Future large aperture telescopes will require several deployable subsystems, including Primary Mirrors (PM), Secondary Mirror Support Structures (SMSS), and Optical Barrel Assemblies (OBA). The three subsystems must be specifically designed to package together but then deploy separately and operate without disturbing each other. This work presents a point design for a combined SMSS and OBA deployable structure for a non-deployed PM telescope. The architecture uses elastic strain energy composites to provide high precision, lightweight, reliable, and repeatedly verifiable deployment. A full scale proof of concept was built using non-flight materials and successfully stowed and deployed many times. Component and full system tests and analyses were performed to estimate the performance for an equivalent system using flight materials.
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