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Eingeladener Vortrag
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Fire stability of glass-fibre sandwich panels: The influence of core materials and flame retardants
(2017)
Fire resistance has become a key property for structural lightweight sandwich components in aviation, shipping, railway vehicles, and construction. The development of future composite materials and components demands adequate test procedures for simultaneous application of compression and fully developed fire. Therefore an intermediate-scale approach (specimen size = 500 mm x 500 mm) is applied with compressive loads (up to 1 MN) and direct application of a burner to one side of the specimens, as established in aviation for severe burn-through tests. The influence of different core structures (polyvinylchloride foam, polyisocyanorate foam reinforced by stitched glass bridges, and balsa wood) was investigated for glass-fibre-reinforced sandwich specimens with and without flame retardants applied on the fabrics, in the matrix, and on surface for each specimen at the same time. Times to failure were increased up to a factor of 4. The intumescent coating prolongs the time to failure significantly.
What is more, using the intrinsic potential of the front skin together with the core to protect a load bearing back skin in sandwich panels, the design of the core – here using the wood core – is the most promising approach.
Non-isothermal heating rate kinetics was applied to two epoxy resin systems. In situ near-infrared (NIR) measurements were taken with a heatable NIR cell which allowed the cure to be monitored by characteristic absorption bands. An autocatalyzed reaction of the nth order was shown to describe the epoxy conversion curves. Differential Scanning Calorimetry (DSC) was used as a complementary method. The kinetic models developed by both NIR and DSC are in good accordance with experimental epoxy conversion in the in situ NIR setup for single and multiple cure temperature ramps.
A linear calibration curve of the characteristic absorption bands of epoxy normalized to aromatic vibrations was introduced. The curing degree of structural epoxies that were cured according to an industrial temperature cure profile was determined by NIR using the calibration curve. The epoxy conversions of the structural components showed good agreement with the experimental in situ NIR. Several degrees of cure for structural specimens were evaluated by NIR and residual reaction enthalpy by DSC. We present the non-destructive NIR spectroscopy as an alternative to determine fast and non-destructive epoxy conversion, particularly suitable for high degrees of cure on structural components.
Proben mit einer Mittelkerbe aus Polyamid 66 mit 35% Gewichtsan-teil an Kurzglasfaser (PA-GF35) wurden im Spritzgießverfahren hergestellt und in einem ungeschädigten und durch Schwingbeanspruch geschädigten Zustand mittels Röntgenverfahren charakterisiert. Sowohl die Faserorientierungsverteilung als auch die Riss-/Mikrorissbildung wurden mit der Röntgenrefraktionstopographie in einem SAXS-Aufbau und dem Diffraction-Enhanced-Imaging am Synchrotron (BESSY II) analysiert. Beide Verfahren spiegeln in guter Übereinstimmung die Charakteristiken dieser Werkstoffklasse in Bezug auf die Fertigungsqualität und die Schädigungsme-chanismen wider.
Proben mit einer Mittelkerbe aus Polyamid 66 mit 35% Gewichtsan-teil an Kurzglasfaser (PA-GF35) wurden im Spritzgießverfahren hergestellt und in einem ungeschädigten und durch Schwingbeanspruch geschädigten Zustand mittels Röntgenverfahren charakterisiert. Sowohl die Faserorientierungsverteilung als auch die Riss-/Mikrorissbildung wurden mit der Röntgenrefraktionstopographie in einem SAXS-Aufbau und dem Diffraction-Enhanced-Imaging am Synchrotron (BESSY II) analysiert. Beide Verfahren spiegeln in guter Übereinstimmung die Charakteristiken dieser Werkstoffklasse in Bezug auf die Fertigungsqualität und die Schädigungsme-chanismen wider.
Die Betriebsbeanspruchung für Rotorblätter ist aus Messungen bekannt. Schäden an Rotorblättern treten im Betrieb meistens an der Blattschale nach 4-5Jahren, weit vor der projektierten Lebensdauer von 20 Jahren auf und führen zum Anlagenstillstand, wenn sie nicht repariert werden. Mittels eines an der BAM entwickelten FKV-Sandwich-Schalenprüfkörpern kann effizient die Betriebs-festigkeit von Imperfektionen und Reparaturstellen studiert werden. Fertigungsbedingte Imperfektionen (Lagenstöße, Schaumstöße) verkürzen die Lebensdauer ggf. erheblich und führen zu Reparaturen. Experimentell konnte gezeigt werden, dass ein(e) aus-reparierte(r) Schaden/Imperfektion die Betriebsbeanspruchung deutlich besser erträgt, als die schadhafte Struktur.Die numerische Betriebsfestigkeitsvorhersage für FKV ist Gegenstand der Forschung. Gleiches gilt für die Abschätzung der Lebensdauerverkürzung infolge bekannter Fertigungsabweichungen.
The fire stability of carbon fiber reinforced polymer (CFRP) shell structures was investigated using an intermediate-scale test setup. The shell specimens are representative of typical load-bearing CFRPs in modern civil aviation. The CFRP shell specimens were exposed to a fully developed fire with direct flame impingement to one side at a heat flux of 182 kW/m2. Specimens were simultaneously loaded with constant compressive force equal to 40% of the ultimate failure load. CFRP shells and four different fire retarding configurations, using integrated protective layers, were investigated. Unprotected CFRP specimens failed after just 27 s. Specimens with integrated protective layers with low heat conductivity and high burn-through resistance showed the most promising results. An integrated titanium foil decelerated the decomposition of the epoxy matrix and increased the time to failure by 68% compared to the unprotected CFRP shell.
In this study, quasi-static material tests on unidirectional and multi-angle glass fiber reinforced epoxy laminates at ambient temperatures from -213 K to 353 K (-60 °C to +80 °C) are performed. In addition, neat resin is investigated under tension and compression loads at different temperatures. The coefficient of thermal expansion is determined for neat resin and unidirectional reinforced specimens. The dependence of the resin’s thermomechanical properties on the ambient temperature is shown. The point of damage onset at which first cracks appear within the matrix under quasi-static loading is investigated by means of optical grey scale analysis. The correlation between damage onset and effective matrix stress at different ambient temperatures is identified. An approach for the calculation of thermomechanical loads and the prediction of the damage onset by means of inverse calculations is presented. The impact of the strain blocking effect of the matrix is considered as well as residual thermal stresses due to curing and resin shrinkage.