Campusleben_HAW_Hamburg_21

Lehrende_HAW_Hamburg_19

Studierende_HAW_Hamburg_21

Informationen für:

Publikationen von Professorinnen und Professoren der HAW Hamburg

Jahr:  
Alle : 1997, ... , 2016, 2017, 2018, 2019
Autor:  
Alle : A, À, B, C, D, E, F, G, H, I, J, K, L, M, N, O, Ö, P, Q, R, S, T, U, V, W, Y, Z 
Alle : O'Brien, ... , Oltrogge, Omenche, Omer Farooq, ... , Ozuyar 
Präferenzen: 
Referenzen pro Seite: Zeige Schlüsselwörter Zeige Zusammenfassung
Referenzen

Zeitschriftenbeiträge:

default
R. Von Katzler, B.C. Zyriax, B. Jagemann, J. Westenhöfer, H.J. Jensen, V. Hardt und M. Oldenburg
Lifestyle behaviour and prevalence of cardiovascular risk factors - a pilot study comparing comparison between Kiribati and European seafarers.
BMC Public Health, 19:855
2019

Marker: LS-GW

default
Christian Berger, Mari Bieri, Karen Bradshaw, Christian Brümmer, Thomas Clemen, Thomas Hickler, Werner Leo Kutsch, Ulfia A Lenfers, Carola Martens, Guy F Midgley, Kanisios Mukwashi und Victor Odipo
Linking scales and disciplines : an interdisciplinary cross-scale approach to supporting climate-relevant ecosystem management
Climatic Change, 156:139-150
2019

Marker: TI-I

Plakate:

default
Aurelio Jose Olivares Ferrer und Markus Linke
Prediction of residual strength and delamination growth of thin CFRP laminates with re-infiltrated Barely-Visible-Impact-Damage
13 November 2019
HAW Hamburg
Englisch
Dies Academicus 2019 Forum Finkenau

Schlüsselwörter: Composite materials; CFRP; Impact damage; BVID; Repairs; Re-infiltration; Finite element modeling; CAI test; 3PB fatigue; Ultrasonic C-Scans; Computer Tomography

Marker: F+F

Zusammenfassung: Thin-walled Carbon-Fiber-Reinforced-Plastics (CFRP) laminates are becoming one of the composite materials most widely used in aeronautical industry for structural parts because of their high specific stiffness and strength. Nevertheless, the impact strength is one of its main drawbacks. Consequently, even low-energy impacts (the most frequent ones) such as accidental tool falls during ground services can cause instances of damage. Mainly, low-energy impacts induce internal damage patterns made of matrix cracks and delaminations in the laminates. They are classified as Barely-Visible-Impact-Damage (BVID) and present a stochastic nature. The pristine properties of laminates with BVIDs can be completely restored by gluing together the internal cracks. Nowadays, the technique that can perform such repair is known as re-infiltration. But, in the aeronautical industry there is no certification process available for primary structural repairs with this technique. In order to certify gluing repairs of damage with a stochastic nature, aeronautical approval authorities demand to prove the load bearing capacity (residual strength and damage growth) by means of experimental tests and numerical predictions. Therefore, the goal of this thesis is to investigate numerical models and methods capable to predict the residual strength and delamination growth of thin-walled CFRP laminates with re-infiltrated BVID. The numerical models will be based on Abaqus finite element code and validated experimentally. Furthermore, in order to perform the repairs, the re-infiltration method will be further developed. Finally, the Non-Destructive-Testing techniques based on ultrasonic scans and computer tomography will be used to model the internal damage patterns in the finite element models.

default
Aurelio Jose Olivares Ferrer und Markus Linke
Prediction of residual strength and delamination growth of thin CFRP laminates with re-infiltrated Barely-Visible-Impact-Damage
25 Oktober 2019
Universitat Politecnica de Valencia, in Valencia (Spain)
Englisch
5th CARPE Conference

Schlüsselwörter: Composite materials; CFRP; Impact damage; BVID; Repairs; Re-infiltration; Finite element modeling; CAI test; 3PB fatigue; Ultrasonic C-Scans; Computer Tomography

Marker: F+F

Konferenz-/Workshop-/Podiumsdiskussionsbeiträge, Ausstellungs-/Modenschaubeteiligungen:

default
Aurelio Jose Olivares Ferrer und Markus Linke
Post-buckling behavior of thin-walled damaged laminates under Compression-After-Impact loading
3DEXPERIENCE Conference Design, Modeling and simulation 2019
Darmstadt, Germany
20 November 2019
Englisch

Schlüsselwörter: Composite materials; CFRP; Impact damage; CAI test; Finite element modeling; Post-buckling

Marker: F+F

Zusammenfassung: The use of thin-walled Carbon-Fiber-Reinforced-Polymer (CFRP) laminates in structural components of aircraft is increasing in recent decades. These components are exposed to receive accidental impacts during its life, most of them classified as low-energy impacts. These impacts cause instances of internal damage in the components. Mainly, delaminations and matrix cracks. Therefore, the laminates used in the structure must be able to work below a certain damage threshold. In the aeronautical industry, the Compression-After-Impact (CAI) test is used to evaluate the residual strength of damaged laminates and there is plenty of open literature for thick laminates. However, when thin laminates are tested under the CAI test, global buckling starts before the laminate rupture. Then, there is an interaction between the global buckling and the local initial damage caused by the previous impact. Then, this become a problem with geometrical and material non-linearities that can be investigated by using the Finite Element code Abaqus (Dassault Systèmes SA, Paris, France). Therefore, this work focuses on how to build-up a model able to predict the residual strength of thin CFRP laminate plates with an idealized initial damaged area under the CAI test. For this purpose, conventional and continuum shell elements are used for verifying the build-up process of the model, as well as, implicit and explicit solver. Finally, Hashin’s criteria and cohesive elements are used to predict the intralaminar failure and delamination growth in the interfaces, respectively.

default
Aurelio Jose Olivares Ferrer, Markus Linke und Juan Antonio García Manrique
Influence of geometric imperfections and internal damage patterns of thin-walled laminates on failure in Compression-After-Impact testing
MESIC 2019 conference
Madrid (Spanien)
20 Juni 2019
Englisch

Schlüsselwörter: Finite elements; Abaqus; Compression-After-Impact testing; geometric imperfection; delamination; internal damage; composites; CFRP; ultrasonic scan; low-energy impacts.

Marker: F+F

Zusammenfassung: Geometric imperfections are induced in composite structures due to manufacturing and assembly processes as well as due to accidental impacts. These geometric imperfections have an influence on the strength of thin-walled composite structures when impact damage is present. Therefore, the influence of the geometric imperfection magnitude on the failure mechanisms of thinwalled laminates with initial internal damage patterns under Compression-After-Impact testing is investigated by creating a finite element model based on different experimental validations. These experiments are a set of tensile tests, low energy impact tests with a pendulum system to induce the internal damage patterns, ultrasonic scanning of the damaged samples to characterize the delaminated areas and, finally, a set of Compression-After-Impact tests combined with digital imaging correlation data using an ARAMIS 3D measuring system (Gom mbH, Braunschweig, Germany). Compression-After-Impact tests are carried out with a frame modified for thin-walled laminates enabling a more reliable measurement of thin laminates. All these data collected during the experiments and damage inspections are used to build up and validate the simulations with the Finite Element code Abaqus (Dassault Systèmes SA, Paris, France). Finally, potential interactions between global and local failure mechanisms in Compression- After-Impact testing are analyzed with different imperfection magnitudes and interface damage idealizations based on these models. The results show an increase of the failure strength with the initial imperfection magnitude.

Total:
90
Export als:
BibTeX, XML

Letzte Änderung: 23.01.15

An die Redaktion