Size effects on tensile and compressive strengths in metallic glass nanowires

Shear localization induced brittleness is the main drawback of metallic glasses which restricts their practical applications. Previous experiments have provided insights on how to suppress shear localization by reducing the sample size of metallic glasses to the order of 100 nm. In order to reveal the size effects and associated deformation mechanisms of metallic glasses in an even finer scale, we perform large-scale atomistic simulations for the uniaxial compression and tension of metallic glass nanowires. The simulation results show that, as the diameter of metallic glass samples decreases from 45 nm to 8 nm, the tensile yield strength increases while the compressive yield strength decreases. Homogeneous flow is observed as the governing deformation mechanism in all simulated metallic glass samples, where plastic shearing tends to initiate on the sample surface and propagate into the interior. To rationalize the size dependence of yield strengths, we propose a theoretical model based on the concept of surface stress and Mohr–Coulomb criterion. The theoretical predictions agree well with the simulation results, implying the important role of surface stress on the yielding of MGs below 100 nm. Finally, a discussion about the size effects of strength in metallic glasses at different length scales is provided. Our results suggest that the shear band energy and surface stress might be the two crucial parameters in determining the critical size required for the transition from shear localization to homogeneous deformation in MGs.     

Effects of fatigue and environment on residual strengths of center-cracked graphite/epoxy buffer strip panels

Graphite/epoxy buffer strip panels were subjected to a fatigue loading spectrum, moisture conditioning, or heating and then statically tested in tension to determine their residual strengths. The specimens were made with T300/5208 graphite/epoxy in a 16-ply quasi-isotropic layup, [45/0/ - 45/90]_2s, with two different buffer strip materials: Kevlar-49 or S-glass. Each panel was cut in the center to represent damage.The panels made from each buffer strip material were divided into two test conditions: those panels tested at room temperature and those tested at 82°C. Each test condition was further divided into two groups, panels tested at ambient conditions and panels tested after moisture conditioning. Thus, there were four combinations of preconditioning and test condition: (1) ambient condition tested at room temperature, (2) moisture conditioned tested at room temperature, (3) ambient condition tested at 80°C, and (4) moisture conditioned tested at 82°C. After preconditioning and fatigue loading, all specimens were statically loaded in tension to failure to determine their residual strengths.After fatigue loading, the buffer strips arrested the crack growth and increased the residual strengths significantly over those of plain laminates without buffer strips under all conditions, with one exception. For the S-glass buffer strip panels with moisture conditioning, the buffer strip arrested the crack growth, but the residual strength was increased only slightly over the strength of a plain laminate. The stiffness of the panels was not affected by the fatigue cycling. Repeated fatigue cycling did not produce any damage growth at the crack tips.Paper was presented at the 1988 SEM Spring Conference on Experimental Mechanics held in Portland, OR on June 5–10.     

大型户外广告牌面板极值风压分布的试验研究

大型户外广告牌作为城市典型的风灾易损性结构,在强风作用下的毁坏倒塌发生频繁,存在巨大的安全隐患.本文针对大型户外独立柱广告牌结构设计的薄弱环节,即广告牌面板的极值风压破坏,通过开展三种湍流度不同的风场的测压试验,考虑面板风压时程的高斯/非高斯特性,使用三种不同的极值风压计算方法,给出了极值风压与风场之间的联系,同时也比...     

Equivalent models of corrugated panels

The design of corrugated panels has wide application in engineering. For example corrugated panels are often used in roof structures in civil engineering. More recently corrugated laminates have been suggested as a good solution for morphing aircraft skins due to their extremely anisotropic behaviour. The optimal design of these structures requires simple models of the panels or skins that may be incorporated into multi-disciplinary system models. Thus equivalent material models are required that retain the dependence on the geometric parameters of the corrugated skins or panels. An homogenisation-based analytical model, which could be used for any corrugation shape, is suggested in this paper. This method is based on a simplified geometry for a unit-cell and the stiffness properties of original sheet. This paper outlines such a modelling strategy, gives explicit expressions to calculate the equivalent material properties, and demonstrates the performance of the approach using two popular corrugation shapes.     

Aeroelastic inverse: Estimation of aerodynamic loads during large amplitude limit cycle oscillations

This paper presents an algorithm to compute the aerodynamic forces and moments of an aeroelastic wing undergoing large amplitude heave and pitch limit cycle oscillations. The technique is based on inverting the equations of motion to solve for the lift and moment experienced by the wing. Bayesian inferencing is used to estimate the structural parameters of the system and generate credible intervals on the lift and moment calculations. The inversion technique is applied to study the affect of mass coupling on limit cycle oscillation amplitude. Examining the force, power, and energy of the system, the reasons for amplitude growth with wind speed can be determined. The results demonstrate that the influence of mass coupling on the pitch–heave difference is the driving factor in amplitude variation. The pitch–heave phase difference not only controls how much aerodynamic energy is transferred into the system but also how the aerodynamic energy is distributed between the degrees of freedom.     

In situ strengths of matrix in a composite

A major obstacle to achieving reasonable strength prediction of a composite only from its constituent infor-mation is in the determination of in situ strengths of the matrix. One can measure only the original strengths of the pure matrix, on the basis of which the predicted transverse strengths of a unidirectional (UD) composite are far from reality. It is impossible to reliably measure matrix in situ strengths. This paper focuses on the correlation between in situ and original strengths. Stress concentrations in a matrix owing to the introduction of fibers are attributed to the strength variation. Once stress concentration factors (SCFs) are obtained, the matrix in situ strengths are assigned as the original counterparts divided by them. Such an SCF can-not be defined following a classical approach. All of the relevant issues associated with determining it are system-atically addressed in this paper. Analytical expressions for SCFs under transverse tension, transverse compression, and transverse shear are derived. Closed-form and compact for-mulas for all of the uniaxial strengths of a UD composite are first presented in this paper. Their application to strength pre-dictions of a number of typical UD composites demonstrates the correctness of these formulas.     

Fracture of cylindrical panels with cracks in tension

Institute of Mechanics, Academy of Sciences of the Ukrainian SSSR, Kiev. Translated from Prikladnaya Mekhanika, Vol. 26, No. 7, pp. 63–67, July, 1990.     

Elastic-plastic models of surface cracks in tensile panels

The surface crack is a common flaw in structures and vessels, and its elastic characterization has been studied extensively as reviewed in Ref. 1 and its references. Elastic-plastic fracture-mechanics (EPFM) technology can be used to characterize surface cracks in tough materials. Two EPFM aprameters are commonly used: the crack-tip-opening displacement (CTOD) and the three-dimensionalJ integral. This paper draws on a series of studies^2–11 at the National Bureau of Standards related to the development and verification of analyticalmodels for the calculation of EPFM parameters in surface-cracked tensile panels. The models previously verified for pipeline steel plates^4–7 are used to calculate the crack-mouth-opening displacement (CMOD) andJ for surface cracks in welded-steel specimens.     

Postbuckling behavior of composite-stiffened-curved panels loaded in compression

In this paper, a methodology is developed for the design of a weight-efficient, composite, curved-stiffened panel, loaded in compression well beyond the initial buckling load. A stiffened fuselage panel is designed to satisfy typical design load criteria for the moderately loaded sections of a typical fighter aircraft. Several stiffened panels are fabricated. Some panels are tested to determine experimentally the static strength and the remaining panels are subjected first to severe fatigue loading and then tested statically to determine the effect of fatigue loading on the postbuckling strengh. The experimentally observed behavior is compared with analytical predictions. The weight efficiencies of buckled and unbuckled construction are also compared.     

In-plane shear test of thin panels

Efficient application of thin-gage composite materials to helicopter fuselage structures necessitates that the materials be designed to operate at loads several times higher than initial buckling load. Methods are required to accurately measure and predict the response of thin-gage composites when subjected to these loads. This paper presents the results of an analytical and experimental study of the behavior of thin-gage composite panels subjected to in-plane shear loads. Finite-element stress analyses were used to aid in the design of an improved shear fixture that minimizes adverse corner stresses and tearing and crimping failure-modes characteristic of commonly used shear fixtures. Tests of thick buckle-resistant aluminum panels and thin aluminum and composite panels were conducted to verify the fixture design. Results of finite-element stress and buckling analyses and diagonal-tension-theory predictions are presented. Correlation of experimental data with analysis indicated that diagonal-tension theory can be used to predict the load-strain response of thin composite panels.     

Prediction of progressive failure in multidirectional composite laminated panels

A mechanism-based progressive failure analyses (PFA) approach is developed for fiber reinforced composite laminates. Each ply of the laminate is modeled as a nonlinear elastic degrading lamina in a state of plane stress according to Schapery theory (ST). In this theory, each lamina degrades as characterized through laboratory scale experiments. In the fiber direction, elastic behavior prevails, however, in the present work, the phenomenon of fiber microbuckling, which is responsible for the sudden degradation of the axial lamina properties under compression, is explicitly accounted for by allowing the fiber rotation at a material point to be a variable in the problem. The latter is motivated by experimental and numerical simulations that show that local fiber rotations in conjunction with a continuously degrading matrix are responsible for the onset of fiber microbuckling leading to kink banding. These features are built into a user defined material subroutine that is implemented through the commercial finite element (FE) software ABAQUS in conjunction with classical lamination theory (CLT) that considers a laminate as a collection of perfectly bonded lamina (Herakovich, C.T., 1998. Mechanics of Fibrous Composites. Wiley, New York). The present model, thus, disbands the notion of a fixed compressive strength, and instead uses the mechanics of the failure process to provide the in situ compression strength of a material point in a lamina, the latter being dictated strongly by the current local stress state, the current state of the lamina transverse material properties and the local fiber rotation. The inputs to the present work are laboratory scale, coupon level test data that provide information on the lamina transverse property degradation (i.e. appropriate, measured, strain–stress relations of the lamina transverse properties), the elastic lamina orthotropic properties, the ultimate tensile strength of the lamina in the fiber direction, the stacking sequence of the laminate and the geometry of the structural panel. The validity of the approach advocated is demonstrated through numerical simulations of the response of two composite structural panels that are loaded to complete failure. A flat, 24-ply unstiffened panel with a cutout subjected to in-plane shear loading, and a double notched 70-ply unstiffened stitched panel subjected to axial compression are selected for study. The predictions of the simulations are compared against experimental data. Good agreement between the present PFA and the experimental data are reported.     

Vibration localization in disordered periodically stiffened double-leaf panels

Vibration localization in periodically stiffened double-leaf multi-span panels is studied by employing the transfer matrix method. The localization factors of the ordered and disordered systems are calculated based on the Lyapunov exponent. The numerical results show that the propagation of vibration in rib-stiffened periodic double-leaf panels exhibits passbands and stopbands. The vibration localization phenomenon occurs and is enhanced with the increasing disorder of span-length. The torsional rigidities of the stiffeners have a significant effect on the pass bands and the localization factor. With the torsional rigidity of the stiffeners increasing, the vibration localization factor first decreases, then increases and finally tends to be the situation of the rib-stiffened single-leaf panels. It is also noted that for the double-leaf panels a passband appears among the lower dimensionless frequencies for some particular values of torsional rigidity of the stiffeners while a stopband always exists for the single-leaf panels.     

On thermal stresses and displacements in finned-tube panels

The end stresses in a finned-tube panel subjected to transverse temperature gradients are shown to be substantially different than those of a flat plate. Important differences occur due to the local bending of the tube and the extension of the tube beyond the end of the fin. On the other hand, stresses not near the ends and the in-plane deflections of a finned-tube panel are similar to those of a flat plate. These results are obtained by means of a review of flat-plate analysis and comparison with measurements made on two finned-tube panels with a step-transverse temperature gradient.     

Some aspects of flutter of cylindrical panels

Summary Pursuing a previous study, the investigation of some aspects of the flutter of weakly curved panels is taken a stage further. A new system of visual presentation of the results evolved for this makes the analog computer study easier and more rewarding. Further, an improvement in the calculating circuit permits continuous variation both of the flutter parameter and of the compression load during calculation.

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Sommario Proseguendo una ricerca già iniziata si approfondiscono alcuni aspetti del flutter dei pannelli a debole curvatura. Per questo è stato messo a punto un nuovo sistema di presentazione visiva dei risultati che ha reso più agevole e profiquo lo studio condotto con il calcolatore analogico; inoltre si è migliorato il circuito di calcolo ottenendo la possibilità di variare in modo continuo, durante il calcolo, oltre che il parametro di flutter, anche il carico di compressione.

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