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Elastic Memory Composite (EMC) materials exhibit many favorable qualities for deployable space structures and have piqued a broad interest within America's deployable space structures industry. EMC materials are similar to traditional fiber-reinforced composites except for the use of a thennoset shape memory resin that enables much higher packaging strains than traditional composites without damage to the fibers or the resin. This unique capability is being exploited in the development of very effcicnt EMC structural components for deployable spacecraft systems. The present paper is intended primarily to help deployable system designers develop a better understanding of the special capabilities of EMC materials, and the unique considerations that must be applied when engineering structural components with these materials. Specifically, the paper discusses: 1) the impacts of incorporating EMC materials on deployable system design, 2) analyses for packaging strain, deployment time, and deployment energy; and 3) requirements and concepts for heating systems.

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing this collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY) SPONSORING / MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSOR/MONITOR'S ACRONYM(S)AFRL/VSSV Air Force Research Laboratory* Space Vehicles Directorate Advanced solar arrays capable of generating greater than 50 kW of total power, at power densities greater than 250 W/kg, are required for many future Air Force missions. The largest heritage systems are limited to less than 20 kW of total power, at roughly 80 W/kg. To meet the requirements of future Air Force missions, the Rollout And Passively Deployed ARray (RAPDAR™) has been developed. This innovative, patent-pending design takes full advantage of the latest advances in thin-film photovoltaic and TEMBO® Elastic Memory Composite (EMC) deployment technologies. A key feature of the design is the use of solar energy to passively actuate the TEMBO® EMC members and deploy the array. The present paper addresses the development and validation of detailed designs for the RAPDAR™ (patent applied for) structural system. Specific focus is placed on comparing the performance projections of RAPDAR™ with other thin-film array systems, and the development and validation of the EMC longerons, which are the primary structural members for the RAPDAR™ system controlling packaging and deployment, and providing primary stiffness and strength to the deployed system. The present paper addresses the development and validation of detailed designs for the RAPDAR™ (patent applied for) structural system. Specific focus is placed on comparing the performance projections of RAPDAR™ with other thin-film array systems, and the development and validation of the EMC longerons, which are the primary structural members for the RAPDAR™ system controlling packaging and deployment, and providing primary stiffness and strength to the deployed system. SUBJECT TERMS