An Investigation of the Thermoviscoplastic Behavior of a Metal Matrix Composite at Elevated Temperatures PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download An Investigation of the Thermoviscoplastic Behavior of a Metal Matrix Composite at Elevated Temperatures PDF full book. Access full book title An Investigation of the Thermoviscoplastic Behavior of a Metal Matrix Composite at Elevated Temperatures by National Aeronautics and Space Administration (NASA). Download full books in PDF and EPUB format.
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722939854
Category :
Languages : en
Pages : 166
Get Book Here
Book Description
This research investigates the response of a fiberless 13 layer hot isostatically pressed Ti-15-3 laminate to creep, constant strain rate, and cyclic constant strain rate loading at temperatures ranging from 482C to 649C. Creep stresses from 48 to 260 MPa and strain rates of .0001 to .01 m/m/sec were used. Material parameters for three unified constitutive models (Bodner-Partom, Miller, and Walker models) were determined for Ti-15-3 from the experimental data. Each of the three models was subsequently incorporated into a rule of mixtures and evaluated for accuracy and ease of use in predicting the thermoviscoplastic response of unidirectional metal matrix composite laminates (both 0 and 90). The laminates were comprised of a Ti-15-3 matrix with 29 volume percent SCS6 fibers. The predicted values were compared to experimentally determined creep and constant strain rate data. It was found that all three models predicted the viscoplastic response of the 0 specimens reasonably well, but seriously underestimated the viscoplastic response of the 90 specimens. It is believed that this discrepancy is due to compliant and/or weak fiber-matrix interphase. In general, it was found that of the three models studied, the Bodner-Partom model was easiest to implement, primarily because this model does not require the use of cyclic constant strain rate tests to determine the material parameters involved. However, the version of the Bodner-Partom model used in this study does not include back stress as an internal state variable, and hence may not be suitable for use with materials which exhibit a pronounced Baushinger effect. The back stress is accounted for in both the Walker and Miller models; determination of the material parameters associated with the Walker model was somewhat easier than in the Miller model. Rogacki, John R. and Tuttle, Mark E. Unspecified Center CREEP PROPERTIES; HIGH TEMPERATURE; HOT PRESSING; LAMINATES; METAL MATRIX COMPOSITES; STRAIN RATE; STRESS ANALYSIS; ...
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722939854
Category :
Languages : en
Pages : 166
Get Book Here
Book Description
This research investigates the response of a fiberless 13 layer hot isostatically pressed Ti-15-3 laminate to creep, constant strain rate, and cyclic constant strain rate loading at temperatures ranging from 482C to 649C. Creep stresses from 48 to 260 MPa and strain rates of .0001 to .01 m/m/sec were used. Material parameters for three unified constitutive models (Bodner-Partom, Miller, and Walker models) were determined for Ti-15-3 from the experimental data. Each of the three models was subsequently incorporated into a rule of mixtures and evaluated for accuracy and ease of use in predicting the thermoviscoplastic response of unidirectional metal matrix composite laminates (both 0 and 90). The laminates were comprised of a Ti-15-3 matrix with 29 volume percent SCS6 fibers. The predicted values were compared to experimentally determined creep and constant strain rate data. It was found that all three models predicted the viscoplastic response of the 0 specimens reasonably well, but seriously underestimated the viscoplastic response of the 90 specimens. It is believed that this discrepancy is due to compliant and/or weak fiber-matrix interphase. In general, it was found that of the three models studied, the Bodner-Partom model was easiest to implement, primarily because this model does not require the use of cyclic constant strain rate tests to determine the material parameters involved. However, the version of the Bodner-Partom model used in this study does not include back stress as an internal state variable, and hence may not be suitable for use with materials which exhibit a pronounced Baushinger effect. The back stress is accounted for in both the Walker and Miller models; determination of the material parameters associated with the Walker model was somewhat easier than in the Miller model. Rogacki, John R. and Tuttle, Mark E. Unspecified Center CREEP PROPERTIES; HIGH TEMPERATURE; HOT PRESSING; LAMINATES; METAL MATRIX COMPOSITES; STRAIN RATE; STRESS ANALYSIS; ...
Author: John R. Rogacki
Publisher:
ISBN:
Category : Metallic composites
Languages : en
Pages : 166
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 692
Get Book Here
Book Description
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781723457616
Category :
Languages : en
Pages : 154
Get Book Here
Book Description
Metal matrix composites (MMC's) are candidate materials for use in high temperature, high loading applications. In particular, an MMC consisting of a titanium alloy reinforced with silicon-carbide fibers is being considered for use on the National Aerospace Plane (NASP). Compared to other metals and metallic alloys, titanium alloys retain relatively high stiffness, strength, and corrosion resistance at elevated temperatures. However, above roughly 316 C titanium exhibits a significant thermoviscoplastic (creep) response. Since the temperatures encountered in many regions of the NASP are expected to exceed 316 C, the potential thermoviscoplastic behavior of titanium-based MMC's at elevated temperatures must be thoroughly investigated. Tuttle, M. E. and Rogacki, J. Unspecified Center CREEP PROPERTIES; CYCLIC LOADS; HEAT RESISTANT ALLOYS; METAL MATRIX COMPOSITES; SPACECRAFT CONSTRUCTION MATERIALS; THERMOPLASTICITY; TITANIUM ALLOYS; VISCOPLASTICITY; AEROSPACE PLANES; AIRCRAFT CONSTRUCTION MATERIALS; CORROSION RESISTANCE; HIGH STRENGTH ALLOYS; MICROSTRUCTURE; NATIONAL AEROSPACE PLANE PROGRAM; REINFORCING FIBERS; SILICON CARBIDES; STIFFNESS; TITANIUM...
Author: CC. Chamis
Publisher:
ISBN:
Category : Mechanical properties
Languages : en
Pages : 20
Get Book Here
Book Description
A set of thermoviscoplastic nonlinear constitutive relationships (TVP-NCR) is presented. This set is unique and has been developed mainly for application to high-temperature metal matrix composites (HT-MMC) and is applicable to thermal and mechanical properties. Formulation of the TVP-NCR is based at the micromechanics level. The TVP-NCR are of simple form and readily integrated into nonlinear composite structural analysis. Results show that this unique set of TVP-NCR is computationally effective. It provides a direct means for predicting complex materials behavior at all levels of the composite simulation; that is, from the constituent materials, through the several levels of composite mechanics, and up to the global response of complex HT-MMC structural components.
Author: W. Steven Johnson
Publisher: ASTM International
ISBN: 0803120397
Category : Metallic composites
Languages : en
Pages : 625
Get Book Here
Book Description
Papers presented at the March 1994 symposium are organized into five sections that progress from basic understanding of mechanical damage mechanisms and environmental effects to life prediction methodology. Five papers discuss the interplay between interfacial strength, residual thermal stresses, an
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1156
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 868
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Engines
Languages : en
Pages : 232
Get Book Here
Book Description
Author: Eric Buzaud
Publisher: John Wiley & Sons
ISBN: 1118622316
Category : Technology & Engineering
Languages : en
Pages : 405
Get Book Here
Book Description
This book presents recent and cutting edge advances in our understanding of key aspects of the response of materials under extreme loads that take place during high velocity impact and penetration. The focus of the content is on the numerous challenges associated with characterization and modeling of complex interactions that occur during these highly dynamic events. The following specific topics, among others, are addressed: characterization of material behavior under extreme loadings (estimate of damage, effects related to moisture contents, large pressures, large strain rates, etc.); measurement of microstructural changes associated with damage and mesoscopic scale modeling; macroscopic modeling, using the framework of the theory of viscoplasticity and damage; modeling and simulation of localization, cracking, and dynamic fragmentation of materials; application to penetration mechanics and trajectory instabilities. The book gathers together selected papers based on work presented as invited lectures at the 2nd US-France symposium held on 28-30 May 2008 in Rocamadour, France. The conference was organized by Eric Buzaud (DGA, Centre d'Études de Gramat) under the auspices of the International Center for Applied Computational Mechanics (ICACM).
