Comparison of Graphite Fabric Reinforced PMR-15 and Avimid N Composites After Long Term Isothermal Aging at Various Temperatures PDF Download

Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 34

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Author: F. C. Campbell
Publisher: ASM International
ISBN: 1615031405
Category : Technology & Engineering
Languages : en
Pages : 622

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This book deals with all aspects of advanced composite materials; what they are, where they are used, how they are made, their properties, how they are designed and analyzed, and how they perform in-service. It covers both continuous and discontinuous fiber composites fabricated from polymer, metal, and ceramic matrices, with an emphasis on continuous fiber polymer matrix composites.

Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722108601
Category :
Languages : en
Pages : 30

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Extensive effort is currently being expended to demonstrate the feasibility of using high-performance, polymer-matrix composites as engine structural materials over the expected operating lifetime of the aircraft, which can extend from 18,000 to 30,000 hr. The goal is to develop light-weight, high-strength, and high-modulus materials for use in higher temperature sections of advanced 21 st century aircraft propulsion systems. To accomplish this goal, it is necessary to pursue the development of thermal and mechanical durability models for graphite-fiber-reinforced, polymer-matrix composites. Numerous investigations have been reported regarding the thermo-oxidative stability (TOS) of the polyimide PMR-15 (1-5). A significant amount of this work has been directed at edge and geometry effects, reinforcement fiber influences, and empirical modeling of high-temperature weight loss behavior. It is yet to be determined if the information obtained from the PMR-15 composite tests is applicable to other polyimide-matrix composites. The condensation-curing polymer Avimid N is another advanced composite material often considered for structural applications at high temperatures. Avimid N has better thermo-oxidative stability than PMR-15 (6), but the latter is more easily processed. The most comprehensive study of the thermo-oxidative stability of Avimid N neat resin and composites at 371 (infinity)C is found in Salin and Seferis (7). The purposes of the work described herein were to compare the thermal aging behavior of these two matrix polymers and to determine the reasons for and the consequences of the difference in thermal durability. These results might be of some use in improving future polymer development through the incorporation of the desirable characteristics of both polyimides. Bowles, Kenneth J. and McCorkle, Linda and Ingrahm, Linda Glenn Research Center NAS3-27351; RTOP 538-06-15...

Author: Vincent K. S. Choo
Publisher: Knowen Academic Press, Incorporated
ISBN: 9780929785004
Category : Composite materials
Languages : en
Pages : 313

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Author: Brian Cantor
Publisher: CRC Press
ISBN: 1420033972
Category : Science
Languages : en
Pages : 432

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With contributions from leading experts in their respective fields, Metal and Ceramic Matrix Composites provides a comprehensive overview of topics on specific materials and trends. It is a subject regularly included as a final year option in materials science courses and is also of much industrial and academic interest. The book begins wit

Author: P Camanho
Publisher: Elsevier
ISBN: 0857094920
Category : Technology & Engineering
Languages : en
Pages : 537

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The growing use of composites over metals for structural applications has made a thorough understanding of the behaviour of composite joints in various applications essential for engineers, but has also presented them with a new set of problems. Composite joints and connections addresses these differences and explores the design, modelling and testing of bonded and bolted joints and connections.Part one discusses bolted joints whilst part two examines bonded joints. Chapters review reinforcement techniques and applications for composite bolted and bonded joints and investigate the causes and effects of fatigue and stress on both types of joint in various applications and environments. Topics in part one include metal hybridization, glass-reinforced aluminium (GLARE), hybrid fibre metal laminates (FML), glass fibre reinforced polymer (GFRP) and carbon fibre reinforced polymer (CFRP) composites. Topics in part two include calculation of strain energy release rates, simulating fracture and fatigue failure using cohesive zone models, marine and aerospace applications, advanced modelling, stress analysis of bonded patches and scarf repairs.Composite joints and connections is a valuable reference for composite manufacturers and composite component fabricators, the aerospace, automotive, shipbuilding and civil engineering industries and for anyone involved in the joining and repair of composite structures. - Explores the design, modelling and testing of bonded and bolted joints and connections - Reviews reinforcement techniques and applications for composite bolted and bonded joints - Investigates the causes and effects of fatigue and stress on bolted and bonded joints in various applications and environments

Author: Shankar Mall
Publisher: CRC Press
ISBN: 1000725472
Category : Technology & Engineering
Languages : en
Pages : 482

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A review and summary of advancements related to mechanical behavior and related mechanics issues of titanium matrix composites (TMCs), a class of high-temperature materials useful in the propulsion and airframe components in advanced aerospace systems. After an introduction to TMCs, different authors review and summarise the advancements related to mechanical behavior and related mechanics issues of TMCs.

Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722047368
Category :
Languages : en
Pages : 26

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The purposes of this study were to evaluate the growth of the surface damage layer in polymer matrix composites (PMC's) fabricated with graphite fabric reinforcement and to determine the effects of the cut-surface degradation on the overall thermo-oxidative (TOS) stability of these materials. Four important conclusions were made about the TOS behavior of T650-35/PNIR- 15 fabric-reinforced composites: (1) Three stages of composite weight loss were seen on the plot of weight loss versus aging time; (2) the depth of the cut-edge damage is related to the composite thickness; (3) the actual weight loss realized by a mechanical test specimen that has had all the aging-induced cut-edge damage removed during the preparation process is significantly less than the weight loss measured using specimens with a high percentage of cut edges exposed to the damaging environment; and (4) an extrapolation of a section of the weight loss curve can be used to obtain a more correct estimate of the actual weight loss after extended periods of aging at elevated temperatures. Bowles, Kenneth J. Glenn Research Center RTOP 538-06-15...

Author: Madhu S. Madhukar
Publisher:
ISBN:
Category : Fibrous composites
Languages : en
Pages : 32

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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781720615163
Category :
Languages : en
Pages : 64

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A cooperative program was conducted with the General Electric Aircraft Engines plant in Evendale, Ohio, to study the effects of long-term isothermal aging at elevated temperatures on compression and thermal durability properties of T650 35 fabric-reinforced PMR 15 composites. This degradation study was conducted over an approximate time period of 3 1/2 yr. The aging temperatures were 204, 260, 288, 316, and 343 C. Specimens of different dimensions were evaluated. Specimens with ratios of the cut edge to total surface area of 0.03 to 0.89 were fabricated and aged. The aged and unaged specimens were tested in compression as specified in Test Method for Compressive Properties of Rigid Plastics (ASTM D695M). Thickness changes, degraded surface layer growth, weight loss, and failure modes were monitored and recorded. All property changes were thickness dependent.Bowles, Kenneth J. and Tsuji, Luis and Kamvouris, John and Roberts, Gary D.Glenn Research CenterAGING (MATERIALS); ISOTHERMAL PROCESSES; FABRICATION; MECHANICAL PROPERTIES; POLYIMIDES; STRUCTURAL WEIGHT; COMPRESSIBILITY; COMPOSITE MATERIALS; FAILURE MODES; DURABILITY; PLASTICS; THICKNESS; DEGRADATION; SURFACE LAYERS; HIGH TEMPERATURE