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David L. Bourell, Joseph J. Beaman, Jr., Donald Klosterman, Ian Gibson, Amit Bandyopadhyay
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curved laminates
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Series: ASM Handbook
Volume: 20
Publisher: ASM International
Published: 01 January 1997
DOI: 10.31399/asm.hb.v20.a0002478
EISBN: 978-1-62708-194-8
... laminates; and curved laminates. It provides information on controlled thermal expansion composites, metal-matrix composites, and ceramic-matrix composites. The article illustrates the types of bonded joints and concludes with a discussion on design for manufacturing. asymmetric in-plane laminates...
Abstract
This article begins with a discussion on fiber-reinforced composite materials and describes the generic behavior and structure/property relationships of composites. The article summarizes lamina properties and presents equations that help in the calculation of lamina properties. Composite laminates are constructed from lamina with uniaxial fiber orientation and frequently from textile fabrics as well. The article explains the characteristics of symmetric in-plane and through-thickness laminates; asymmetric in-plane and symmetric through-thickness laminates; asymmetric laminates; and curved laminates. It provides information on controlled thermal expansion composites, metal-matrix composites, and ceramic-matrix composites. The article illustrates the types of bonded joints and concludes with a discussion on design for manufacturing.
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Published: 01 January 2001
Fig. 4 A curved laminate “C” channel in various loading conditions. (a) Unloaded. (b) Radii open under tensile load. (c) Radii close under compressive load
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Published: 01 January 2001
Fig. 5 Development of radial stresses in a curved laminate. (a) The force couples (– P , + P ) act on the curved laminate. (b) The radial stresses (σ r ) must balance the vertical components of these loads.
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Published: 01 January 2001
Fig. 6 Combined loads acting on a curved laminate. P , in-plane load; V , shear load; M , end moment; p i , surface pressure
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Book: Composites
Series: ASM Handbook
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003387
EISBN: 978-1-62708-195-5
..., the strength analyst must be cognizant of cases where primary loads in the plane of the laminate induce secondary loads that act in the through-thickness direction. Such cases include free-edge stresses in cross-plied laminates under axial loads, radial stresses in curved laminates subject to tangential loads...
Abstract
This article discusses the methods of analyzing the directional dependence of the mechanical properties of composites, especially those perpendicular to the major plane of the laminate. It provides a description of the common indirect load cases and direct out-of-plane load cases. The article concludes with a discussion on composite materials that are reinforced in the z-direction (also known as three-dimensional, or 3-D composites).
Book: Fatigue and Fracture
Series: ASM Handbook
Volume: 19
Publisher: ASM International
Published: 01 January 1996
DOI: 10.31399/asm.hb.v19.a0002416
EISBN: 978-1-62708-193-1
... in compressive strength and tensile strength. The article reviews low velocity impacts in aircraft structures in terms of resin toughness, laminate thickness, specimen size and impactor mass, and post-impact fatigue. It explains the tension strength analysis, such as linear elastic fracture mechanics and R-curve...
Abstract
This article presents the damage tolerance criteria for military composite aircraft structures to safely operate the structures with initial defects or in-service damage. It describes the effects of defects, such as wrinkles in aircraft structures, and the reduction in compressive strength and tensile strength. The article reviews low velocity impacts in aircraft structures in terms of resin toughness, laminate thickness, specimen size and impactor mass, and post-impact fatigue. It explains the tension strength analysis, such as linear elastic fracture mechanics and R-curve methods, to predict the residual strength of the structures.
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Published: 01 January 1996
Fig. 6 S-N curves for (a) various AS4-epoxy laminates and (b) glass-fiber polymer laminates at various ply orientations. Source: (a) Engineered Materials Handbook, Vol 1, Composites, ASM International, 1987, p 438 and (b) C. Osgood, Fatigue Design, 2nd ed., 1982, Pergamon Press, p 530
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Image
Published: 01 January 1996
Fig. 28 R-curve for [ + 45/0/90/ + 30/ 0 ] s AS4/938 fuselage crown laminate (2 a o = 23 cm and W = 91 cm)
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Image
Published: 01 January 1996
Fig. 31 R-curves for [ + 45/0/90/ + 30/ 0 ] s AS4/938 fuselage crown laminates with various cut lengths. W ≥ 8 a o
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Book: Composites
Series: ASM Handbook
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003382
EISBN: 978-1-62708-195-5
... [0°/±45°/90°] 2s laminates. Although some correlation has been made between unidirectional fatigue behavior and that of multidirectional laminates, it is best to characterize laminates of interest rather than infer S - N curves from unidirectional data. This is in part due to the acceleration...
Abstract
In the design of composite structures for durability and damage tolerance, the primary concerns are out-of-plane failures, such as delamination, material degradation associated with environment, stability under compression loading, large degree of scatter in fatigue life, and bearing failure of joints. This article presents an introductory discussion on the fatigue damage process, methodologies assessing fatigue behavior, and life prediction models. It describes the damage mechanisms introduced for a quasi-isotropic laminate under tension-compression fatigue loading. Delamination is a critical issue in fatigue and generally results from high interlaminar normal and shear stresses. The article schematically illustrates the structural elements in which high interlaminar stresses are common. It concludes with a discussion on the classification of fatigue models such as mechanistic or phenomenological, for composite materials under cyclic loading.
Book: Composites
Series: ASM Handbook
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003465
EISBN: 978-1-62708-195-5
... there is a threefold difference in CTE at this point in the TMA curve ( Ref 1 ). Figure 4 shows measurement of the expansion coefficient and the T g in a printed circuit board (PCB) laminate, where the signal is affected by an enthalpic relaxation effect due to stress induced by processing (lower curve...
Abstract
This article focuses on various thermal analysis techniques used to verify the cure of a polymer composite. The techniques include differential scanning calorimetry (DSC), modulated DSC, thermomechanical analysis, dynamic mechanical analysis, and dielectric analysis. The article also provides an overview of the composite failure modes affected by matrix resin and testing approach.
Book Chapter
Book: Composites
Series: ASM Handbook
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003378
EISBN: 978-1-62708-195-5
.... It explains the development of the relations between mid-surface strains and curvatures and membrane stress and moment resultants. The article discusses the properties, such as thermal expansion, moisture expansion, and conductivity, of symmetric laminates and unsymmetric laminates. It describes...
Abstract
The properties of unidirectional composite (UDC) materials are quite different from those of conventional, metallic materials. This article provides information on the treatment of UDC stress-strain relations in the forms appropriate for analysis of thin plies of material. It explains the development of the relations between mid-surface strains and curvatures and membrane stress and moment resultants. The article discusses the properties, such as thermal expansion, moisture expansion, and conductivity, of symmetric laminates and unsymmetric laminates. It describes the distribution of temperature and moisture through the thickness of a laminate. Stresses caused due to mechanical loads, temperature, and moisture on the laminate are analyzed. The article concludes with information on interlaminar cracking, free-edge delamination, and transverse cracks of laminates.
Book Chapter
Book: Composites
Series: ASM Handbook
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003397
EISBN: 978-1-62708-195-5
... an external, rotatable feed table, picked up with a vacuum chuck, and shuttled to the mandrel. A flexible thermoforming mechanism laminates each new layer to the curved mandrel with steady, uniform vacuum pressure and heat. After the laminator retracts, a CO 2 laser cuts each layer, accounting for the sloped...
Abstract
This article reviews various rapid prototyping (RP) processes such as stereolithography, powder sintering, hot melt extrusion, sheet lamination, solid ground curing, and three-dimensional printing. It discusses the various material prototypes produced by RP technology. The list of materials includes particulate and fiber-reinforced polymers, ceramic-matrix composites, and metal-matrix composites. The article also provides information on freeform-fabrication techniques for composite part lay-up.
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Published: 01 January 2001
Book: Composites
Series: ASM Handbook
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003394
EISBN: 978-1-62708-195-5
...Abstract Abstract Continuous fiber composite materials offer dramatic opportunities for producing lightweight laminates with tremendous performance capabilities. This article describes the kinematics of fabric deformation and explains the algorithms used in draping simulation. It discusses...
Abstract
Continuous fiber composite materials offer dramatic opportunities for producing lightweight laminates with tremendous performance capabilities. This article describes the kinematics of fabric deformation and explains the algorithms used in draping simulation. It discusses the basic components, such as laminate and ply, of continuous fiber composite. The article provides information on the core sample and ply analysis. It details producibility, flat-pattern evaluations, and laminate surface offset. The article discusses various interfaces, such as the structural analysis interface, the resin transfer molding interface, the fiber placement and tape-laying interface, and the laser projection interface.
Image
Published: 01 January 1996
Fig. 30 Predicted failing strains using R-curve and LEFM for [ + 45/0/90/ + 30/ 0 ] s AS4/938 fuselage crown laminates. W ≥ 8 a o
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Book Chapter
Series: ASM Desk Editions
Publisher: ASM International
Published: 01 November 1995
DOI: 10.31399/asm.hb.emde.a0003044
EISBN: 978-1-62708-200-6
...Abstract Abstract Testing of fiber-reinforced composite materials is performed to determine uniaxial tensile strength, Young's modulus, and Poisson's ratio relative to principal material directions, that helps in the prediction of the properties of laminates. Beginning with an overview...
Abstract
Testing of fiber-reinforced composite materials is performed to determine uniaxial tensile strength, Young's modulus, and Poisson's ratio relative to principal material directions, that helps in the prediction of the properties of laminates. Beginning with an overview of the fundamentals of tensile testing of fiber-reinforced composites, this article describes environmental exposures that often occur during specimen preparation and testing. These include exposures during specimen preparation, and planned exposure such as moisture, damage (impact), and thermal cycling techniques. The article also discusses the test procedures, recommended configurations, test specimen considerations, and safety requirements considered in the four major types of mechanical testing of polymer-matrix composites: tensile test, compression test, flexural test, and shear test.
Book Chapter
Book: Fatigue and Fracture
Series: ASM Handbook
Volume: 19
Publisher: ASM International
Published: 01 January 1996
DOI: 10.31399/asm.hb.v19.a0002415
EISBN: 978-1-62708-193-1
... data analysis fatigue life fatigue stress fiber break GLARE laminates interface debonding layer cracking life prediction notched specimens S-N curves unnotched specimens Weibull distribution KNOWLEDGE of fatigue behavior at the laminate level is essential for understanding the fatigue...
Abstract
Knowledge of fatigue behavior at the laminate level is essential for understanding the fatigue life of a laminated composite structure. This article describes fatigue failure of composite laminates in terms of layer cracking, delamination, and fiber break and interface debonding. It discusses the fatigue behavior of composite laminates in the form of a relation between applied maximum fatigue stress and fatigue life. The article explains Weibull distribution and parameters estimation for fatigue data analysis and life prediction of composite laminates. It analyzes the fatigue properties and damage tolerance of fiber-metal laminates such as ARALL and GLARE laminates. The article concludes with a discussion on the effects of fatigue on notched and unnotched specimens.
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in Nondestructive Testing of Composites (Polymer- and Metal-Matrix Composites)[1]
> Nondestructive Evaluation of Materials
Published: 01 August 2018
Fig. 24 Leaky Lamb wave characterization. (a) The reflection at 39.5° incidence angle and the dispersion curve for a graphite/epoxy [0] 24 laminate with no defects. (b) Response at a defect area where simulated porosity was introduced in the middle layer using microballoons
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Published: 01 January 2001
Fig. 5 Matrix cracks related to the proportional limit stress and onset of nonlinearity of the stress-strain curve; arrows indicate matrix cracks in 0°/90° laminate Nicalon fiber reinforced CAS glass-matrix composite. Source: Ref 4
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