Analysis of composite T-joint designs for enhanced resistance to hydrodynamic ram

May, Michaël; Ganzenmüller, Georg; Wolfrum, Johannes; Heimbs, Sebastian

doi:10.1016/j.compstruct.2015.02.012

Cited by 25 publications

(3 citation statements)

References 23 publications

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“…Keeping an eye on potential future certification of a morphing leading edge concept, one aspect to consider is the proof of bird strike resistance [36]. In particular, it must be shown that the bird does not damage the front spar of the wing and the fuel tank, as this might result in catastrophic failure of the fuel system and subsequent loss of the aircraft [37][38][39]. For this work, the proof of the bird strike resistance of the morphing leading edge was demonstrated by means of simulation.…”

Section: Bird Strikementioning

confidence: 99%

Analysis and Design of a Leading Edge with Morphing Capabilities for the Wing of a Regional Aircraft—Gapless Chord- and Camber-Increase for High-Lift Performance

et al. 2021

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In order to contribute to achieving noise and emission reduction goals, Fraunhofer and Airbus deal with the development of a morphing leading edge (MLE) as a high lift device for aircraft. Within the European research program “Clean Sky 2”, a morphing leading edge with gapless chord- and camber-increase for high-lift performance was developed. The MLE is able to morph into two different aerofoils—one for cruise and one for take-off/landing, the latter increasing lift and stall angle over the former. The shape flexibility is realised by a carbon fibre reinforced plastic (CFRP) skin optimised for bending and a sliding contact at the bottom. The material is selected in terms of type, thickness, and lay-up including ply-wise fibre orientation based on numerical simulation and material tests. The MLE is driven by an internal electromechanical actuation system. Load introduction into the skin is realised by span-wise stringers, which require specific stiffness and thermal expansion properties for this task. To avoid the penetration of a bird into the front spar of the wing in case of bird strike, a bird strike protection structure is proposed and analysed. In this paper, the designed MLE including aerodynamic properties, composite skin structure, actuation system, and bird strike behaviour is described and analysed.

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Section: Bird Strikementioning

confidence: 99%

Analysis and Design of a Leading Edge with Morphing Capabilities for the Wing of a Regional Aircraft—Gapless Chord- and Camber-Increase for High-Lift Performance

et al. 2021

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“…The initial failure load of T-joints with 3D 4D braided composite fillers was 35.6% higher than the T-joints filled unidirectional carbon fiber prepreg fillers. May et al 17 conducted T-pull tests on the composite T-joint with braided carbon fiber noodle, they found the damage is initiated in the curvature of the fillet and slightly above the fillet and then propagates along the web as well as in the flange-skin interface. Heimbs et al 18 conducted quasi-static and high-rate dynamic tensile tests on the composite T-joints and found the usage of PEI filler leads to a significant improvement with 23% higher energy absorption of 98 J compared to the carbon braid filler.…”

Section: Introductionmentioning

confidence: 99%

Effects of the fillers on the interface strength of the hat-stiffened composite panel

Liu,

Guan

2023

Polymers and Polymer Composites

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Hat-stiffened composite skins have been widely used in primary structures of aircraft components. The bonding strength at the stiffener-skin interface is critical to ensure the advanced load-bearing capacity of the stiffened skin, whereas, the deltoid regions are usually the weakest locations because of the geometrical singularity. Inserting fillers into the deltoid regions could alter the bonding strength. In this study, a series of four-point bending tests are conducted on the co-cured hat-stiffened composite skin specimens with and without fillers and with different pre-fabricated debonding defects, furthermore, finite element simulations are implemented to predict the failure process. The stiffness, initial failure load, failure mode and failure process are analyzed to obtain the influences of the fillers on the damage tolerance of the hat-stiffened composite panels, and the influential mechanisms were revealed by the combined analyses of the test and simulation results. It is found that the usage of fillers can increase the initial stiffness of the panel without prefabricated defects by about 10%, but provide limited influence on the initial failure load. The pre-fabricated debonding defect along longitudinal direction has little influence on the stiffness and failure load, but the influence of the defect along transverse direction are higher. The initial failure of all hat-stiffened composite panels with/without filler and with/without prefabricated defects under four-point bending onsets around the deltoid region. The usage of the fillers changed the load transfer and the stress status in the deltoid region of the hat-stiffened composite panels and as a consequence, the initial failure modes were changed and the failure load were increased by the fillers. This work provides a technical support for the damage tolerance design and strengthening method of hat-stiffened composite structures.

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“…The increased integration level of composite structures is beneficial to its affordability and development efficiency; adhesive bonding has been widely used for manufacturing integrated composite structures [3]. Some typical composite joints have been comprehensively investigated, such as single lap joints [4], double lap joints [5] and T-joints [6]. The strength and damage tolerance of those adhesive bonded structures have been extensively documented; the experimental characterization methods [7,8,9] have been well established, and corresponding numerical models have been successfully developed [10,11,12].…”

Section: Introductionmentioning

confidence: 99%

On the rate dependent behaviour of epoxy adhesive joints: Experimental characterisation and modelling of mode I failure

Lißner

Alabort

Cui

et al. 2018

Composite Structures

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The increasing use of adhesive joints in dynamic applications require reliable measurements of the rate-dependent stress-displacement behaviour. The direct measurement of the stress-displacement curve is necessary when using cohesive models in discretised solutions of boundary value problems in solid mechanics. This paper aims to investigate the rate-dependent tensile failure of adhesive joints by using a new experimental methodology-it relies upon the combination of the stress wave propagation theory and digital image correlation methods on high speed footage to quantify the tensile stress and the dissipated energy respectively. For this purpose, the Split Hopkinson Bar methodology was employed-the experimental configuration was optimised using numerical modelling. To prove the sensitivity of our framework, two different adhesives are characterised at different loading rates: the adhesive failure strength was found to increase considerably with the strain rate, while the plastic deformation of these adhesives was reduced. The film adhesive showed superior performance over the particle toughened one. In the final part, a rate-dependent cohesive zone model is proposed, one which captures the measured behaviour and which has the potential to be used in industrial applications.

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Analysis of composite T-joint designs for enhanced resistance to hydrodynamic ram

Cited by 25 publications

References 23 publications

Analysis and Design of a Leading Edge with Morphing Capabilities for the Wing of a Regional Aircraft—Gapless Chord- and Camber-Increase for High-Lift Performance

Analysis and Design of a Leading Edge with Morphing Capabilities for the Wing of a Regional Aircraft—Gapless Chord- and Camber-Increase for High-Lift Performance

Effects of the fillers on the interface strength of the hat-stiffened composite panel

On the rate dependent behaviour of epoxy adhesive joints: Experimental characterisation and modelling of mode I failure

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