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Accommodating Thickness in Origami-Based Deployable ArraysThe purpose of this work is to create deployment systems with a large ratio of stowed-to-deployed diameter. Deployment from a compact form to a final flat state can be achieved through origami-inspired folding of panels. There are many models capable of this motion when folded in a material with negligible thickness; however, when the application requires the folding of thick, rigid panels, attention must be paid to the effect of material thickness not only on the final folded state, but also during the folding motion (i.e., the panels must not be required to flex to attain the final folded form). The objective is to develop new methods for deployment from a compact folded form to a large circular array (or other final form). This paper describes a mathematical model for modifying the pattern to accommodate material thickness in the context of the design, modeling, and testing of a deployable system inspired by an origami six-sided flasher model. The model is demonstrated in hardware as a 1/20th scale prototype of a deployable solar array for space applications. The resulting prototype has a ratio of stowed-to-deployed diameter of 9.2 (or 1.25 m deployed outer diameter to 0.136 m stowed outer diameter).
Document ID
20150008719
Document Type
Conference Paper
External Source(s)
Authors
Zirbel, Shannon A.
(Brigham Young Univ. Provo, UT, United States)
Magleby, Spencer P.
(Brigham Young Univ. Provo, UT, United States)
Howell, Larry L.
(Brigham Young Univ. Provo, UT, United States)
Lang, Robert J.
(Lang Origami Alamo, CA, United States)
Thomson, Mark W.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Sigel, Deborah A.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Walkemeyer, Phillip E.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Trease, Brian P.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Date Acquired
May 21, 2015
Publication Date
August 4, 2013
Subject Category
Spacecraft Propulsion And Power
Structural Mechanics
Report/Patent Number
DETC2013-12348
Meeting Information
ASME International Design Engineering Technical Conference and Computers and Information in Engineering Conference(Portland, OR)
Distribution Limits
Public
Copyright
Other
Keywords
flasher
rigid
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