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 TEMBO™ 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.