Show simple item record Liyanage, PM Mallikarachchi, HMYC 2019-11-22T07:51:12Z 2019-11-22T07:51:12Z
dc.description.abstract A deployable structure should mainly be adequately compact and should fit into any remaining space of the launch vehicle. The main factors which will determine these are the folding pattern, ease of deployment and stresses in the fold lines. Two folding patterns are selected based on extensive literature review to investigate the possibility of using those techniques for a large solar sail mission. It is expensive as well as extremely time consuming to perform experimental investigation under reduced gravity environment for this type of large membranes. Thus developing simulating techniques are quite important. Two models are simulated using Abaqus/Explicit commercial finite element software. Quasistatic conditions and numerical accuracy are verified by comparing strain energy together with kinetic energy and artificial strain energy. It is shown that spiral folding pattern requires less energy for deployment and hence that is preferred. en_US
dc.language.iso en en_US
dc.subject deployable structures, folding patterns, origami en_US
dc.title Folding patterns for ultra-thin deployable membranes en_US
dc.type Conference-Abstract en_US
dc.identifier.faculty Engineering en_US
dc.identifier.department Department of Civil Engineering en_US
dc.identifier.year 2015 en_US
dc.identifier.conference International Symposium on Advances in Civil and Environmental Engineering Practices for Sustainable Development en_US Galle, Sri Lanka en_US
dc.identifier.pgnos pp. 8 - 15 en_US en_US

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