You are working for a satellite manufacturer. The satellite is designed for use in a geosynchronous (GEO) orbit. Its electronics unit produces a maximum 500W of waste heat that needs to be dissipated into deep space, and the unit produces a minimum of 100W during stand-by operation. The electronics package contains a heat exchanger with a working fluid that transports waste heat to a radiator. During cold operation (without solar heating), the fluid should not be cooled below 0 °C; during hot operation the fluid should not exceed 50 °C. The fluid is transported passively using heat pipes to the radiator. Specifications of operating conditions are as follows:
Hot conditions (maximum heat generation and solar flux)
Normal incident solar flux =522 W/m²
Solar radiation vector relative to satellite =23°
Cold conditions (minimum heat generation and no sun)
Normal incident solarflux =0 W/m²
The dimensions of the electronics package are 2m x 1m x 1m. Ideally, the radiator will fit onto the package without the need for external panels. Undertake a thermal analysis of the system and specify your choice of materials and coatings for the radiator. You might want to consider louvers to shield the radiator from solar radiation if necessary. Provide data for all your materials properties. Specify the power requirements for a heater, if necessary, to maintain the radiator fluid at the minimum operating temperature. Provide a concise report (four page maximum) of your preliminary analysis and design,with a drawing and references to the sources of data that you used.