Finite element-based damage and failure analysis of honeycomb core sandwich composite structures for space applications

K. R. Venkatesan, A. Rai, A. Chattopadhyay, T. Stoumbos, D. Inoyama

Research output: Chapter in Book/Report/Conference proceedingConference contribution

2 Scopus citations

Abstract

The paper presents an investigation into the thermomechanical performance of complex composite sandwich structures with adhesively bonded metallic fittings when exposed to extreme temperature ranges. A detailed finite element analysis is conducted by explicitly modeling the honeycomb core geometry with a cup metallic fitting. The material properties for the core sheet are identified from the experimental load-displacement curves of the test coupons. The identified properties are implemented in a finite element model of a sandwich cylindrical panel section of a spacecraft’s thrust tube subjected to thermal cycles. The critical stresses and potential failure modes of the sandwich panel section with the cup bonded fitting are correlated with experimental observations. The developed methodology for the analysis of composite sandwich structures is intended to investigate thrust tubes with other configurations of bonded joints and fittings.

Original languageEnglish (US)
Title of host publicationAIAA Scitech 2020 Forum
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105951
DOIs
StatePublished - 2020
EventAIAA Scitech Forum, 2020 - Orlando, United States
Duration: Jan 6 2020Jan 10 2020

Publication series

NameAIAA Scitech 2020 Forum
Volume1 PartF

Conference

ConferenceAIAA Scitech Forum, 2020
Country/TerritoryUnited States
CityOrlando
Period1/6/201/10/20

ASJC Scopus subject areas

  • Aerospace Engineering

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