NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Press Enter or click the Search button to begin your search.

Back to Results
Bistable Deployable Composite Booms With Parabolic Cross-SectionsThis paper investigates how stable equilibrium states in the extended and coiled configurations can be predicted in thin-shelled composite booms with parabolic cross-sections. These conic shapes potentially offer greater stiffness properties when compared to circular cross-sections, which is critical for improving the load bearing performance of deployed booms. Inducing bistability through the choice of composite shell layups in parabolic booms would allow for controllable self-deployment due to a less energetic coiled state when compared to monostable booms. An inextensional analytical model is used to predict the stable coiled diameters of tape spring and Collapsible Tubular Mast (CTM) booms with parabolic cross-sections. The parabolic section is discretized into circular segments using biarc spline interpolation, which allows them to be integrated into the strain energy minimization procedure used to obtain the equilibrium states. When the parabolic booms are parametrically compared against circular booms with identical layups, flattened height, and mass, the former are found to generally have better stiffness performance while being less efficient in stowed volume as evidenced by larger
coiled diameters. Analytical coiled diameters and their strain energy are verified with finite element simulations for optimal parabolic tape spring and CTM booms.
Document ID
20210025395
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Andrew J. Lee
(North Carolina State University Raleigh, North Carolina, United States)
Juan M Fernandez
(Langley Research Center Hampton, Virginia, United States)
Jacob G. Day
(North Carolina State University Raleigh, North Carolina, United States)
Date Acquired
December 3, 2021
Subject Category
Structural Mechanics
Meeting Information
Meeting: AIAA SciTech Forum
Location: San Diego, CA
Country: US
Start Date: January 3, 2022
End Date: January 7, 2022
Sponsors: American Institute of Aeronautics and Astronautics
Funding Number(s)
WBS: 969115.04.28.23.01
Distribution Limits
Public
Copyright
Use by or on behalf of the US Gov. Permitted.
Patent
1527021295
Patent Application
15/503,663 (USPub. No. 2020/0011057 A1, US11,199,005)
Technical Review
Single Expert
No Preview Available