Mechanical Behavior in Compression-after-Impact(CAI) Tests of Conventional CF/Epoxy Laminates.

隆司, 石川; 正道, 松嶋; 洋一, 林

doi:10.6089/jscm.26.141

Cited by 5 publications

(1 citation statement)

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“…In that case, a significant reduction in strength due to damage is one of the concerns. [8][9][10] Therefore, researches have been actively carried out on Structural Health Monitoring (SHM), which rapidly evaluates the damage conditions during flight. In addition, research on the strain measurement method related to SHM has been conducted.…”

Section: Introductionmentioning

confidence: 99%

Fundamental Study on Adaptive Wing Structure for Control of Wing Load Distribution

Fujii

Yokozeki

Arizono

et al. 2017

AEROSPACE TECHNOLOGY JAPAN

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When damage occurrs on a wing during flight, the stress at the damage site becomes large and the risk of catastrophic failure increases. In order to deal with this problem, Objective Stress Reduction (OSR) is considered by controlling the wing load distribution using an adaptive wing. The purpose of OSR is to reduce all or part of the stress acting on the wing. OSR also helps to adjust the extent of reduction depending on the condition in order to avoid increasing drag as much as possible. Static aeroelastic analysis is conducted for an adaptive wing model that has plain flaps at its leading-and trailing-edges using MSC/NASTRAN. From the results of a parametric study, it is revealed that the bending moment and drag are in a trade-off, and that OSR can adjust the extent of stress reduction depending on the various flight conditions by controlling the set of flap deflection angles.

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Section: Introductionmentioning

confidence: 99%

Fundamental Study on Adaptive Wing Structure for Control of Wing Load Distribution

Fujii

Yokozeki

Arizono

et al. 2017

AEROSPACE TECHNOLOGY JAPAN

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Damage Behaviors and Compressive Strength of Toughened CFRP Laminates with Thin Plies Subjected to Transverse Impact Loadings

Yokozeki¹,

Aoki²,

Ogasawara³

2007

JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCE

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It has been recognized that damage resistance and strength properties of CFRP laminates can be improved by using thin-ply prepregs. This study investigates the damage behaviors and compressive strength of CFRP laminates using thin-ply and standard prepregs subjected to out-of-plane impact loadings. CFRP laminates used for the evaluation are prepared using the standard prepregs, thin-ply prepregs, and combinations of the both. Weight-drop impact test and post-impact compression test of quasi-isotropic laminates are performed. It is shown that the damage behaviors are different between the thin-ply and the standard laminates, and the compression-after-impact strength is improved by using thin-ply prepregs. Effects of the use of thin-ply prepregs and the layout of thin-ply layers on the damage behaviors and compression-after-impact properties are discussed based on the experimental results.

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Impact Damage Monitoring of CFRP Laminated Plate Based on Impact Force Identification

Tajima¹,

Miura²,

Sugimoto³

et al. 2009

JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCE

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:The present paper discusses a structural health monitoring method of CFRP structures based on a impact force identification. In the first part, an experimental identification method of impact force is developed where the relation between force histories and strain responses is determined experimentally. By employing this relation, the impact force is identified for CFRP laminated plates involving impact damages under a drop-weight impact test. It is shown that the identified force history agrees well with the experimental one even when the impact damage is induced. Next, the impact damage monitoring method is proposed. When the information on the maximum impact force is obtained, the occurrence of the impact damage can be predicted easily from the shape of force history, and the damage size can also be estimated using the experimental relation between the damage size and the maximum impact force. Thus, structural health can be evaluated automatically, by monitoring the impact force from the sensor response in real time, and great improvement of the structure safety becomes possible.

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Mechanical Behavior in Compression-after-Impact(CAI) Tests of Conventional CF/Epoxy Laminates.

Cited by 5 publications

References 0 publications

Fundamental Study on Adaptive Wing Structure for Control of Wing Load Distribution

Fundamental Study on Adaptive Wing Structure for Control of Wing Load Distribution

Damage Behaviors and Compressive Strength of Toughened CFRP Laminates with Thin Plies Subjected to Transverse Impact Loadings

Impact Damage Monitoring of CFRP Laminated Plate Based on Impact Force Identification

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