000921726 001__ 921726
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000921726 040__ $$aCIT$$beng$$erda
000921726 049__ $$aCIT6
000921726 099__ $$aTHESIS
000921726 1001_ $$aWilson, Lee L.,$$eauthor.
000921726 24510 $$aAnalysis of packaging and deployment of ultralight space structures $$cLee L. Wilson ; Sergio Pellegrino, advisor.$$h[electronic resource] /
000921726 264_1 $$aPasadena, California :$$bCalifornia Institute of Technology,$$c2017.
000921726 300__ $$a1 online resource (xxiv, 151 leaves) :$$bdigital (34 Mb), illustrations (some color).
000921726 336__ $$2rdacontent$$atext$$btxt
000921726 337__ $$2rdamedia$$acomputer$$bc
000921726 338__ $$2rdacarrier$$aonline resource$$bcr
000921726 347__ $$atext file$$bPDF$$c34 Mb
000921726 4901_ $$aCIT theses ;$$v2017
000921726 500__ $$aAdvisor and committee chair names found in the thesis' metadata record in the digital repository.
000921726 502__ $$aThesis (Ph. D.) -- California Institute of Technology, 2017.
000921726 504__ $$aIncludes bibliographical references.
000921726 5203_ $$aThis thesis presents a new approach to modeling in finite element analysis (FEA) creased thin-film sheets such as those used for drag sails, as well as modeling the packaging behavior of coilable deployable booms.  This is highly advantageous because these deployable space structures are challenging to test on the ground due to their lightweight nature and the effects of gravity and air resistance. Such structures are utilized in the space industry due to their low mass and ability to be packaged into a small volume during their launch into space. It is shown that removing the crease bending stiffness in creased sheets still allows the deployment behavior of a benchmark problem to be captured, including deployment forces and equilibrium configurations.  In addition, folding creased sheets from a flat state into a packaged configuration can result in crease crumpling and excessive wrinkling. To avoid this the Momentless Crease Force Folding (MCFF) technique is developed. Further presented is the behavior of tape springs and Tubular Rollable and Coilable (TRAC) booms when coiled to radii greater than their natural bend radius.  Under these conditions the booms can form multiple localized folds which may jam during boom deployment.  Understanding this behavior is important for extending the use of these booms to large scale space structures such as orbital solar power stations. A useful analytical model is developed determining when the localized folds in a tape spring will bifurcate and is verified against simulation results.  Additionally, a numerical model of the wrapping an isotropic tape spring around a hub with a radius greater than the localized fold radii is validated against physical experiments.  This model is used to predict trends in the force required to fully wrap a tape spring around a given hub radii. Finally, when examining the coiling and uncoiling behavior of TRAC booms it was found that the tension force required to keep a TRAC boom tightly coiled is significantly less than the force required to initially coil the boom.
000921726 5880_ $$aTitle from home page (viewed September 20, 2017).
000921726 653__ $$adeployable
000921726 653__ $$anumerical analysis
000921726 653__ $$asolar sail
000921726 653__ $$aspace
000921726 653__ $$atape spring
000921726 653__ $$athin-film
000921726 653__ $$aTRAC boom
000921726 653__ $$aultralight
000921726 655_0 $$aElectronic dissertations.
000921726 690__ $$aspace
000921726 7001_ $$aPellegrino, S.$$eadvisor.$$q(Sergio),
000921726 7102_ $$aCalifornia Institute of Technology.$$bDivision of Engineering and Applied Science.
000921726 830_0 $$aCIT theses ;$$v2017
000921726 85640 $$uhttp://resolver.caltech.edu/CaltechTHESIS:05242017-230338904$$z<a href="http://resolver.caltech.edu/CaltechTHESIS:05242017-230338904" TARGET="_blank"><img src="https://caltech.tind.io/sslredirect/library.caltech.edu/images/CaltechConnect-button-light.png" style="max-width:81px" alt="Caltech Connect"></a>
000921726 909CO $$ooai:caltech.tind.io:921726$$pcaltech:bibliographic
000921726 948__ $$aPP
000921726 980__ $$aBIB
000921726 998__ $$awww$$b170920$$ca$$dm$$e-