Filtern
Dokumenttyp
- Vortrag (5)
- Beitrag zu einem Sammelband (1)
- Beitrag zu einem Tagungsband (1)
- Dissertation (1)
Referierte Publikation
- nein (8)
Schlagworte
- CFRP (4)
- Damage evolution (2)
- FRP (2)
- Fatigue (2)
- X-ray (2)
- CFK (1)
- Carbon fibre-reinforced-plastics (1)
- Epoxidharz (1)
- Ermüdung (1)
- Faser-Kunststoff Verbunde (1)
Organisationseinheit der BAM
Eingeladener Vortrag
- nein (5)
In der vorliegenden Arbeit wurden verschiedene Epoxidharzsysteme charakterisiert. Zwei Systeme mit großen bruchmechanischen Unterschieden wurden zur Fertigung äquivalenter GFK- und CFK-Laminate mit Faserausrichtungen in 0/90° und ±45° ausgewählt. In quasi-statischen Zugversuchen und Einstufenschwingversuchen mit einem Beanspruchungsverhältnis von R= 0,1 wurden diese Laminate hinsichtlich ihres Schädigungsbeginns und ihrer Schädigungsentwicklung untersucht. Die Detektion der Schädigungen sowie die Dokumentation der Schädigungsentwicklung wurde anhand der Lichtabsorptionsanalyse an GFK-Laminaten und anhand der Röntgenrefraktionsanalyse an CFK-Laminaten umgesetzt. Auf diese Weise konnten Einflüsse der bruchmechanischen Eigenschaften der Matrix auf die Schädigungsentwicklung im Verbund aufgezeigt werden. Zudem wurden für die untersuchten Laminate die Schädigungsgrenzen bei schwingender Beanspruchung ermittelt. Anhand durchgeführter Schwingversuche an CFK-Laminaten im Very High Cycle Fatigue-(VHCF)-Lastwechselbereich bis 108 konnten Rückschlüsse vom Schädigungsverhalten im High Cycle Fatigue-(HCF)-Lastwechselbereich bis 106 auf die Dauerfestigkeit im VHCF-Bereich gezogen werden und damit VHCF-Dauerfestigkeitsgrenzen bestimmt werden. Mit dem Ziel die Ermüdung der Laminate auf die Beanspruchung der Matrix zurückzuführen, wurden die Erweiterte Inverse Laminattheorie, mikromechanikbasierte Mischungsregeln sowie eine Vergleichsspannungshypothese auf die untersuchten Laminate angewendet. Die Schädigungsgrenzen konnten damit in Form der Matrixbeanspruchung wiedergegeben werden. Die Abbildung der Ermüdung verschiedener Laminate anhand einer matrixspezifischen normierten Masterschädigungslinie ist für die behandelten CFK- und GFK-Laminate gelungen.
Nondestructive investigation of the VHCF-endurance on cyclically loaded CFRP by X-Ray-Refractography
(2016)
Carbon fiber-reinforced-plastics (CFRP) are already used under high-cycle- (HCF) and very-high-cycle-fatigue (VHCF) at relatively low loads not only in aerospace industry, but also in other growing markets like especially wind energy and increasingly also automotive industry. While the static strength of CFRP is satisfyingly predictable by means of layerwise-strenght-analysis and material data from single layers, it is more and more uncertain to predict residual strength or lifetime as the design lifetime increases. Previous studies showed that local minor cracks and inter-fiber-fracture (IFF) originate long before total failure of single layers. Reliable fatigue estimation for fiber-reinforced-plastics is not available at present. Subsequently safety-related primary structures made out of FRP are over dimensioned.
It is possible to detect the change of inner surface in a specimen by means of X-Ray-Refractography. This includes voids, intact fiber-matrix-interfaces as well as defective ones, cracks and all interfaces in plane with the X-Ray-beam. As the crack-density (including IFF) increases, the inner surface of the material correspondingly increases.
The borderline where even at high cycles no early cracks were detected was identified for selected laminates out of woven and non-crimped fabric with epoxy-matrix.
When no micro-cracks were detected up to 106 cycles, the specimens also lasted in the VHCF-regime. Furthermore for the epoxy resin LY556 in combination with carbon fiber it was distinguished that at a load minor to 50% IFF-load level, no micro cracks were detected and consequently the VHCF-endurance reached.
The integration of the set-up small-sized testing machine into the X-Ray buildup in order to achieve in-situ non-destructive detection of the crack initiation while loading the specimens (CFRP and GFRP- woven fabric and non-crimped-fabric) at the same time will increase the performance of the studies.
In earlier investigations at BAM it was shown, that the matrix has a strong influence on the micro-crack formation and finally on the total lifetime. In order to determine the influence of the matrix properties on the boarderline to infinite life, research is done on laminates while replacing the epoxy-based matrix with an equivalent one with different fracture mechanical properties.
With the evolution of early cracks and IFF monitored as well as the influence of the matrix on the crack propagation investigated we are working on an appropriate model to improve lifetime prediction in CFRP. This work is done within the priority program “infinite life” (SPP 1466) funded by Deutsche Forschungsgemeinschaft (DFG).
Nondestructive investigation of the VHCF-endurance on cyclically loaded CFRP by X-Ray-Refractography
(2016)
Carbon fiber-reinforced-plastics (CFRP) are already used under high-cycle- (HCF) and very-high-cycle-fatigue (VHCF) at relatively low loads not only in aerospace industry, but also in other growing markets like especially wind energy and increasingly also automotive industry. While the static strength of CFRP is satisfyingly predictable by means of layerwise-strenght-analysis and material data from single layers, it is more and more uncertain to predict residual strength or lifetime as the design lifetime increases. Previous studies showed that local minor cracks and inter-fiber-fracture (IFF) originate long before total failure of single layers. Reliable fatigue estimation for fiber-reinforced-plastics is not available at present. Subsequently safety-related primary structures made out of FRP are over dimensioned.
It is possible to detect the change of inner surface in a specimen by means of X-Ray-Refractography. This includes voids, intact fiber-matrix-interfaces as well as defective ones, cracks and all interfaces in plane with the X-Ray-beam. As the crack-density (including IFF) increases, the inner surface of the material correspondingly increases.
The borderline where even at high cycles no early cracks were detected was identified for selected laminates out of woven and non-crimped fabric with epoxy-matrix.
When no micro-cracks were detected up to 106 cycles, the specimens also lasted in the VHCF-regime. Furthermore for the epoxy resin LY556 in combination with carbon fiber it was distinguished that at a load minor to 50% IFF-load level, no micro cracks were detected and consequently the VHCF-endurance reached.
The integration of the set-up small-sized testing machine into the X-Ray buildup in order to achieve in-situ non-destructive detection of the crack initiation while loading the specimens (CFRP and GFRP- woven fabric and non-crimped-fabric) at the same time will increase the performance of the studies.
In earlier investigations at BAM it was shown, that the matrix has a strong influence on the micro-crack formation and finally on the total lifetime. In order to determine the influence of the matrix properties on the boarderline to infinite life, research is done on laminates while replacing the epoxy-based matrix with an equivalent one with different fracture mechanical properties.
With the evolution of early cracks and IFF monitored as well as the influence of the matrix on the crack propagation investigated we are working on an appropriate model to improve lifetime prediction in CFRP. This work is done within the priority program “infinite life” (SPP 1466) funded by Deutsche Forschungsgemeinschaft (DFG).
Faser-Kunststoff Verbunde und insbesondere Kohlenstofffaserverstärkte Kunststoffe werden bereits im Bereich der hohen (HCF) und sehr hohen Lastspielzahlen (VHCF) eingesetzt. Während statische Festigkeiten für diese Materialien bereits gut vorhersagbar sind, gibt es noch keine verlässliche Methode Schwingfestigkeiten zu bestimmen.
Vergangene Studien an Faser-Kunststoff Verbunden an der BAM zeigten, dass bei Schwingbelastung Mikrorisse und Zwischenfaserrisse bereits weit vor dem finalen Versagen auftreten. Diese Schäden erhöhen die innere Oberfläche des Materials. Die Änderung der inneren Oberfläche kann mittels der Röntgenrefraktion bestimmt werden.
Damit konnte im Rahmen der aktuellen Arbeit eine Lastgrenze ermittelt werden, bei der im untersuchten Lastwechselbereich keine Mikrorisse auftreten. Unter den gegebenen Material- und Versuchsparametern kann damit von einer ermittelten Dauerfestigkeitsgrenze gesprochen werden.
Carbon Fibre Reinforced Plastics (CFRP) are more and more used in modern civil aircrafts. These days the whole fuselage is made of this material (B787; A350). Due to strict certification standards the normal in-service loading gives a low stress level compared to the static and even the fatigue strength of the material. Hence CFRP are assumed to have an infinite life. To evaluate this assumption, fatigue tests on CFRP-specimens were performed up to 108 load cycles and the first inter-fibre failure was evaluated non-destructively by accompanying Xray-refraction topography. A tensile testing machine was integrated in a small angle X-ray scattering (SAXS) setup. X-ray refraction topography was performed while the CFRP samples were tensile loaded. This non-destructive technique enables the detection of micro-cracking and inter-fibre failure especially for CFRP. For Glass Fibre Reinforced Plastic (GFRP) X-ray refraction and in-situ loading has already been successfully used. The increase of inner surfaces due to inter fibre failure was measured as a function of the stress state. Fatigue tests were performed at and below the limit of inter-fibre failure strength. State of the art is to assume the failure of the samples under cyclic loading as the fatigue life. Accompanying non-destructive X-ray refraction measurements reflects the damage state and enables to trace its evolution even if the total failure of the specimens does not occur. This investigation technique is of high interest to give the engineer a design value of infinite life which is practically often reached due to knock down factors of certification standards. Finally the infinite life was found for cyclic fatigue loaded CFRP-samples even under high inter fibre transverse and shear loading investigated up to 108 load cycles.
The described investigation of carbon-fibre-reinforced plastics (CFRP) documents that damage evolution can be observed by means of X-ray refractography. Comparative investigations with synchrotron technique on CFRP and grey-scale analysis on glass fibre-reinforced-plastics (GFRP) confirm these results. Moreover it was found that the fracture mechanical properties of the matrix system influence damage nucleation and propagation in the laminate during static and fatigue loads. Single-step fatigue tests were carried out on Laminates with RIM135 and LY556 matrix systems made from non-crimped fabric (NCF) or twill weave in different fibre orientations. The damage to the LY556 laminates was characterized by laminate cracks growing rapidly over the whole specimen width, whereas the damage on the RIM135 laminates was characterized by an earlier onset of micro-cracking followed by laminate cracks. The specimens were fatigued up to 108 (very high cycle fatigue (VHCF) regime) load cycles. S-N-curves of damage initiation were drawn and boundaries were identified for endurance within the VHCF regime. A phenomenology based model focusing on matrix stress was applied to reproduce the first inter-fibre failure (IFF) under static and fatigue loads.