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Experimental study of the low-velocity impact behaviour of primary sandwich structures in aircraft
Authors:Joris Leijten  Harald EN Bersee  Otto K Bergsma  Adriaan Beukers
Affiliation:1. Department of Aircraft Design, Beihang University, Beijing 100191, PR China;2. Faculty of Engineering and Computing, Coventry University, Coventry CV1 2JH, UK;1. NASA Langley Research Center, Hampton, VA 23681, United States;2. National Institute of Aerospace, Hampton, VA 23666, United States;3. Syracuse University, Syracuse, NY 13244, United States;1. AMADE, Polytechnic School, University of Girona, Campus Montilivi s/n, 17071 Girona, Spain;2. Aernnova Engineering Division, Structural Integrity Department, 20 Manoteras Avenue – Building B, 5th Floor, 28050 Madrid, Spain;3. Oxeon AB, Företagsgatan 24, 504 64 Borås, Sweden;1. College of Engineering, Ocean University of China, Qingdao 266100, China;2. Shandong Provincial Key Laboratory of Ocean Engineering, Ocean University of China, Qingdao 266100, China;3. School of Aerospace, Mechanical and Mechatronic Engineering, The University of Sydney, Sydney, NSW 2006, Australia;4. School of Naval Architecture and Ocean Engineering, Huazhong University of Science and Technology, Wuhan, Hubei 430074, China
Abstract:The susceptibility of sandwich structures to localised (impact) damage is one of the main reasons why the sandwich concept is not yet used in large primary aircraft structures of airliners. The objective of this work is to experimentally investigate the damage tolerance of representative composite sandwich panels for primary aircraft structures. Instrumented low-velocity impact tests were performed on sandwich specimens consisting of carbon Non-Crimp Fabric/epoxy facings and a Rohacell (PMI) foam core. Both internal and external damage resulting from these impact events was evaluated.The foam core material has a considerable influence on the amount of damage detected by ultrasonic TTU C-scan. CAI tests however showed that this core damage has no significant influence on the residual compressive strength of the specimens.
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