paraffin wax that melts around the maximum operating temperature of the satellite components one method to perform this would be to drill a hole in one surface of the carbon carbon face sheets and vacuum fill the phase change material in the liquid state into the porous foam once filled the sample can be cooled the phase change material solidifies and the hole can be plugged with an epoxy or screw type cap the epoxy and any other sealant must be able to withstand the operating temperature of the application the foam core composite will then be mounted on the side of the satellite that is exposed to the sun during orbit as the satellite orbits the earth and is exposed to the sun the radiant energy from the sun will begin to heat the composite panel to the melting point of the phase change material at this point the panel will not increase in temperature as the phase change material melts the amount of radiant energy the panel can absorb will be dependent on the thickness and outer dimensions of the panel this can be easily calculated and designed through knowledge of the orbit times of the satellite such that the material never completely melts and thus never exceeds the melt temperature then when the satellite leaves the view of the sun it will begin to radiate heat to space and the phase change material will begin to freeze the cycle will repeat itself once the satellite comes into view of the sun once again currently.