An Approach to Determine Thermal Properties of Spaceborne Solid Materials

Thermal conductance of contacting surfaces is an important parameter for spacecraft thermal design. No universal model exists that can enable one to predict contact resistance between any two surfaces. If none of the available models fit the need for prediction of thermal contact resistance, determination of thermal contact resistance with a proper measurement set up is the best choice. Carbon fiber reinforced plastic or aluminum face sheeted honeycomb cored composite panels are commonly used to construct spacecraft structure. The thermal interaction between composite panels and the equipment is crucial for spacecraft thermal design. The focus of this study to develop thermal contact resistance measurement device to determine contact resistance of composite panels interacting with solid materials in accordance with the American Society for Testing and Materials (ASTM) directives. Thermal contact resistance measurement device is capable of generating interface pressure up to 9.8 MPa and interface temperatures between -50°C and 120°C. By means of the thermal contact resistance measurement device, empirical data for the interaction of composite panels with common solid materials preferred for spacecraft design can be obtained.