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Minimum mass design of large-scale space trusses subjected to thermal gradientsLightweight, 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.
Document ID
20060044022
Acquisition Source
Jet Propulsion Laboratory
Document Type
Conference Paper
External Source(s)
Authors
Williams, R. Brett
Agnes, Gregory S.
Date Acquired
August 23, 2013
Publication Date
May 1, 2006
Subject Category
Structural Mechanics
Meeting Information
Meeting: 47th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics,and Materials Conference
Location: Newport RI
Country: United States
Start Date: May 1, 2006
End Date: May 4, 2006
Distribution Limits
Public
Copyright
Other
Keywords
thermal truss analysis
orbital heating

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