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Research Papers: Design of Mechanisms and Robotic Systems

An Approach to Designing Origami-Adapted Aerospace Mechanisms

[+] Author and Article Information
Jessica Morgan, Spencer P. Magleby, Larry L. Howell

Department of Mechanical Engineering,
Brigham Young University,
Provo, UT 84602

Contributed by the Mechanisms and Robotics Committee of ASME for publication in the JOURNAL OF MECHANICAL DESIGN. Manuscript received October 9, 2015; final manuscript received February 11, 2016; published online March 25, 2016. Assoc. Editor: David Myszka.

J. Mech. Des 138(5), 052301 (Mar 25, 2016) (10 pages) Paper No: MD-15-1694; doi: 10.1115/1.4032973 History: Received October 09, 2015; Revised February 11, 2016

An approach to designing products based on adapting patterns and behaviors from origami is presented. The approach is illustrated by showing its capability for developing mechanism applications for aerospace-based systems. Origami has several attributes that are sought after in aerospace designs, such as deployability, stowability, and portability. The origami-adapted design process seeks to facilitate designers in reliably adapting origami into useful products that achieve desirable attributes. The origami-adapted design process is illustrated and tested using three examples of preliminary design: an origami bellows to protect the drill shafts of a Mars Rover, an expandable habitat for the International Space Station, and a deployable parabolic antenna for space and earth communication systems. Each of these examples starts with an origami fold pattern and modifies it to fulfill specific needs for an aerospace-based product.

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Figures

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Fig. 1

A fidelity continuum ranging from a direct, idealized use of the mathematical model of origami to abstract applications of origami [1,2]

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Fig. 2

Diagram of origami-adapted design process [6]

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Fig. 3

A diagram showing the general material design options and descriptions based on whether the product needs to be rigid and/or continuous

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Fig. 4

Various origami models that can be applied to a bellows

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Fig. 5

(a) The Kresling and accordion fold patterns shown (b) folded to fit the dimension restrictions of the drill shafts of the Mars rover. Both fold patterns have the same compressed height and are optimized to maximize the deployed height and compressibility. The Kresling fold pattern has a higher compressibility.

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Fig. 6

The Kresling fold pattern folded in Mylar, Tyvek, Kapton, and UHMWPE. These materials are possible candidates for the final material and were subjected to testing for final selection.

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Fig. 7

The (a) fold pattern and (b) deployment sequence of the Tachi–Miura polyhedron

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Fig. 8

The four-sided accordion fold pattern (a) without modification and (b) modified with additional creases to improve its deployment

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Fig. 9

A prototype of the habitat using the modified accordion fold pattern in thick, rigid material in both its stowed and deployed states

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Fig. 10

The flasher fold pattern modified to create curvature. (a) To add curvature, one wedge of the flasher fold pattern is removed and the two adjacent wedges are attached. (b) Prototype of the 6n − 1 antenna using the 6 deg flasher fold pattern minus one wedge.

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Fig. 11

The mixed tension resistant surrogate hinge to be applied to the deployable parabolic antenna design [44]

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Fig. 12

Deployable antenna adapted from the flasher fold pattern in both its stowed and deployed states

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Fig. 13

Three antennas with different curvature. From left to right, they are the 6n − 1, 7n − 1, and 7n − 2 antenna. The first number refers to the degree of the flasher fold pattern used and the second value is the number of wedges removed to give curvature.

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Fig. 14

Plot of the vertices of the 6n − 1 antenna curved fitted to a parabolic curve

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