Thermally Conductive Hinge Development for Deployable Radiators (kTC P k002)

Period of Performance: 05/01/2000 - 04/02/2001


Phase 1 SBIR

Recipient Firm

K Technology Corp.
2000 West Cabot Blvd.Suite 150
Langhorne, PA 19047
Principal Investigator


The current development trend of small, highly integrated satellites has created a challenge to remove heat. These small satellites have less surface area available for static radiator panels. To increase the radiative area, deployable radiators are used. Deployable space radiators require a hinge or flexible joint to provide the degree of freedom to deploy. Traditional designs using aluminum foil stacks are bulky and can be excessively stiff. kTC's thermal hinge concept incorporates thin high conductivity pyrolytic graphite foils. These flexible foils have high conductivity (>1000 W/mK) and low mass (