A spherical satellite in near-earth orbit is exposed to solar irradiation of 1353 W/m2. To maintain a desired operating temperature, the thermal control engineer intends to use a checker pattern for which a fraction F of the satellite surface is coated with an evaporated aluminum film (8 = 0.03, αS = 0.09) and the fraction (1-F) is coated with a white, zinc-oxide paint (8 = 0.85, as = 0.22). Assume the satellite is isothermal and has no internal power dissipation. Determine the fraction F of the checker pattern required to maintain the satellite at 300 K.