NASA 1996 SBIR Phase I

PROJECT TITLE : Novel Materials For Thermal Management of Spacecraft Systems

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Novel materials are needed to support the performance and function of thermal doublers, zero CTE optical benches, lightweight CTE matched heat spreaders for heat pipe evaporator and condenser ends, and thermal cores for electronic assemblies. Highly oriented pyrolitic graphite (HOPG) is a highly aligned crystalline graphite with an in-plane thermal conductivity of 1700 W/mK . Encapsulating HOPG within a carbon fiber composite results in a high conductivity (>1000 W/mK), low mass density (<2.0 g/cm3) material system. The isotropic in-plane conductivity of the HOPG will increase the composite thermal performance by 300% over typical K1000/Epoxy composites. In addition to high specific conductivity, the proposed material system can have tailored thermal expansion and stiffness properties.

The objective of this Phase I program is to determine the feasibility of using the carbon fiber encapsulated HOPG material system in spacecraft systems through the development and evaluation of material samples. The program will establish, through sample evaluation, key design, fabrication and performance characteristics.

Future commercial satellite platforms are dependent on proven, successful new technologies to reduce weight and improve reliability. Novel materials will allow for increased payload s with higher reliability. These payoffs will support the trend toward smaller less expensive satellites

Mark J. Montesano
k Technology Corporation
500 Office Center Drive, Suite 250
Fort Washington, PA 19034

k Technology Corporation
500 Office Center Drive, Suite 250
Fort Washington, PA 19034