Ballistic Impact of Braided Composites with a Soft Projectile

Roberts, Gary D.; Pereira, J. Michael; Revilock, Duane M.; Binienda, Wieslaw K.; Xie, Minzhu; Braley, Mike

doi:10.1061/(asce)0893-1321(2005)18:1(3)

Cited by 43 publications

(17 citation statements)

References 1 publication

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“…Results show that both the center of the back side and the boundary of the front side experience relatively high fiber-tension damage, while the middle ply experiences relatively small damage. These distribution laws agree well with the experimental observations from the previous literature dealing with the other composite material systems under high-velocity impact [16,22,40].…”

Section: +2063e+02supporting

confidence: 90%

“…front side experience relatively high fiber-tension damage, while the middle ply experiences relatively small damage. These distribution laws agree well with the experimental observations from the previous literature dealing with the other composite material systems under high-velocity impact [16,22,40]. In terms of failure analysis of composite materials, it requires the mesh size to be small enough in order to well capture the fracture properties, but in the explicit dynamic analysis of structures under impact, the mesh size cannot be too small, so as to avoid the numerical instability.…”

Section: +2063e+02supporting

confidence: 85%

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Bird-Strike Resistance of Composite Laminates with Different Materials

2019

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To obtain some basic laws for bird-strike resistance of composite materials in aeronautical application, the high-velocity impact behaviors of composite laminates with different materials were studied by numerical methods. The smoothed particle hydrodynamics (SPH) and finite element method (FEM) coupling models were validated from various perspectives, and the numerical results were comparatively investigated. Results show that the different composite materials have relatively little effect on projectile deformations during the bird impact. However, the impact-damage distributions can be significantly different for different composite materials. The strength parameters and fracture energy parameters play different roles in different damage modes. Lastly, modal frequency was tentatively used to explain the damage behavior of the composite laminates, for it can manifest the mass and stiffness characteristics of a dynamic structure. The dynamic properties and strength properties jointly determine the impact-damage resistance of composite laminates under bird strike. Future optimization study can be considered from these two aspects.

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Section: +2063e+02supporting

confidence: 90%

Section: +2063e+02supporting

confidence: 85%

Bird-Strike Resistance of Composite Laminates with Different Materials

2019

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“…The response of plates impacted by soft body impactors is specific as the impact load is spread over a wider area. Gas-gun experimental data of bird substitute gelatine impacting on the woven CFRP plates, in the velocity range from 140 to 220 m/s, are provided in [19]. Soft body gas-gun impact testing on unidirectional CFRP plates is available in [20].…”

Section: Validation Of the Applied Failure And Damage Model For Compomentioning

confidence: 99%

Bird strike damage analysis in aircraft structures using Abaqus/Explicit and coupled Eulerian Lagrangian approach

Smojver

Ivančević

2011

Composites Science and Technology

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a b s t r a c tThe subject of this paper is numerical prediction of bird strike induced damage in real aeronautical structures using highly detailed finite element models and modern numerical approaches. Due to the complexity of today's aeronautical structures, numerical damage prediction methods have to be able to take into account various failure and degradation models of different materials. A continuum damage mechanics approach has been employed to simulate failure initiation and damage evolution in unidirectional composite laminates. Hashin's failure initiation criteria have been employed in order to be able to distinct between four ply failure modes. The problem of soft body impacts has been tackled by applying the Coupled Eulerian Lagrangian technique, thereby avoiding numerical difficulties associated with extensive mesh distortion. This improvement in impactor deformation modelling resulted in a more realistic behaviour of bird material during impact. Numerical geometrical and material nonlinear transient dynamic analyses have been performed using Abaqus/Explicit. The main focus of the work presented in this paper is the application of the damage prediction procedure in damage assessment of bird impact on a typical large airliner inboard flap structure. Due to the high cost of gas-gun testing of aircraft components, experimental testing on the real flap structure could not have been performed. In order to evaluate the accuracy of the presented method, the bird and composite damage model have been validated against experimental data available in the literature.

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“…In this method, the triaxial braid architecture is simulated using four parallel shell elements, each of which is modeled as a laminated composite. Roberts et al also performed impact tests using cylindrical gelatin projectile to identify the failure modes which occurred in composite plates and half‐rings made with triaxial braid architecture. Xuan et al conducted ballistic tests on the triaxial braided composites using cylinder and blade‐like projectile and observed its damage modes.…”

Section: Introductionmentioning

confidence: 99%

Containment capability of 2D triaxial braided tape wound composite casing for aero‐engine

Liu

et al. 2015

Polymer Composites

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Two-dimensional (2D) triaxial braided composites have been successfully used in aero-engine fan containment system for weight reduction. In the current study, blade containment tests were conducted on highspeed rotor spin tester to investigate the containment process and failure mechanisms of the composite casing. The composite casing was fabricated by winding 2D carbon fiber triaxial braided tape on a capstan into predetermined thickness and then infused with epoxy resin. Test results indicate that the damages to the containment casing increase significantly with the increase in blade released speed. In contained case, two damaged areas can be observed on the inner wall of the casing due to continued impacts of the released blade. However in uncontained case, a perforated hole was found in the casing. Finite element method was used to study this high-speed impact process using LS-DYNA. The influence of blade release speed and case thickness was also analyzed and found that the failure modes turns from tension to shear as the blade speed increases and casing is able to absorb more energy with increase in casing areal density. An empirical equation was derived for the triaxial braided composite casing, which can help in the design of the composite fan casing for aero-engine. POLYM.

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Ballistic Impact of Braided Composites with a Soft Projectile

Cited by 43 publications

References 1 publication

Bird-Strike Resistance of Composite Laminates with Different Materials

Bird-Strike Resistance of Composite Laminates with Different Materials

Bird strike damage analysis in aircraft structures using Abaqus/Explicit and coupled Eulerian Lagrangian approach

Containment capability of 2D triaxial braided tape wound composite casing for aero‐engine

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