A solar panel mounted on a spacecraft has an area of 1m^2 and a solar to the electrical power conversion efficiency of 12%. The side of the panel with the photovoltaic array has an emissivity of 0.8 and a solar absorptivity of 0.8. The backside of the panel has an emissivity of 0.7. The array is oriented normal to the solar irradiation of 1500 W/m^2.

(a) Determine the steady-state temperature of the panel and the electrical power (W) produce for the prescribed conditions.

(b) If the panel were a thin plate without the solar cells, but with the same radiative properties, determine the temperature of the plate for the prescribed conditions. Compare this result with that from part(a). Are they the same or different? Explain.

(c) Determine the temperature of the solar panel 1500s after the spacecraft is eclipsed by a planet. The thermal capacity of the panel per unit area is 9000 J/m^2*K