CaltechAUTHORS
Published April 4, 2011 | Version Accepted Version
Book Section - Chapter Open

Design and Validation of Thin-Walled Composite Deployable Booms with Tape-Spring Hinges

Creators

  • 1. ROR icon University of Cambridge
  • 2. ROR icon California Institute of Technology

Abstract

This paper presents a 1 m long self-deployable boom that could be folded around a spacecraft. Previously developed simulation techniques are used to analyze this two-hinge boom, made from two-ply plain weave carbon fiber laminate. A stress-resultant based failure criterion is used to study safety of the structure during both stowage and dynamic deployment. A safe design that latches without any overshoot is selected and validated by a dynamic deployment experiment.

Additional Information

© 2011 by H. M. Y. C. Mallikarachchi and S. Pellegrino. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. We thank Dr Michael Sutcliffe for helpful discussions and Professor Chiara Daraio and Dr Jinkyu Yang for help with high speed imaging. John Ellis (Hexcel, UK) kindly provided materials for our experiments. HM thanks the Cambridge Commonwealth Trust and the California Institute of Technology for financial support.

Attached Files

Accepted Version - MallikarachchiAIAA2011.pdf

Files

MallikarachchiAIAA2011.pdf

Files (4.4 MB)

Name Size
md5:f9514d87cc88d2745d2628f101cc1aff
4.4 MB Preview Download

Additional details

Identifiers

Eprint ID
98940
Resolver ID
CaltechAUTHORS:20190930-110458726

Funding

Cambridge Commonwealth Trust
Caltech

Dates

Created
2019-10-04
Created from EPrint's datestamp field
Updated
2021-11-16
Created from EPrint's last_modified field

Caltech Custom Metadata

Caltech groups
GALCIT
Other Numbering System Name
AIAA Paper
Other Numbering System Identifier
2011-2019