Applying Fiber Support Technology to Small Satellite Systems

Cryogenically cooled components in infrared instruments designed by Utah State University's Space Dynamics Laboratory traditionally have been mounted on glass-epoxy composite (G-10) cylinders for thermal isolation. Ensuring adequate mechanical stiffness to withstand typical launch loads often compromises the desired thermal isolation and conduction parasitic heat loads become a concern. Beginning with a senior design project in the Mechanical and Aerospace Engineering Department, a new approach to rigidly supporting cold components using high performance fibers in tension was initiated. The development effort included consideration of several candidate fibers for tensile strength, shear strength, creep, and thermal conductivity as well as a technique for attaching and tensioning the support strands. * Graduate Student, Mechanical and Aerospace