keywords: COMPOSITE MATERIALS
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  • 3
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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
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  • 4
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    Effect of preload on the fatigue and static strength of composite laminates with defects (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The effect of a preload cycle on the structural performance of three graphite/epoxy composite laminates was studied. The layups studied were a laminate typical of general purpose structures (L1), a laminate representative of a filament wound tank (L2), and a laminate representative of turboengine fan blades. The effects of three sizes of simulated initial defects were studied. The tests developed static strength data, fatigue to failure data, and residual static data after application of a predetermined number of fatigue cycles. For L1 specimens, there was a slight trend for the static strength to be greater for preloaded specimens. After application of cyclic loading, however, the influence of preloading was insignificant. In L2 and L3 specimens there was no consistent difference in the static or fatigue results between preloaded and nonpreloaded specimens.
    Keywords: COMPOSITE MATERIALS
    Type: Annual Meeting on Recent advances in engineering science; Nov 14, 1977 - Nov 16, 1977; Bethlehem, PA
    Format: text
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  • 5
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    Evaluation of flawed composite structure under static and cyclic loading (1977)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: This paper presents the results of a program investigating the effects of initial defects on the fatigue and fracture response of composite laminates. The structural laminates investigated were a typical angle-ply laminate, a polar/hoop-wound pressure vessel laminate, and a typical engine fan blade laminate. Defects investigated were full- and half-penetration circular holes, full- and half-penetration slits, and countersink holes. Results are presented showing the effects of the defect size and type on the static fracture strength, fatigue performance, and residual static strength. The results of inspection procedures are shown, describing the effect of cyclic and static loadings on damage propagation in composite laminates. The data in this study were used to define proof test levels as a qualification procedure in composite structure subjected to cyclic loading.
    Keywords: COMPOSITE MATERIALS
    Type: Symposium on Fatigue of filamentary composite materials; Nov 15, 1976 - Nov 16, 1976; Denver, CO
    Format: text
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  • 6
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    Evaluation of flawed composite structural components under static and cyclic loading (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effects of initial defects on the fatigue and fracture response of graphite-epoxy composite laminates are presented. The structural laminates investigated were a typical angle ply laminate, a polar/hoop wound pressure vessel laminate, and a typical engine fan blade laminate. Defects investigated were full and half penetration circular holes, full and half penetration slits, and countersink holes. The effects of the defect size and type on the static fracture strength, fatigue performance, and residual static strength are shown as well as the results of loadings on damage propagation in composite laminates. The data obtained were used to define proof test levels as a qualification procedure in composite structure subjected to cyclic loading.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-CR-135403
    Format: application/pdf
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  • 7
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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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  • 8
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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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