Deployment Optimization of a Boom for FalconSAT-3 using Elastic Memory Composite Material

Rationale for the inclusion of deployable structures onboard small satellites is ever increasing. For example, replacing traditional mass-expulsion control thrusters with micropropulsion ion thrusters on extendible booms can significantly reduce fuel mass requirements for attitude control systems. However, current flight-heritage booms are rendered inadequate when held to the stringent mass and mechanical requirements necessary to justify such a change. To address the deficiencies of existing boom technologies, a new generation of deployable structures must be developed. Paramount in this endeavor will be the ability to incorporate new materials into the design of next-generation deployable space structures. One promising new material/ technology for longeron members of deployable booms is TEMBOTM Elastic Memory Composite (EMC). EMC retains the structural properties of traditional fiber reinforced composites, i.e. high stiffness to mass ratio, while possessing the ability to behave as a shape memory material. These characteristics enable the primary structural component of a boom to additionally function as the primary deployment mechanism. This paper will focus on the developmental efforts encountered while advancing EMC from a material concept to a viable boom technology. In particular, this paper will introduce a family of deployable EMC booms and then outline the down select process employed during the development of the baseline United States Air Force Academy FalconSat-3 microsat boom.