Hard tissue as a composite material. I - Bounds on the elastic behavior
Elastic behavior of bone as two phase composite material, using ultrasonically measured hydroxyapatite moduli
Katz, J. L.↗
Engineering topics
Materials science
Explore NASA and DOE materials research. Search alloys, composites and material properties, then open the original technical report for test conditions and results.
Composition gradients in Ni-Fe alloy films produced by vapor deposition from a tungsten boat
Ni-Fe alloy films composition gradients produced by W boats evaporation, noting vapor pressures effect
Carson, K. R.↗
Selection of an alloy composition in the ternary Co-Cr-Al system for oxidation resistance
Ternary Co-Cr-Al alloy oxidation resistant composition selection, using oxide maps superimposed on phase diagram
Hed, A. Z.↗
Graphite and boron-reinforced composite materials data summary
Data summary is collection of information on typical processing techniques. Mechanical properties, and physical properties of advanced composite materials which are being considered for structural applications on advanced space vehicles.
Source record↗
Application of composite materials to space shuttle tanks
Tanks are broken down into two categories: pressure vessels that carry primarily pressure loads, and structural tanks that carry structural loads such as thrust or bending in addition to pressure. A significant portion of the shuttle orbiter structure are tanks and in order to minimize both weight and cost growth on these shuttle tank structures, composite material tanks of both types are considered.
Faddoul, J. R.↗
Brazing of refractory, superalloy, and composite materials for Space Shuttle applications.
Research work concerning the metallic portion of the shuttle-orbiter heat shield (expected to experience temperatures up to 2500 F) is described. The five metals being evaluated are TD-Ni-Cr, Cb-C129Y, Cb752, Hayes 188, and Inconel 625. Brazing techniques whereby pairs of these materials are joined into thin-membered assemblies for heat shield applications are described. Results obtained with the vacuum-furnace brazing process are examined. In addition, the use of brazed aluminum-boron metal-matrix-contoured composite structures for heat shield applications is evaluated.
Beuyukian, C. S.↗
Materials data handbook on Inconel Alloy 718
Handbook is divided into twelve chapters. Scope of information presented includes physical- and mechanical-property data at cryogenic, ambient, and elevated temperatures. This is supplemented with useful information in such areas as material procurement, metallurgy of alloy, corrosion, environmental effect, fabrication, and joining techniques. Design data are presented, as available.
Muraca, R. F.↗
Estimating Weibull parameters for composite materials.
This paper deals with the statistical analysis of strength and fracture of materials in general, with application to fiber composites. The 'weakest link' model is considered in a fairly general form, and the resulting equations are demonstrated by using a Weibull distribution for flaws. This distribution appears naturally in a variety of problems, and therefore additional attention is devoted to analysis and statistical estimation connected with this distribution. Special working charts are included to facilitate interpretation of observed data and estimation of parameters. Implications of the size effect are considered for various kinds of flaw distributions. The paper describes failure and damage in a fiber-reinforced systems.
Robinson, E. Y.↗
Surface emissivity of a reinforced carbon composite material with an oxidation-inhibiting coating
Total effective emissivity and spectral emissivity over the wavelength range of 0.65 to 6.3 microns were determined for temperatures from 1300 t0 2250 deg K. A multi channel radiometer was used in the arcjet and laboratory tests. The black-body-hole method was used to independently check radiometer results. The results show the silicon-carbide coated reinforced carbon composite material is a nongray radiator. The total effective emissivity and the spectral emissivity at 0.65 micron both decreased with increasing temperature, respectively, from approximately 0.8 to 0.6, and from 0.4 to 0.25, over the temperature range. The emissivity values were the same when the sample was viewed normal to the surface or at a 45 deg angle. Recommended emissivity values are presented.
Wakefield, R. M.↗
Composite materials in space structures
The use of composite materials in space vehicle structures offers significant advantages in reduction of structural weight fractions and in obtaining improved dynamic characteristics. Recent studies and developments include inertial booms for scientific satellites, structural components for future space shuttle applications, and pressurized tanks. Future applications could include major portions of vehicle primary structures as well as many secondary structural components. A number of problems still exist regarding achievement of the objectives, including development of sufficient environmental data, reliable design techniques, and general user confidence. These will be attacked in future R&D programs.
Mayer, N. J.↗
Bibliography of information on mechanics of structural failure (hydrogen embrittlement, protective coatings, composite materials, NDE)
This bibliography is comprised of approximately 1,600 reference citations related to four problem areas in the mechanics of failure in aerospace structures. The bibliography represents a search of the literature published in the period 1962-1976, the effort being largely limited to documents published in the United States. Listings are subdivided into the four problem areas: Hydrogen Embrittlement; Protective Coatings; Composite Materials; and Nondestructive Evaluation. An author index is included.
Carpenter, J. L., Jr.↗
Study to determine peening stress profile of rod peened aluminum structural alloys versus shot peened material
The objective of this program was to determine the peening stress profiles of rod peened aluminum structural alloys versus shot peened material to define the effective depth of the compressed surface layer.
Rosas, R. E.↗
Cosmic ray interactions with lunar materials - Nature and composition of species formed
The paper discusses the effect of cosmic-ray proton interactions with lunar material, the nature and composition of the species resulting from these interactions, and the contribution of these species to the lunar atmosphere. It is shown that hydrogen atoms resulting from cosmic-ray proton neutralization escape into the atmosphere mostly as H2, that only a small fraction of the very small amount of OH and H2O produced by cosmic-ray protons escapes into the atmosphere, and that cosmic-ray protons play a very minor role, as compared with solar-wind protons, in producing lunar atmospheric hydrogen and hydrogenated species. It is concluded that the atmospheric contributions of H2, H, OH, and H2O produced by cosmic-ray protons are about three orders of magnitude less than those due to solar-wind protons.
Mukherjee, N. R.↗
A new experimental method for the accelerated characterization of composite materials
The use of composite materials for a variety of practical structural applications is presented and the need for an accelerated characterization procedure is assessed. A new experimental and analytical method is presented which allows the prediction of long term properties from short term tests. Some preliminary experimental results are presented.
Yeow, Y. T.↗
Tungsten fiber reinforced FeCralY: A first generation composite turbine blade material
Tungsten-fiber/FeCrAlY (W/FeCrAlY) was identified as a promising aircraft engine, first generation, turbine blade composite material. Based on available data, W/FeCrAlY should have the stress-rupture, creep, tensile, fatigue, and impact strengths required for turbine blades operating from 1250 to 1370 K. It should also have adequate oxidation, hot corrosion, and thermal cycling damage resistance as well as high thermal conductivity. Concepts for potentially low cost blade fabrication were developed. These concepts were used to design a first stage JT9D convection cooled turbine blade having a calculated 50 K use-temperature advantage over the directionally solidified superalloy blade.
Petrasek, D. W.↗
Investigation and characterization of constraint effects on flaw growth during fatigue loading of composite materials
An investigative program is presented in an attempt to add to the current understanding of constraint effects on the response of composite materials under cyclic loading. The objectives were: (1) to use existing data and to develop additional data in order to establish an understanding and quantitative description of flaw growth in unidirectional lamina under cyclic loading at different load direction to fiber direction angles; (2) to establish a similar understanding and description of flaw growth in lamina which are embedded in laminates between other unflawed lamina; (3) to determine the nature of the influence of constraint on flaw growth by quantitatively comparing the results of the tests; and (4) to develop a model and philosophy of constraints effects based on our investigative results.
Stinchcomb, W. W.↗
A review of composite material applications in the automotive industry for the electric and hybrid vehicle
A review is made of the state-of-the-art in regard to the use of composite materials for reducing the structural mass of automobiles. Reduction of mass provides, in addition to other engineering improvements, increased performance/range advantages that are particularly needed in the electric and hybrid vehicle field. Problems encountered include the attainment of mass production techniques and the prevention of environmental hazards.
Bauer, J. L.↗
Thermal performance modification of composite materials
This paper reports on an investigation of the concept of modifying the thermal performance of filled polymers through a minor compositional change (presently by coating the filler). The fire-safety of construction materials and the instability of solid rockets are used as examples. A theory is developed which shows that vast improvements are possible by controlling thermal conductivity. Experiments are described that show the weight loss and smoke density in the NBS smoke-density chamber of fiberglass-reinforced epoxy panels, and the instability trends of an AP-HTPB propellant fired in an L-Star rocket motor. The feasibility of tailoring thermal behavior to suit each particular need is demonstrated.
Ramohalli, K.↗