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Recent advances in structural technology for large deployable and erectable spacecraftUltra-low mass deployable and erectable truss structure designs for spacecraft are identified using computerized structural sizing techniques. Extremely slender strut proportions are shown to characterize minimum mass spacecraft which are designed for shuttle transport to orbit. Discrete element effects using a recently developed buckling theory for periodic lattice type structures are presented. An analysis of fabrication imperfection effects on the surface accuracy of four different antenna reflector structures is summarized. The tetrahedral truss has the greatest potential of the structures examined for application to accurate or large reflectors. A deployable module which can be efficiently transported is identified and shown to have significant potential for application to future antenna requirements. Investigations of erectable structure assembly are reviewed.
Document ID
19810002906
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Bush, H. G.
(NASA Langley Research Center Hampton, VA, United States)
Heard, W. L., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
October 1, 1980
Subject Category
Structural Mechanics
Report/Patent Number
NASA-TM-81905
IAF-80-A-27
Report Number: NASA-TM-81905
Report Number: IAF-80-A-27
Meeting Information
Meeting: Congr. of the Intern. Astron. Federation,
Location: Tokyo
Country: Japan
Start Date: September 21, 1980
End Date: September 27, 1980
Accession Number
81N11414
Funding Number(s)
PROJECT: RTOP 506-53-43-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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