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Book: Fatigue and Fracture
Series: ASM Handbook
Volume: 19
Publisher: ASM International
Published: 01 January 1996
DOI: 10.31399/asm.hb.v19.a0002392
EISBN: 978-1-62708-193-1
... approaches to corrosion identification and prevention. These include safe-life, fail-safe, and damage tolerance approaches. The article discusses their application to the process of extending the life of aircraft structural components. aircrafts corrosion damage tolerance fatigue life fracture...
Abstract
This article describes two analysis methods that are used to determine the life of aircrafts: fatigue life and fracture mechanics methods. The life limiting factors that control the durability of the aircraft are also discussed. The article provides an overview of the various approaches to corrosion identification and prevention. These include safe-life, fail-safe, and damage tolerance approaches. The article discusses their application to the process of extending the life of aircraft structural components.
Book: Fatigue and Fracture
Series: ASM Handbook
Volume: 19
Publisher: ASM International
Published: 01 January 1996
DOI: 10.31399/asm.hb.v19.a0002393
EISBN: 978-1-62708-193-1
... Abstract Damage tolerance is a philosophy used for maintaining the structural safety of commercial transport aircrafts. This article describes the structural evaluations necessary to comply with the regulations contained in the Federal Air worthiness Requirements 25.571 whose guidance is given...
Abstract
Damage tolerance is a philosophy used for maintaining the structural safety of commercial transport aircrafts. This article describes the structural evaluations necessary to comply with the regulations contained in the Federal Air worthiness Requirements 25.571 whose guidance is given in Advisory Circular 25.571-1A from the Federal Aviation Administration. It provides an overview of the historical evolution of damage tolerance philosophy and presents a discussion of the design philosophies and a summary of the evaluation tasks for damage tolerance certification.
Book: Fatigue and Fracture
Series: ASM Handbook
Volume: 19
Publisher: ASM International
Published: 01 January 1996
DOI: 10.31399/asm.hb.v19.a0002381
EISBN: 978-1-62708-193-1
... principles of fracture control and reviews the concepts of damage tolerance analysis. It further presents practical guidelines to obtain useful and reasonable answers from damage tolerance analysis. The article concludes with information on fracture mechanics and fatigue design. damage tolerance...
Abstract
Fracture control is a systematic process to prevent fracture during operation that depends on the criticality of the component, the economic consequences of the structures being out of service, and the damage that would be caused by a fracture failure. This article describes the key principles of fracture control and reviews the concepts of damage tolerance analysis. It further presents practical guidelines to obtain useful and reasonable answers from damage tolerance analysis. The article concludes with information on fracture mechanics and fatigue design.
Book: Fatigue and Fracture
Series: ASM Handbook
Volume: 19
Publisher: ASM International
Published: 01 January 1996
DOI: 10.31399/asm.hb.v19.a0002382
EISBN: 978-1-62708-193-1
... Abstract Damage tolerance analysis consists of three parts such as the calculation of the residual strength diagram to obtain the permissible crack size, calculation of the crack growth curve, and calculation of the inspection interval. This article discusses the aspects of obtaining material...
Abstract
Damage tolerance analysis consists of three parts such as the calculation of the residual strength diagram to obtain the permissible crack size, calculation of the crack growth curve, and calculation of the inspection interval. This article discusses the aspects of obtaining material property data and geometry factors to analyze any fracture or crack growth problem. It describes the integration of crack growth rates in terms of constant-amplitude loading and cycle-by-cycle counting with variable-amplitude loading. The article concludes with information on the classification of sources of error in damage tolerance analysis.
Book: Composites
Series: ASM Handbook
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003386
EISBN: 978-1-62708-195-5
... Abstract This article addresses the issue of the implementation of composite damage tolerance requirements as it relates to military aircraft. It presents a brief introduction on the durability impact threat, damage tolerance impact threat, and other damage tolerance damage threats. The article...
Abstract
This article addresses the issue of the implementation of composite damage tolerance requirements as it relates to military aircraft. It presents a brief introduction on the durability impact threat, damage tolerance impact threat, and other damage tolerance damage threats. The article summarizes damage tolerance criteria and durability criteria for military aircraft. It discusses the damage tolerance design philosophy for metallic structures and composite structures of the aircraft. The article describes the implementation of a damage tolerance analysis methodology in terms of the mechanics based model, the regression algorithm, and the semi-empirical analysis.
Book Chapter
Series: ASM Handbook
Volume: 2B
Publisher: ASM International
Published: 15 June 2019
DOI: 10.31399/asm.hb.v02b.a0006617
EISBN: 978-1-62708-210-5
... Abstract Alloy 2624 was developed by Alcoa as a plate product to replace alloy 2024 and 2324 in applications requiring moderate or high strength and the highest levels of damage tolerance. This datasheet provides information on composition limits, processing effects on physical and mechanical...
Abstract
Alloy 2624 was developed by Alcoa as a plate product to replace alloy 2024 and 2324 in applications requiring moderate or high strength and the highest levels of damage tolerance. This datasheet provides information on composition limits, processing effects on physical and mechanical properties, and applications of this alloy. Figures provide comparisons of plane stress R-curves of 2624 with 2024-T351 and 2324-T39 and fatigue crack growth resistance of 2624 with 2024-T351 and 2324-T39.
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Published: 01 January 2006
Fig. 16 Application of damage tolerance by ENSIP (a) and RFC (b) and relation to safe inspection interval (SII)
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Published: 01 January 1996
Fig. 24 Comparison of damage tolerance life of 8090-T852 and 7050-T7452 in normal air and saline environments for R = 0.1. Source: Ref 57
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Published: 01 January 2002
Fig. 7 Damage tolerance approach to life management of cyclic-limited engine components. The safety limit or residual life is the time for the initial flaw to grow and cause failure. The size of the initial flaw, a i , is based on the inspection method or material defect distribution
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in Failure Analysis and Life Assessment of Structural Components and Equipment
> Failure Analysis and Prevention
Published: 01 January 2002
Fig. 12 Damage-tolerance approach to life assessment. Curves indicate progression of damage from different nucleating conditions, with broken segments representing regimes in which a perfect NDE technique would remove the component from service.
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Published: 01 January 2002
Fig. 3 Illustration of the damage tolerance approach to life assessment. Curves indicate progression of damage from different nucleating conditions, with broken segments representing regimes in which a perfect NDE technique would remove the component from service
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Published: 01 January 2001
Fig. 1 Damage tolerance of a metallic structure based on initial design. Flaw size (broken line) and residual strength (solid line) are plotted versus time.
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Published: 01 January 2001
Fig. 2 Damage tolerance of a metallic structure based on actual usage. Flaw size (broken line) and residual strength (solid line) are plotted versus time. Analytical life is reduced due to increased loading, severity of usage, or the discovery of analytical errors in the original life
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Published: 01 January 2001
Fig. 3 Damage tolerance of a composite structure based on initial design. Flaw size (broken line) and residual strength (solid line) are plotted versus time. The step function nature of the curves represents large growths in the degradation associated with the highest load cycles in each block
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Published: 01 January 2001
Fig. 4 Damage tolerance of a composite structure based on actual usage. Flaw size (broken line) and residual strength (solid line) are plotted versus time. Increased loading could lead to static failure. Increase in the spectrum severity does not affect the compression after impact failure
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Published: 01 August 2018
Fig. 9 Damage tolerance approach to life management of operational cycle limited jet engine components. The safety limit or residual life is the time for an initial flaw to grow and cause failure. The size of the initial flaw, a i , is based on the inspection method or material defect
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in Failure Prevention through Life Assessment of Structural Components and Equipment
> Analysis and Prevention of Component and Equipment Failures
Published: 30 August 2021
Fig. 12 Damage-tolerance approach to life assessment. Curves indicate progression of damage from different nucleating conditions, with broken segments representing regimes in which a perfect nondestructive evaluation technique would indicate removal of the component from service.
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Published: 15 June 2019
Fig. 1 Damage tolerance of 2055-T84 extrusions and 7 xxx extrusions. (a) toughness as a function of strength, (b) fatigue crack growth curves (L-T orientation). Note: T7E127 is Arconic’s internal designation for an age formable temper. Courtesy of Arconic, ATI- 2055 Fact Sheet
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Book: Fatigue and Fracture
Series: ASM Handbook
Volume: 19
Publisher: ASM International
Published: 01 January 1996
DOI: 10.31399/asm.hb.v19.a0002394
EISBN: 978-1-62708-193-1
... Abstract The inclusion of damage tolerance design and a systematic review of design procedures allow the U.S. Air Force to design, manufacture, and maintain systems that are structurally safe and economically prudent. After a brief introduction of fracture mechanics, this article describes...
Abstract
The inclusion of damage tolerance design and a systematic review of design procedures allow the U.S. Air Force to design, manufacture, and maintain systems that are structurally safe and economically prudent. After a brief introduction of fracture mechanics, this article describes the particular aspects that relate to damage tolerance in aircraft design. It discusses the use of fracture mechanics as a method of predicting failure, understanding failure mechanisms, and suggesting inspection methods to protect against failure in pressure vessels. Various programs of U.S. Air Force to design aircraft structure, namely, airframe structural integrity programs, engine structural integrity program, and mechanical subsystems structural integrity program are also discussed.
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in Aluminum-Lithium Alloys
> Properties and Selection: Nonferrous Alloys and Special-Purpose Materials
Published: 01 January 1990
Fig. 24 S-N fatigue life curves for damage-tolerant 8090 sheet (8090-T81) and clad 2024-T3 sheet. Stress ratio ( R ), 0.1; cyclic frequency, 80 Hz. (a) Smooth specimens. Theoretical stress concentration factor ( K t ) = 1. (b) Notched specimens. K t = 2.6
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