A novel design for reinforcing the aircraft tail leading edge structure against bird strike

Liu, Jun; Li, Yulong; Yu, Xiancheng; Tang, Zhongbin; Gao, Xiaosheng; Lv, Jun; Zhang, Zhengli

doi:10.1016/j.ijimpeng.2016.12.017

Cited by 40 publications

(18 citation statements)

References 17 publications

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“…In the SPH approach, a continuous field is represented by a set of discrete but interacting particles. Therefore, SPH has recently experienced high popularity [2,7,9,13,21,23,38,39] in bird-strike and high-velocity dynamics studies. In the present study, an SPH method has been employed, which is a meshless particle-based method.…”

Section: Methodsmentioning

confidence: 99%

Impact-Damage Equivalency for Twisted Composite Blades with Symmetrical Configurations

2019

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In spite of potential advantages for aircraft structures, composite laminates can be subjected to bird-strike hazard in civil aviation. For purpose of future surrogate experiments, in this study, impact-damage equivalency for twisted composite blades is numerically investigated by Smoothed Particle Hydrodynamics (SPH) and finite element method (FEM). Cantilever slender flat plates are usually used for basic impact tests, the impact-damage equivalency is being considered by comparing damage modes and energies of three impact configurations: (1) twisted blade; (2) flat blade (axisymmetric); and (3) inclined flat blade (centrosymmetric). The damage maps and energy variations were comparatively investigated. Results indicate that both symmetrical flat and inclined flat blades can be, to a certain extent, regarded as alternatives for real twisted blades under bird impact; however, both types of blade have their own merits and drawbacks, and hence should be used carefully. These results aim to serve as tentative design guideline for future prototype or model experimental study of laminated blades in real aeronautical structures.

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Section: Methodsmentioning

confidence: 99%

Impact-Damage Equivalency for Twisted Composite Blades with Symmetrical Configurations

2019

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“…The mass of the bird is 800 g, and the impact velocity is 180 m/s. The bird model geometry is approximated as a circular cylinder with hemispherical end caps (Mccarthy et al, 2004b, Hedayati et al, 2014, Liu et al, 2017 as shown in Fig. 11, which was used widely (Mccarthy et al, 2004b, Vignjevic et al, 2013, Liu et al, 2017.…”

Section: Birdstrike Modelmentioning

confidence: 99%

Analytical determination of the critical impact location for wing leading edge under birdstrike

Xue

Yao

et al. 2019

Lat. Am. j. solids struct.

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The wing leading edge is one of the aircraft structures which are vulnerable to birdstrike. Therefore, Federal Aviation Regulation has clear requirements of anti-birdstrike performance for wing leading edge. However, the impact location is not specified in aviation regulation. The forefront of the wing leading edge is selected as a critical location for the birdstrike in most researches. But the rationality of the selection is not given. This paper proposes an analytical method for determining the critical location that causes the most severe damage under impact due to birdstrike. The analysis is based on the concept of effective impact, i.e. the component of the bird velocity perpendicular to the surface of wing leading edge. A birdstrike model is established using Pam-crash and used to validate the analytical prediction. The numerical model proves its effectiveness compared to the birdstrike test. The residual compressive strength of the spar when the birdstrike is at the critical impact location determined by the proposed method is 44.5% of that at the traditional impact location. Moreover, the critical penetrating velocity of the traditional impact location is not the lowest. In other words, the traditional impact location is not the weakest. Airworthiness verification experiment of birdstrike on wing structure should pay attention to this aspect.

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“…Among these methods, SPH can better describe bird fragmentation into discrete particles with high efficiency. Therefore, SPH has recently experienced high popularity [2,5,10,15,16,32,33,40,41] in bird strike, high-velocity impact, and other large deformation studies. In the present study, a SPH method was employed, represented by a set of discrete but interacting particles, which belong to a meshless particle-based method.…”

Section: Sph-fem Computational Modelmentioning

confidence: 99%

SPH-FEM Design of Laminated Plies under Bird-Strike Impact

2019

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Composite laminates can potentially reduce the weight of aircrafts; however, they are subjected to bird strike hazards in civil aviation. To handle their nonlinear dynamic behaviour, in this study, the impact damage of composite laminates were numerically evaluated and designed by means of smoothed particle hydrodynamics (SPH) and the finite element method (FEM) to simulate the interaction between bird projectiles and the laminates. Attention was mainly focused on the different damage modes in various laminates’ plies induced by bird impact on a square laminated plate. A continuum damage mechanics approach was exploited to simulate damage initiation and evolution in composite laminates. Damage maps were computed with respect to different ply angles, i.e., 0°, 45° and −45°. The damage distributions were comparatively investigated, and then the ply design was considered for crashworthiness improvement. The results aim to serve as a design guideline for future prototype-scale bird strike studies of complex laminated structures.

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A novel design for reinforcing the aircraft tail leading edge structure against bird strike

Cited by 40 publications

References 17 publications

Impact-Damage Equivalency for Twisted Composite Blades with Symmetrical Configurations

Impact-Damage Equivalency for Twisted Composite Blades with Symmetrical Configurations

Analytical determination of the critical impact location for wing leading edge under birdstrike

SPH-FEM Design of Laminated Plies under Bird-Strike Impact

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