Description: While the CubeSat launch rate has steadily increased since their inception in 1999, the incidence rate of failure has unfortunately remained very high. For NASA�s Heliophysics program, the fundamental challenge is designing CubeSats capable of making accurate and meaningful measurements of slight variations in Earth�s magnetic field. Such measurements help maintain the accuracy of models that are used for many science and society applications, including the study of Space Weather, the Earth�s core, navigation, chartography, drilling and many more. The Heliophysics Division at GSFC is a world leader in the development of magnetic field sensor systems and is leading NASA�s efforts to grow this science by investing in magnetic field measurement technologies that can be miniaturized for CubeSat missions. Through in-house programs, GSFC has created a new suite of miniature magnetometer instruments compatible with CubeSat architectures. However, achieving data of scientific value requires not only advancements in the sensors themselves, but also development of high quality non-magnetic, non-conducting, thermally-stable rigid booms to separate the sensors from the noise of the spacecraft bus. To date no CubeSat mission has successfully flown a science magnetometer. This is primarily due to the lack of a reliable and inexpensive boom technology that is appropriate for 1) the CubeSat form factor and 2) a science magnetometer application. The above Harris development faces many of the same scaling challenges. Namely, it is very difficult to scale the thickness of a high strain composite boom down to the CubeSat form factor as the individual lamina constituent materials result in an inherent ply thickness that will not scale. As a result, these small (i.e. CubeSat) boom systems must operate at very high packaging strains. The aforementioned Harris effort is expected to solve many of the challenges of scaling a boom system to the CubeSat form factor. A new class of composite CubeSat boom will be developed, and novel approaches towards how these miniaturized booms are supported during the stowage and deployment process will be addressed. The proposed CRP effort will leverage these advancements, while ensuring the requirements for a science magnetometer mission are also achieved. As a result, the combined Harris project and NASA CRP will culminate in a new class of CubeSat �ROC-Booms� that are appropriate for magnetometer applications. In particular, the expected benefits of the new ROC-Booms are summarized in Table 1. These specifications have been quantified by the Heliophysics team that work on CubeSat magnetometers, and the engineering team that designed and built the magnetometer boom for the ST5 mission. The proposed CRP program will the validate several of these key performance (stability and magnetic signature) benefits, while creating enough detail in the system design for Roccor to make a preliminary assessment of the feasibility of achieving a one-tenth purchase price as compared with current COTS systems (~$25K per boom versus ~$250K per boom). Initially, under both the Harris-funded and NASA-funded activities emphasis will be placed on requirements definition. Once an adequate set of engineering requirements are established, detailed design activities will commence, with a design review planned for roughly the midpoint of the program (six months after contract start), and hardware fabrication expected to shortly thereafter. Functional and acceptance testing is expected to be completed during the last three months of the program with some time reserved during that quarter for engineering re-work as necessary. As this work is going on, Roccor will remain in close conversation with both Harris and NASA GSFC to coordinate delivery of the test article(s) in a timely fashion and to allow integration within Harris� RF antenna ground test program and NASA�s magnetometer ground test program at GSFC.