28TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES ENERGY DISTRIBUTION IN GLARE AND 2024-T3 ALUMINIUM DURING LOW-VELOCITY IMPACT F.D. Morinière, R.C. Alderliesten, R. Benedictus Structural Integrity Group, Faculty of Aerospace Engineering, Delft University of Technology, Kluyverweg 1, 2629 HS Delft, The Netherlands [email protected];[email protected];[email protected] Keywords: impact, GLARE FML, aluminium, energy, delamination Abstract primary structures such as fuselage and wing skins, this material is also applied in cargo This paper presents a theoretical and floors, engine cowlings, patch repair, stringers, experimental comparative study on the low- cargo containers and seamless tubes [3-5]. velocity impact behaviour of GLARE Fibre- Impact is a type of damage that has to be Metal Laminate (FML). Using the Classical considered in the design process for safety Laminate Theory and the First-order Shear reasons [6]. However, no available method can Deformation Theory, an analytical model was predict the perforation behaviour of FMLs developed to predict the impact behaviour of under impact loading. Multiple studies have FMLs. Delamination onset and contact increase resulted in the theoretical prediction of the during perforation were taken into account. impact response of GLARE under various New generic expressions were derived for strain loading conditions [7-12] but the methodologies energy and contact force. Absorbed energy, focused mainly on the elastic response which impact force, maximum deflection and impact represents a minor portion of the perforation velocity were predicted within 5% of test response. Consequently, the impact strength results. GLARE 5-2/1-0.4 is 72% more resistant substantiation is typically evaluated via testing. than its monolithic 2024-T3 aluminium This method is time consuming and because of counterpart of the same thickness. scatter in the results, it requires a large amount Because GLARE is made of thin high strength of coupons. The development of impact layers that can undergo large deformation, this resistant concepts is therefore limited. A new hybrid material is an ideal candidate for impact technique is necessary to assess the impact prone structures. This general understanding performance of FMLs. will support the development of high-energy In this paper, a theoretical model will be absorbing FML concepts. presented to predict the perforation behaviour of GLARE under low-velocity impact. The Classical Laminate Theory (CLT) will be used 1 Introduction with the First-order Shear Deformation Theory Fibre-Metal Laminates (FMLs) are lightweight (FSDT) to perform a sequential failure analysis. hybrid composite materials that consist of This new method will introduce new equations alternating aluminium layers bonded to fibre- for strain energy and impact force. Besides, it reinforced epoxy layers. GLARE (GLAss- will be able to evaluate the contribution of the Reinforced) FML demonstrates outstanding material constituents of GLARE 5-2/1-0.4. The damage tolerance capabilities [1] in present approach which provides a general combination with excellent impact resistance understanding of the impact behaviour of FMLs when compared to composites and metals [2]. is not found in the literature. With such a high structural efficiency, designers gained interest in the application of GLARE in aircraft structures. Originally developed for 1 F.D. Morinière, R.C. Alderliesten, R. Benedictus 2 Experimental Arrangement total plate mass ratio is larger than 2 (quasi- static boundary-controlled impact), the entire Panels of GLARE 5-2/1-0.4 were prepared by plate is deformed during the impact, and the hand lay-up technique. This laminate consists of contact force and plate deformation are slightly a [0°/90°/90°/0°] composite core of S2- out of phase, as shown in Fig. 1. glass/FM94-epoxy prepregs embedded in two layers of 2024-T3 aluminium of 0.4 mm. Plates of the same aluminium alloy were used as a reference. Both materials had a thickness of 1.3 mm. Mechanical properties were taken from [13-15]. For modelling purposes, aluminium is isotropic. The Young’s modulus is then the average between the available data. According to ASTM E8M [16], 12 dogbone samples of 0.4mm-thick 2024-T3 aluminium – 6 in the Fig. 1. a) Quasi-static and b) dynamic impact responses rolling direction and 6 in the transverse one – [19] were tested to estimate the modulus of In this study, the impactor-plate mass ratio was plasticity. Thereby, a bilinear stress-strain curve larger than 31. A quasi-static analysis can be was assumed for aluminium with a mean realised to compute stresses until detection of Young’s modulus of 70.15 GPa and a mean failure though the strain rate affects mechanical modulus of plasticity of 1.60 GPa. properties of 2024-T3 aluminium and S2-glass fibres [2, 20, 21]. A series of impact tests were executed at room temperature at the centre of rectangular plates. Considering that the full plate participates in the The rolling direction and the 0° fibre orientation response, the strain rate is approximated by corresponded to the major axis of the rectangle. dividing the impact velocity by the average-half The 150 mm x 100 mm flat panels were fully of the plate dimensions. clamped in a fixture with a 125 mm x 75 mm The empirical Johnson-Cook model aperture. A falling weight of 1.075 kg hit the accounts for strain rate effect on the yield specimens via a conical-shaped steel impactor strength of aluminium [22]. Thermal effect is with a hemispherical nose whose radius was ignored as tests were operated at room 6.35 mm. The exact dimensions are stated in temperature. This model appraises also failure ASTM D5628 [17]. Four panels were used for strain. The value applied in this research is the each material to determine the perforation average between the strain obtained with the threshold. Perforation occurred when cracking original method and the strain found with an in aluminium was observed on both sides of the updated version [23]. Furthermore, the effect of specimens. plate thickness is not included in the Johnson- Cook approach. As ductility can decrease up to 3 Model Development 6% for a thickness of 3 cm [9, 24], a 12% failure strain is used for a 1.3mm-thick plate. 3.1 Approach Regarding glass composites, a strain rate of 100 s-1 results in a 10% increase in strength The impact response type is governed by the from static values [9, 25]. impactor–plate mass ratio and not by impact Hereby, the established method will define velocity [18]. If the impactor mass divided by for an initial strain rate the evolution of the the effective mass of panel is lower than 1/5 energy partition between the material (dynamic wave-controlled impact), the plate constituents until the perforation limit. deformation is localised to the vicinity of the impact point and, the contact force and plate deformation are never in phase. If the impactor- 2 ENERGY DISTRIBUTION IN GLARE AND 2024-T3 ALUMINIUM DURING LOW-VELOCITY IMPACT Deformation, delamination, fracture and calculated from the neutral axis of the plate. The petaling are selected among several failure corresponding off-axis stresses in the CLT [26] modes [2] to form the total absorbed energy: are computed in each layer at the height where they are maximum. As soon as an aluminium EEEEE (1) abs tot def del frac petal layer yields, the Young’s modulus is updated At perforation threshold this total energy equals with the strain-hardened modulus of plasticity. the kinetic energy of impact. The impact When a composite ply fails, the stresses in the velocity limit (V ) is given by: principal axes of the failed layer are distributed 0 into the intact ones according to their respective stiffnesses. Then, a failed layer has zero 2Eabs tot V0 (2) stiffness for the same thickness. M with (M) the mass of projectile. In order to For small deformation, stresses are limited by calculate the total absorbed energy during the Von-Mises criterion for aluminium and by impact, the substance of each component in the Tsai-Hill criterion for unidirectional Eq. (1) has to be quantified. composite to obtain the maximum allowed deflection at each failure step until the last fibre 3.2 Energy Absorbed in Global Flexure layer breaks. Then, the damage process ends with the Johnson-Cook failure strain as An initial in-plane radius of 1.588 mm was aluminium layers undergo large deformation. determined experimentally to account for the Unlike for the thick aluminium, elastic increase of the radial contact. The springback is considered in GLARE. Permanent corresponding initial dent depth defines an deflection equals the difference between the initial arc length which represents the true maximum deflection and the displacement when contact radius (r). When a layer fails, the first failure occurs. penetration depth increases with the thickness of the failed layer, which leads to a larger arc Taking into account the assumptions of the CLT length. This simplification in the penetration of and integrating strain energy along the laminate a hemispherical nose into a laminate is valid if thickness, membrane energy (Um), flexural- the laminate thickness does not exceed a height extensional coupling energy (Uc) and bending equivalent to the nose radius. energy (Ub) are gathered: w4 32 32 Since large deflection is expected, the in-plane UAAA0 5 9 24 7 7 m 88 11 12 66 displacements are neglected. The deflection ab 45 49 profile (w) of the neutral line of the laminate is a 329 5 8 6 8 8 6 4 A22 A 16 A 26 w 0 Km revised formulation of a FE analysis [10]: 45 3 w3 32 64 UBBB 0 3 7 28 5 5 0 xr c ab66 1121 12 66 25 0 yr 32 w x, y B7 3 16 B 4 6 B 6 4 w 3 K 22 22 16 26 0 c (4) 22xy r x a 2 (3) 21 w 11 0 w2 32 64 ab r y b 2 UDDD0 5 8 3 3 b 44 11 12 66 ab 59 22 with w0 1 2 r a 1 2 r b c 32 5 2 4 4 2 2 D22 32 D 16 D 26 w 0 Kb 5 This shape meets the boundary conditions of a with a 22 r and b r fully clamped plate with maximum displacement (∆) at the centre.