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Fatigue life evaluation of composite wing spar cap materials

  • Volker Trappe
Published/Copyright: November 18, 2019
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Abstract

An effective method for evaluating the fatigue strength of thick unidirectional composite laminates of wing spar caps has been presented here. A typical width-tapered bending specimen has been developed for a four-point loading set up. Static and fatigue loading was performed at a load ratio R = ‒1. The complex stress state has been investigated numerically by finite element analysis. Finally, the concept is proven experimentally on specimens made of pultruded fibre rods. The fatigue behavior of the continuously tapered width by water jet cutting has been compared to discrete tapering via rod-drop. The new method enables a screening of material fatigue behavior caused by normal and shear loading.


*Correspondence Address, Prof. Dr.-Ing. Volker Trappe, BAM-5.3 – FB “Mechanik der Polymerwerkstoffe”, Unter den Eichen 87, 12205 Berlin; Germany, E-mail:

Prof. Dr.-Ing. Dipl.-Phys. Volker Trappe, was born in 1963 in Göttingen. After receiving his Diploma in Physics in 1994 at the Technical University Braunschweig, he was a Scientific Assistant at the Institute for Aircraft Design and Lightweight Structures where he presented his doctoral thesis “Description of the Intralaminar Fatigue Behavior of CFRP with inner State Variables” in 2001. Since then, he has been a collaborator at the Federal Institute of Materials Research and Testing (BAM) in Berlin, Division 5.3 “Mechanics of Polymers”. Since April 2005 he has been an Assistant Lecturer at the Technical University Berlin, and in 2014 he became Honorary Professor for “In-service strength of lightweight structures”.


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Published Online: 2019-11-18
Published in Print: 2019-12-02

© 2019, Carl Hanser Verlag, München

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