Filtern
Erscheinungsjahr
Dokumenttyp
- Zeitschriftenartikel (22) (entfernen)
Schlagworte
- Fatigue (3)
- Fire stability (3)
- Fully developed fire (3)
- Composite (2)
- Curing kinetics (2)
- High-temperature properties (2)
- Buckling (1)
- CFRP (1)
- Carbon Fiber Reinforced Plastics (1)
- Carbon fiber reinforced polymer (CFRP) (1)
Organisationseinheit der BAM
Paper des Monats
- ja (1)
Moderne Leichtbaustrukturen (Luftfahrt, Eisenbahn, Automotive) aus Faserverbundwerkstoffen (FVW) sind hohen mechanischen und klimatischen Beanspruchungen ausgesetzt. Aussagen über die Lebensdauer und Funktionssicherheit der FVW-Bauteile können eher aus Untersuchungen der mikromechanischen Eigenschaften gewonnen werden als aus der globalen Festigkeit. Die Röntgenrefraktionstopografie ist ein Verfahren zur zerstörungsfreien Bestimmung von inneren Oberflächen in Werkstoffen. Angewendet auf FVW lassen sich Aussagen über die Faserorientierungen, die Fertigungsqualität sowie über Faser-Matrix-Ablösungen und Matrixrisse infolge mechanischer Beanspruchung gewinnen. Nachfolgend wird ein neues Verfahren zur Bestimmung des Zwischenfaserbruchversagens am komplexen Laminat vorgestellt. Hierbei wird das Röntgenrefraktionsverfahren "online bei Zug-Belastung der Probe angewendet.
A new approach is discussed for characterizing the damage state of FRP with the appearance of micro cracking and its influence on the residual strength. For the quantitative analysis of micro cracking, X-ray refraction topography was used. Fatigue treatment of carbon fibre reinforced plastics (CFRP) laminates were performed to create defined damage states. With regard to real loading conditions of CFRP, studies on tube samples were performed to investigate two dimensional (tensiontorsion) loads. A rheological material model was presented which described the increase of micro cracking in ±45° CFRP laminates with a continuum mechanical approach. The correlation between the results of the X-ray refraction topography, the damage parameter of the rheological model and the decrease of residual strength were shown. The inter fibre fracture surface of the investigated CFRP materials was determined with tensiontorsion loaded tube specimens of 90°-laminate and a layer-wise strength analysis was done. Micro cracking occurs even at 50% inter-fibre fracture loading and can lead to a distinct strength reduction. The intralaminar fatigue effect itself seems to be an indication for the damage accumulation and the load history.
A test set-up in intermediate scale was conceived to investigate the structural integrity of materials under fire. The task was to develop a realistic test scenario targeting component-like behaviour. Carbon-fibre-reinforced sandwich specimens (500 X 500 X 20 mm) were used to examine failure mechanisms, times to failure and critical failure loads under compression. Fire tests were performed with fully developed fire applied to one side of the specimen by an oil burner. In a first test series, the applied load was varied, but the fully developed fire remained unchanged. In general, times to failure were short. Decreased load levels resulted in prolonged times to failure and led to a different failure mechanism. Results obtained in the test series were compared with a bench-scale study (150 X 150 X 20 mm) investigating identical material. The comparison clearly revealed the influence of size on the time to failure and the load-bearing capacity.
In a research project fatigue tests on two identical wing sections that are used as representative substitute components were performed to estimate lifetime enhancement of light-weight aircraft such as general aviation gliders. Single step fatigue tests at limit load on one component were compared with spectrum loading on the other. A characteristic damage behaviour was observed. Local buckling due to high shear loading of the sandwich core of the wing shell causes the main damage. Even though an intentionally high load level was chosen no increase of micro-cracking could be detected. Additionally no delamination effects in laminates or bondings were observed except the skin-core delamination which causes the buckling effect in the wing shell due to fatigue loading. Finally the concept of using representative substructures and accompanying specimen tests is an effective approach for in-service loading investigations and could also be applied to research on wind turbine blades.
Fracture mechanics approaches are increasingly applied for the characterization of epoxy resin and adhesive mechanical properties. Therefore, the fracture toughness and crack resistance under static load ISO 13586 [1] are often regarded as state of the art to analyse material improvements. However, experimental investigations on fatigue behaviour, thus the crack propagation according to ISO 15850 [2], seem to be much more sensitive to characterize the materials for in service loading conditions. Firstly, an efficient testing concept was developed at BAM. In this framework, the geometry for a modified single edge notched tensile specimen (SET) was developed in order to assure appropriate resolution in measuring the crack length via a CCD-camera [3]. In the next step, the influence of the cure temperature on the fracture-mechanical properties was investigated.
Short glass fiber reinforced polyamides are increasingly used in automotive applications. Concepts and models are needed, which enable the prediction of the structural durability. The fiber orientation and the content of moisture have a major influence on the fracture mechanical properties and on the damage mechanisms. The complex crack growth behavior was investigated and described in an empirical model.
In this study, the thermomechanical damage behavior of a glass fiber reinforced polymer material is investigated. The coefficients of thermal expansion of the composite as well as the matrix are measured in a wide temperature range. Quasi-static experiments with neat resin, unidirectional and multidirectional laminates are performed as well as fatigue experiments in a temperature range from 213 K to 343 K. This study focusses on the matrix damage due to fiber-parallel loading. A correlation between matrix effort, the dilatational strain energy of the matrix and the damage state of the specimen is demonstrated. It is shown that a fatigue life assessment can be performed with the aid of a temperature-independent master fatigue curve.
Für die Schubkennwertermittlung an faserverstärkten Kunststoffen existieren verschiedene Verfahren, die nur eine Prüfung bis zu einer vorgegebenen maximalen Schubdehnung zulassen. Die Grasse Zur Ingenieurgesellschaft hat auf Basis eines an der BAM entwickelten Schubrahmens ein Schubprüfsystem etabliert, das diese Nachteile aufhebt. Damit ist es nun erstmals möglich, Schubkennwerte ohne Einschränkung einer maximalen Schubdehnung effizient und mit sehr guter Reproduzierbarkeit zu ermitteln.