Exercice : Suppose the structure is cubed shaped 0.3 m, on an edge, with solar panels on the four sides. Manufacturer specifications for the panels tell us their transmissivity is zero, their reflectivity is 0.05 and their absorptivity is 0.95 and efficiency of 20%. Pannel emissivity is 0.85. The top and bottom sections of the satellite are covered in Multi-Layer Insulation (MLI) providing an emissivity of 0.00 and absorptivity of 0.00 (perfect insulator). Suppose the satellite needs 11.5 W to operate. During payload operations, an additional 20 W peak power is consumed. Determine the equilibrium temperature for the satellite with full sunlight on one solar panel during payload operation, and in eclipse (no payload operation during eclipse). You can ignore the input of the Earth radiation on the nadir-facing panel since it is covered in MLI. The solar flux is about 1350 Watt/m2