Evaluation of bird strike-induced damages of helicopter composite fuel tank assembly based on fluid-structure interaction analysis

Kim, Dong-Hyeop; Kim, Sang Woo

doi:10.1016/j.compstruct.2018.11.086

Cited by 28 publications

(6 citation statements)

References 21 publications

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“…As is known to all, the bird strike is an airborne collision between a flying bird and a manned aircraft, which is a major threat to the safety of civil aviation as this incident can lead to serious structural damage [17][18][19][20][21][22]. According to the Federal Aviation Administration (FAA), it was reported that more than 258 people had been killed and at least 245 aircraft have been destroyed under the bird strike accidents during the year of 1988-2014 [23].…”

Section: Relevant Statistics Of Bird Strike Damagementioning

confidence: 99%

UAV airborne collision to manned aircraft engine: Damage of fan blades and resultant thrust loss

Liu

Man

Low

2021

Aerospace Science and Technology

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Section: Relevant Statistics Of Bird Strike Damagementioning

confidence: 99%

UAV airborne collision to manned aircraft engine: Damage of fan blades and resultant thrust loss

Liu

Man

Low

2021

Aerospace Science and Technology

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“…Each criterion governs a distinct failure mode: matrix tensile, matrix compressive, fibre tensile and fibre compressive. They interact in terms of stresses and strength properties, and are well established in measuring fibre composite first ply failure and/or damage onset (Zhu et al 2017;Koh and Madsen 2018;de Miguel et al 2018;Li et al 2019;Kim and Kim 2019;Joosten 2019).…”

Section: Hashin's Failure Criteriamentioning

confidence: 99%

Optimal orientation of fibre composites for strength based on Hashin’s criteria optimality conditions

Ferreira

Ashcroft

2020

Struct Multidisc Optim

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The Hashin's strength criteria are usually employed in first ply failure and damage-onset analysis of fibre-reinforced composites. This work presents optimality conditions of local material orientations for these criteria, in terms of principal stresses and material strength parameters. Each criterion (matrix tensile/compressive, fibre tensile/compressive modes) has its conditions separately derived, analytically, based on a fixed stress field assumption. The conditions found show that orientations which coincide and do not coincide with principal stress directions may minimise local failure indices. These solutions are employed in a proposed algorithm, named HA-OCM (Hashin Optimality Criteria Method), which selectively satisfies the matrix failure modes (either tensile or compressive), iteratively and finite element-wise in composites. It is demonstrated that the HA-OCM is able to design single-layer plane structures with improved failure loads in comparison with designs following only maximum (in absolute) principal stress orientations. Results show that the material orientations have a trend to end up either aligned or at 90 • with maximum in absolute principal stress directions. Global optima for compliance are, however, not guaranteed. To give an idea of gains in terms of failure loads, some HA-OCM designs show improvements of 71% and 140%, for example, in comparison with principal stress design.

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“…With the continuous development of the aerospace field, scholars have systematically studied bird strike problems [16][17][18][19][20], but research on the impact of raindrops and sand on aircraft is insufficient. When an aircraft is in a rainy environment or passes through clouds, its surface is affected by the rain.…”

Section: Introductionmentioning

confidence: 99%

Investigation of the Mechanical Behaviors and Damage Mechanism of C/C Composites Impacted by High-Velocity Jets

Yue,

Wang,

Yan

et al. 2024

Materials

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Carbon/Carbon (C/C) composites exhibit excellent mechanical properties at high temperatures, making them widely used in aerospace, such as the leading edges of spaceplane wings and the nose cones of hypersonic aircraft. However, damage caused by rain erosion to C/C composites affects their mechanical properties and poses significant challenges during operational service periods. A jet impingement test platform was employed to conduct single and multiple water-jet erosion tests on three-dimensional orthogonal C/C composite materials and to investigate the residual mechanical properties of the specimens after jet impact. The damage was characterized using optical microscopy, scanning electron microscopy, and X-ray computed tomography. The results showed that the damage types of the C/C composite materials under water-jet impingement included fiber bundle fracturing, delamination, and debonding. The extent of erosion damage was positively correlated with the jet velocity and diameter. The changes in the multi-jet damage indicated a cumulative expansion process, and z-directional fiber bundles exhibited superior resistance to jet impact damage propagation. The results of the three-point bending tests showed that the greater the initial impact damage, the lower the residual mechanical properties of the materials, and the residual strength of the specimen suddenly decreased when damage occurred at the back of the specimen.

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Evaluation of bird strike-induced damages of helicopter composite fuel tank assembly based on fluid-structure interaction analysis

Cited by 28 publications

References 21 publications

UAV airborne collision to manned aircraft engine: Damage of fan blades and resultant thrust loss

UAV airborne collision to manned aircraft engine: Damage of fan blades and resultant thrust loss

Optimal orientation of fibre composites for strength based on Hashin’s criteria optimality conditions

Investigation of the Mechanical Behaviors and Damage Mechanism of C/C Composites Impacted by High-Velocity Jets

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