High velocity impact on composite link of aircraft wing flap mechanism

Heimbs, Sebastian; Lang, Holger; Havar, Tamas

doi:10.2478/s13531-012-0002-8

Cited by 3 publications

(6 citation statements)

References 9 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Some studies focus on impacts on particular components instead of generic plates or shells: composite aircraft wing flap support impacted by a wheel rim fragment [201], impacts on scarf joints [260], on helmets [261,262] or on composite pipes [263]. Most numerical investigations are conducted using the finite element method and often some well-known commercial codes.…”

Section: Low Velocity Impactsmentioning

confidence: 99%

“…Most numerical investigations are conducted using the finite element method and often some well-known commercial codes. For example, Abaqus is used by many authors and the bilinear cohesive element COH3D8R [201,[253][254][255][256]264]. Other numerical approaches are also used.…”

Section: Low Velocity Impactsmentioning

confidence: 99%

“…Fiber failures can also be modeled by cohesive elements. In a series of articles, Bouvet et al [199,[232][233][234] use cohesive elements to High velocity impact [201,275,372,373] Soft impact [202,[254][255][256] Crushing tube [203,326] Crushing plate [349,350] Energy absorbing structures [338,339,374] predict both intraply and interlaminar damage during low velocity impacts. This approach was also used to study the compression after impact behavior of laminates [235].…”

Section: Low Velocity Impactsmentioning

confidence: 99%

“…Many authors [201][202][203] showed that the element size was very important for the accuracy of the calculation and its convergence. At the crack tip, the variation of stress can be very high in a small area.…”

Section: Loading Rate Moisture and Other Complicating Effectsmentioning

confidence: 99%

See 3 more Smart Citations

Cohesive zone models and impact damage predictions for composite structures

2015

View full text Add to dashboard Cite

This article surveys existing cohesive zone models (CZM) and their use in numerical simulations for analysis impacts on composite structures and predicting the damage induced. These models are used for matrix cracks and delamination. The first part of article gives the required background on failure criteria for predicting the onset of delaminations, on fracture mechanics and the various types of CZM. The second part discusses applications of CZM to several types of impact problems with composite structures. Applications for these models to other problems are briefly mentioned at the end. CZM are now part of state of the art numerical simulations with progressive damage analysis.

show abstract

Section: Low Velocity Impactsmentioning

confidence: 99%

Section: Low Velocity Impactsmentioning

confidence: 99%

Section: Low Velocity Impactsmentioning

confidence: 99%

Section: Loading Rate Moisture and Other Complicating Effectsmentioning

confidence: 99%

See 2 more Smart Citations

Cohesive zone models and impact damage predictions for composite structures

2015

View full text Add to dashboard Cite

show abstract

“…4 During operation, the composite aircraft structures could suffer damage, e.g. arising from high velocity impact 5 and replacement of the damaged parts is costly. However, where the damage features benign cracks (e.g.…”

Section: Introductionmentioning

confidence: 99%

A simple portable low-pressure healant-injection device for repairing damaged composite laminates

Lai

Cheah

Ruiz

et al. 2017

International Journal of Mechanical Engineering Education

View full text Add to dashboard Cite

This article presents the outcomes of an undergraduate design-for-industry teamdriven project to develop a portable low-pressure healant-injection device. The developed healant-injection device is intended to use for teaching purpose. The students practice some of the techniques of repairing damaged composite laminates, as part of an engineering composite-related course, which mainly covers the fundamentals and applications of composite laminates. The healant-injection device works by introducing resin into damaged site that can assist the healant to flow through the network of micro-cracks in a low-pressure environment. The device comprises three components: a chamber featuring a (rectangular box) cover made from acrylic that is intended to cover a damaged surface in a low-pressure environment, an injection unit and a vacuum pump unit. Only the vacuum chamber was designed from scratch by the team; the other components were sourced commercially. The repair of composite laminates can be performed using a low viscosity resin, which is made to flow through a hole on the roof of the chamber, assisted by the injection unit (fluid dispenser), from which the resin flows into the damaged (micro-cracks) site; the very low pressure environment (25-29 inHg) in the chamber facilitates the removal of air pockets in the cracks. The composite laminates featured in this project are carbon fibre reinforced composite laminates, which are of great interest to the aerospace industry. Testing and evaluation were carried out by the team to assess the performance of the healant-injection device using impacted carbon fibre

show abstract

A multiscale approach for modelling impact on woven composites under consideration of the fabric topology

Todt

Pettermann

2018

Journal of Composite Materials

View full text Add to dashboard Cite

A computationally efficient multiscale modelling approach for predicting impact damage within fabric reinforced laminated composites is presented. In contrast to common ply-level approaches, the topology of a multi-layered fabric reinforced laminate is resolved at tow-level for a sub-domain embedded in a shell layer with homogenised representation of the laminate. The detailed sub-domain is entirely modelled using shell elements, where material nonlinearities such as damage and plasticity-like behaviour of the tows, inelastic behaviour of unreinforced resin zones up to failure and delamination between plies are accounted for. To exemplify the capabilities of the approach, an explicit finite element simulation of a laminated plate consisting of eight carbon fabric reinforced epoxy plies with eight harness satin weaving style in a drop weight impact test setup is conducted. The spatial and temporal distribution of intra- and inter-ply damage is predicted and the total energy absorption by the plate, as well as the contributions of individual damage mechanisms are evaluated. The predictions show very good agreement with corresponding experimental data from the literature and give insight into the impact behaviour of the laminate beyond the capability of usual experiments. The new approach allows to resolve the stress concentrations due to fabric topology in detail. Compared to common ply-level approaches this is reflected in different predicted energy absorptions per mechanism although, the total energy absorption hardly differs. This is especially important when the post impact behaviour of laminates is predicted as it is strongly influenced by the extent of the individual damage mechanisms.

show abstract

High velocity impact on composite link of aircraft wing flap mechanism

Cited by 3 publications

References 9 publications

Cohesive zone models and impact damage predictions for composite structures

Cohesive zone models and impact damage predictions for composite structures

A simple portable low-pressure healant-injection device for repairing damaged composite laminates

A multiscale approach for modelling impact on woven composites under consideration of the fabric topology

Contact Info

Product

Resources

About