PSI - Issue 19

Available online at www.sciencedirect.com Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2019) 000 – 000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2019) 000 – 000

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ScienceDirect

Procedia Structural Integrity 19 (2019) 101–105

Fatigue Design 2019 Fatigue damage and failure analysis of honeycomb sandwich Fatigue Design 2019 Fatigue damage and failure analysis of honeycomb sandwich

F.Alila a , P.Casari a a Université de Nantes, France F.Alila a , P.Casari a a Université de Nantes, France

Abstract Fatigue behavior of sandwich structures with honeycomb core and GFRP skins is studied and failure mode is investigated through tomographic observations. The first S/N curves are presented. The second part discusses the failure modes observed during fatigue tests and responsible for stiffness decrease during fatigue tests. Abstract Fatigue behavior of sandwic structures with honeycomb core and GFRP skins is studied and failure mode is in estigated through tomographic bservati n . Th first S/N curves are present d. The second part discusses the failure modes observed during fatigue tests and responsible for stiffness decrease during fatigue tests.

© 2019 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Fatigue Design 2019 Organizers. © 2019 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Fatigue Design 2019 Organizers. © 2019 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Fatigue Design 2019 Organizers.

Keywords: Fatigue; Honeycomb; Composite; Failure Keywords: Fatigue; Honeycomb; Composite; Failure

1. Introduction Fatigue of composite materials has been less studied during numerous years since these materials were known not to damage under cyclic loading (particularly entrenched reputation for materials-based carbon fiber in the world of aeronautics) [1 – 6]. Their use is being more and more important in many industries. However the increasingly occurrence of frequent and early failure in composite structure showed the necessity to design and study these structures also in fatigue. Thus the complex aspect of the fatigue phenomenon of composite materials and industrial interest have contributed to the further development of research on the subject over the past two decades [7 – 9]. In terms of complexity it can be cited for example failure modes and multi-axial stress state. The stress distribution in a composite material is often multi-axial even when subjected to a single load. In aeronautics, the use of sandwich structures is being increased due to their weight-performance ratio. The challenge nowadays in aeronautics transport field is the reduction of energy consumption by reducing the weight of the airplane [10 – 12]. For equal reliability and durability and with significant weight savings compared to metal materials, new materials are trying to meet this challenge. Among these materials there may be mentioned the sandwich structures with foam or honeycomb core [13]. In this paper honeycomb core sandwich with GFRP faces was studied in fatigue under 4 point bending test. Honeycomb core sandwich could be fabricated in two different ways. In fact, honeycomb structure is a hexagonal 1. Introduction Fatigue of composite materials has been less studied during numerous years since these materials were known not to damage under cyclic loading (particularly entrenched reputation for materials-based carbon fiber in the world of aeronautics) [1 – 6]. Their use is being more and more important in many industries. However the increasingly occurrence of frequent and early failure in composite structure showed the necessity to design and study these structures also in fatigue. Thus the complex aspect of the fatigue phenomenon of composite materials and industrial interest have contributed to the further development of research on the subject over the past two decades [7 – 9]. In terms of complexity it can be cited for example failure modes and multi-axial stress state. The stress distribution in a composite material is often multi-axial even when subjected to a single load. In aeronautics, the use of sandwich structures is being increased due to their weight-performance ratio. The challenge nowadays in aeronautics transport field is the reduction of energy consumption by reducing the weight of the airplane [10 – 12]. For equal reliability and durability and with significant weight savings compared to metal materials, new materials are trying to meet this challenge. Among these materials there may be mentioned the sandwich structures with foam or honeycomb core [13]. In this paper honeycomb core sandwich with GFRP faces was studied in fatigue under 4 point bending test. Honeycomb core sandwich could be fabricated in two different ways. In fact, honeycomb structure is a hexagonal

2452-3216 © 2019 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Fatigue Design 2019 Organizers. 2452-3216 © 2019 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Fatigue Design 2019 Organizers.

2452-3216 © 2019 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Fatigue Design 2019 Organizers. 10.1016/j.prostr.2019.12.012