Effect of load duration on the fatigue behaviour of graphite/epoxy laminates containing delaminations

Saunders, D. S.; Blaricum, T.J. Van

doi:10.1016/0010-4361(88)90240-6

Cited by 18 publications

(5 citation statements)

References 4 publications

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“…As is the case with the growth of delamination damage the large scatter associated with impact damage growing under operational flight load spectra is large. [30][31][32] Much more recently Molent and Forrester 33 suggest that the "fastest" growing impact damage is an exponential function of the flight loads and therefore conforms to the formulation outlined in the USAF approach to assessing the risk of failure. 20…”

Section: Impact Damagementioning

confidence: 82%

A review of composite product data interoperability and product life-cycle management challenges in the composites industry

McMillan

Swindells

Archer

et al. 2017

Advanced Manufacturing: Polymer & Composites Science

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A review of composite product data interoperability and product life-cycle management challenges is presented, which addresses "Product Life-cycle Management", developments in materials. The urgent need for this is illustrated by the life-cycle management issues faced in modern military aircraft, where in-service failure of composite parts is a problem, not just in terms of engineering understanding, but also in terms of the process for managing and maintaining the fleet. A demonstration of the use of ISO 10303-235 for a range of through-life composite product data is reported. The standardization of the digital representation of data can help businesses to automate data processing. With the development of new materials, the requirements for data information models for materials properties are evolving, and standardization drives transparency, improves the efficiency of data analysis, and enhances data accuracy. Current developments in Information Technology, such as big data analytics methodologies, have the potential to be highly transformative.

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Section: Impact Damagementioning

confidence: 82%

A review of composite product data interoperability and product life-cycle management challenges in the composites industry

McMillan

Swindells

Archer

et al. 2017

Advanced Manufacturing: Polymer & Composites Science

View full text Add to dashboard Cite

show abstract

“…This phenomena has been observed in other studies that examined the residual strength of specimens that had survived a fatigue regimen [3,6,7,9,12,19,25]. Only one reference could be found where fatigue decreased the CAI strength of laminates [18]. In that reference, the high amplitude loads were held for 120 s perhaps indicating a creep rupture phenomena that may need to be explored for parts experiencing long dwell times at UL.…”

Section: Fatigue Testingmentioning

confidence: 87%

“…It was of interest to see if other experimental programs found damage growth (using any NDE technique), so a 'growth detected' column was added. Since two of the studies [17,18] used variable amplitude fatigue spectrums, the maximum amplitude in the spectrum is presented. The corresponding cycles are numbers of cycles to this maximum load, while no other load excursions are counted.…”

Section: Effects Of Fatiguementioning

confidence: 99%

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An Examination of the Compressive Cyclic Loading Aspects of Damage Tolerance for Polymer Matrix Launch Vehicle Hardware

Nettles

Hodge

Jackson

2010

Journal of Composite Materials

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The issue of fatigue loading of structures composed of composite materials is considered in a requirements document that is currently in place for manned launch vehicles. By taking into account the short lives of these parts, coupled with design considerations, it is demonstrated that the necessary coupon level fatigue data collapse to a static case. Data from a literature review of past studies that examined compressive fatigue loading after impact and data generated from this experimental study are presented to support this finding. In other studies from the literature, a stress amplitude of about 60% of the static compression after impact (CAI) strength was found to exist, below which fatigue had no deleterious effects up to one million cycles. In this study, a stress amplitude of about 80% of the static (CAI) strength was found to exist, below which fatigue had no deleterious effects up to 10,000 cycles. A launch vehicle structure should never experience one cycle above 61.4% of static CAI strength, much less 10,000 at 80%. Despite utilizing severe fatigue amplitude loading in impact damaged coupons, residual strength after fatigue was consistently higher than expected. Unrealistically high fatigue stress amplitudes were needed to fail 5 of 15 specimens, before 10,000 cycles was reached. Since a typical launch vehicle structure, such as the ARES I interstage, only experiences a few cycles near limit load, it is concluded that static CAI strength data will suffice for most launch vehicle structures.

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“…If any growth was detected, it happened at high load levels and close to the ultimate collapse [12,[31][32][33]. Only in few cases, a significant period of delamination growth before the collapse is reported [11,25,34,35]. In another review article, Molent and Haddad investigate various experimental damage growth studies from the literature.…”

Section: Introductionmentioning

confidence: 99%

An Experimental Study of the Cyclic Compression after Impact Behavior of CFRP Composites

Bogenfeld

Gorsky

2021

J. Compos. Sci.

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The behavior of impact damaged composite laminates under cyclic load is crucial to achieve a damage tolerant design of composite structures. A sufficient residual strength has to be ensured throughout the entire structural service life. In this study, a set of 27 impacted coupon specimens is subjected to quasi-static and cyclic compression load. After long intervals without detectable damage growth, the specimens fail through the sudden lateral propagation of delamination and fiber kink bands within few load cycles. Ultrasonic inspections were used to reveal the damage size after certain cycle intervals. Through continuous dent depth measurements during the cyclic tests, the evolution of the dent visibility was monitored. These measurements revealed a relaxation of the indentation of up to 90% before ultimate failure occurs. Due to the distinct relaxation and the short growth interval before ultimate failure, this study confirms the no-growth design approach as the preferred method to account for the damage tolerance of stiffened, compression-loaded composite laminates.

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Effect of load duration on the fatigue behaviour of graphite/epoxy laminates containing delaminations

Cited by 18 publications

References 4 publications

A review of composite product data interoperability and product life-cycle management challenges in the composites industry

A review of composite product data interoperability and product life-cycle management challenges in the composites industry

An Examination of the Compressive Cyclic Loading Aspects of Damage Tolerance for Polymer Matrix Launch Vehicle Hardware

An Experimental Study of the Cyclic Compression after Impact Behavior of CFRP Composites

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