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Finite Rotation Analysis of Highly Thin and Flexible StructuresDeployable space structures such as sunshields and solar sails are extremely thin and highly flexible with limited bending rigidity. For analytical investigation of their responses during deployment and operation in space, these structures can be modeled as thin shells. The present work examines the applicability of the solid shell element formulation to modeling of deployable space structures. The solid shell element formulation that models a shell as a three-dimensional solid is convenient in that no rotational parameters are needed for the description of kinematics of deformation. However, shell elements may suffer from element locking as the thickness becomes smaller unless special care is taken. It is shown that, when combined with the assumed strain formulation, the solid shell element formulation results in finite element models that are free of locking even for extremely thin structures. Accordingly, they can be used for analysis of highly flexible space structures undergoing geometrically nonlinear finite rotations.
Document ID
20020014426
Acquisition Source
Goddard Space Flight Center
Document Type
Preprint (Draft being sent to journal)
Authors
Clarke, Greg V.
(NASA Goddard Space Flight Center Greenbelt, MD United States)
Lee, Keejoo
(Maryland Univ. College Park, MD United States)
Lee, Sung W.
(Maryland Univ. College Park, MD United States)
Broduer, Stephen J.
Date Acquired
August 20, 2013
Publication Date
January 1, 2001
Subject Category
Structural Mechanics
Meeting Information
Meeting: ICES 2001
Location: Puerto Vallarta
Country: Mexico
Start Date: August 19, 2001
End Date: August 24, 2001
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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