Fundamentals of 3D Deployable Mechanisms in Space

Metadata Updated: May 2, 2019

Fundamentals of 3D Deployable Origami Structures in Space

The primary objectives of my research are to study the application of 3D deployable origami structures in space. The study of origami has produced many innovative ideas and models that have direct application to the design of thick, deployable structures in space such as solar panels. However, the use of deployable structures faces several challenges that must be considered. Some of these challenges include designing structures that can provide the needed folding motion as well as dealing with vibration in flexible structures. Specifically, my work will focus on three major areas:

1.Creating Rigid Foldability

2.Surrogate Folds and Rigid Foldability

3.Vibration of Deployable Structures

A useful characteristic of deployable structures is rigid foldability or the ability to fold without requiring any members to warp or stretch. This characteristic allows a folding structure to be manufactured out of inflexible materials such as steels or glasses as described by Homer et al.

Other problems in the design of deployable structures include incorporating compliant surrogate folds into rigidly foldable structures and studying their vibration characteristics. Work in this area will help increase reliability, reduce part count and prevent premature failure.

Zirbel et al studied the use of a flasher base in the design of a folding solar panel. Merriam describes the design of a compliant pointing mechanism based on spherical mechanisms which are found in origami. Fowler et al described a surrogate hinge suitable for space applications.

Methods for designing rigidly foldable crease patterns will be developed to allow designers to manufacture these mechanisms from rigid components. Options such as adding creases/hinges to a design, removing panels and splitting hinges will be considered to create rigid foldability.

Methods for designing rigidly foldable structures with surrogate hinges as well as techniques for controlling vibration will also be studied. Alterations to current models of rigid origami to account for crease behavior will be studied. Modifications that alter rigidity and damping characteristics will be investigated to control vibration.

Research in deployable origami structures will contribute to achieving goals in the NASA Technology Roadmap. TA12.2 discusses expandable structures such as precision mirrors and solar/antenna arrays and can be benefited by work on these problems. Studying these structures can also benefit precision structure deploy mechanisms discussed in TA12.3.

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Public: This dataset is intended for public access and use. License: U.S. Government Work

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Dates

Metadata Created Date August 1, 2018
Metadata Updated Date May 2, 2019

Metadata Source

Harvested from NASA Data.json

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Resource Type Dataset
Metadata Created Date August 1, 2018
Metadata Updated Date May 2, 2019
Publisher Space Technology Mission Directorate
Unique Identifier TECHPORT_91470
Maintainer
TECHPORT SUPPORT
Maintainer Email
Public Access Level public
Bureau Code 026:00
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Metadata Catalog ID https://data.nasa.gov/data.json
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Datagov Dedupe Retained 20190501230127
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Harvest Source Id 39e4ad2a-47ca-4507-8258-852babd0fd99
Harvest Source Title NASA Data.json
Data First Published 2019-08-01
Homepage URL https://techport.nasa.gov/view/91470
License http://www.usa.gov/publicdomain/label/1.0/
Data Last Modified 2018-07-19
Program Code 026:027
Source Datajson Identifier True
Source Hash baf1cdab71f1c65ef1185190206a52804d2e921e
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