Design and Validation of Thin-Walled Composite Deployable Booms with Tape-Spring Hinges
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.
© 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.
Accepted Version - MallikarachchiAIAA2011.pdf