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Minimum mass design of large-scale space trusses subjected to thermal gradients

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dc.contributor.author Williams, R. Brett
dc.contributor.author Agnes, Gregory S.
dc.date.accessioned 2006-05-01T20:25:18Z
dc.date.available 2006-05-01T20:25:18Z
dc.date.issued 2006-05-01
dc.identifier.citation 47th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics,and Materials Conference, Newport, Rhode Island, May 1-4, 2006. en
dc.identifier.clearanceno 06-0980
dc.identifier.uri http://hdl.handle.net/2014/39195
dc.description.abstract Lightweight, deployable trusses are commonly used to support space-borne instruments including RF reflectors, radar panels, and telescope optics. While in orbit, these support structures are subjected to thermal gradients that vary with altitude, location in orbit, and self-shadowing. Since these instruments have tight dimensional-stability requirements, their truss members are often covered with multi-layer insulation (MLI) blankets to minimize thermal distortions. This paper develops a radiation heat transfer model to predict the thermal gradient experienced by a triangular truss supporting a long, linear radar panel in Medium Earth Orbit (MEO). The influence of self-shadowing effects of the radar panel are included in the analysis, and the influence of both MLI thickness and outer covers/coatings on the magnitude of the thermal gradient are formed into a simple, two-dimensional analysis. This thermal model is then used to size and estimate the structural mass of a triangular truss that meets a given set of structural requirements. en
dc.description.sponsorship NASA/JPL en
dc.format.extent 515410 bytes
dc.format.mimetype application/pdf
dc.language.iso en_US en
dc.publisher Pasadena, CA : Jet Propulsion Laboratory, National Aeronautics and Space Administration, 2006. en
dc.subject orbital heating en
dc.subject thermal truss analysis en
dc.title Minimum mass design of large-scale space trusses subjected to thermal gradients en
dc.type Preprint en


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