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  • 1
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    Hidden impact damage in thick composites (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: NASA is developing light-weight graphite/epoxy filament-wound cases (FWC) for the solid rocket motors of the Space Shuttle. The 12-foot-diameter FWC's are about 1.4 inches or more thick. Tests were conducted to determine the tension strength of an FWC after low-velocity impact. Impactors of various kinetic energies, masses, and shapes were used. The conditions that give minimum visual evidence of damage were emphasized. The capability to characterize impact damage with radiography and ultrasonic attenuation was also evaluated. After impact, the specimens were loaded uniaxially in tension to determine residual strengths.
    Keywords: COMPOSITE MATERIALS
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    FACTORS IN EVALUATING FATIGUE LIFE ON STRUCTURAL PARTS (1960)
    In:  Other Sources
    Details
    Publication Date: 2013-08-29
    Description: Variable amplitude loading, fatigue loading, fatigue crack propagation and structural parts - fatigue life
    Keywords: THERMODYNAMICS AND COMBUSTION
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Fatigue and fracture (1979)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: The effects of the load/temperature environment of the shuttle on the fatigue life of the body-flap were investigated by conducting real time and accelerated flight-by-flight tests up to 500 flights on coupons containing holes. On the fracture side, much is known about the sensitivity of the tensile strengths of composites to holes and other flaws, predominantly at room temperature. The effects of notches were assessed for graphite/polyimides at the expected temperature extremes of the body-flap: 117K (-250 F) to 589K (600 F). Results indicate that the shuttle temperature extremes may affect fatigue properties HTS/PMR-15. There is no significant effect of temperature on notch-strength. Tensile strengths for specimens with holes and slots are equal.
    Keywords: COMPOSITE MATERIALS
    Type: Graphite/Polyimide Composites; p 259-272
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Prediction of impact force and duration due to low-velocity impact on circular composite laminates (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Two simple and improved models - energy-balance and spring-mass - were developed to calculate impact force and duration during low velocity impact of circular composite plates. Both models include the contact deformation of the plate and the impactor as well as bending, transverse shear, and membrane deformations of the plate. The plate was transversely isotropic graphite/epoxy composite laminate and the impactor was a steel sphere. Calculated impact forces from the two analyses agreed with each other. The analyses were verified by comparing the results with reported test data.
    Keywords: STRUCTURAL MECHANICS
    Type: ASME, Transactions, Journal of Applied Mechanics (ISSN 0021-8936); 52; 674-680
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    NASA TECHNICAL REPORTS
  • 5
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    Factors in evaluating fatigue life of structural parts (1960)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: GENERAL
    Type: NASA Conf. on V(STOL Aircraft; p 325-334
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Structural materials for hypersonic aircraft (1967)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Keywords: GENERAL
    Type: Conf. on Hypersonic Aircraft Technol.; p 485-499
    Format: text
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  • 7
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    Fatigue of four stainless steels and three titanium alloys before and after exposure to 550 deg f /561 deg k/ up to 8800 hours (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Fatigue tests of stainless steels and titanium alloys before and after exposure to high temperatures
    Keywords: MATERIALS, METALLIC
    Type: NASA-TN-D-2899
    Format: application/pdf
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  • 8
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    Infrared shield facilitates optical pyrometer measurements (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Water-cooled shield facilitates optical pyrometer high temperature measurements of small sheet metal specimens subjected to tensile stress in fatigue tests. The shield excludes direct or reflected radiation from one face of the specimen and permits viewing of the infrared radiation only.
    Keywords: PHYSICAL SCIENCES
    Type: LAR-133
    Format: application/pdf
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  • 9
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    Strength of a thick graphite/epoxy rocket motor case after impact by a blunt object (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The National Aeronautics and Space Administration is developing graphite/epoxy filament-wound cases (FWC) for the solid rocket motors of the Space Shuttle. The membrane region is about 36 mm thick. A study was made to determine the reduction in strength of the FWC due to accidental damage caused by low-velocity impacts. Two 76.2 cm diameter by 30.5 cm long cylinders were impacted every 5 cm of circumference with 1.27 cm radius impacters of various mass. The impacters represented tools and equipment dropped from various heights. One cylinder was empty and the other was filled with inert propellant. Five cm wide test specimens were cut from the cylinder. Each was centered on an impact sight. The specimens were X-rayed and loaded to failure in uniaxial tension. The strengths and depths of impact damage were analyzed in terms of maximum impact force. Rigid body mechanics and the Hertz law were used to derive an equation for impact force in terms of kinetic energy and the masses of the impacter and target. The depth of damage was predicted in terms of impact force using Love's solution of pressure applied on part of the boundary of a semi-infinite body.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-TM-89099 , NAS 1.15:89099
    Format: application/pdf
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  • 10
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    Tension strength of a thick graphite/epoxy laminate after impact by a 1/2-in. radius impactor (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: NASA is developing graphite/epoxy filament-wound cases for solid rocket motors of the space shuttle. They are wet-wound with AS4W graphite fiber and HBRF-55A epoxy. The membrane region is about 1.4 inches thick. Two 30-inch-diameter by 12-inch-long cylinders were impacted every two inches of circumference with 1/2-inch radius impactors that were dropped from various heights. One cylinder was empty and the other was filled with inert propellant. Two-inch-wide test specimens were cut from the cylinders. Each was centered on an impact site. The specimens were x-rayed and loaded to failure in uniaxial tension. Rigid body mechanics and the Hertz law were used to predict impact force, local deformations, contact diameters, and contact pressures. The depth of impact damage was predicted using Love's solution for pressure applied on part of the boundary of a semi-infinite body. The predictions were reasonably good. The strengths of the impacted specimens were reduced by as much as 37 percent without visible surface damage. Even the radiographs did not reveal the nonvisible damage.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-TM-87771 , NAS 1.15:87771
    Format: application/pdf
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