Auniversity group designs a 1kg cylindrical pico-satellite 10cm diameter and 20cm in height. the satellite has an internal power dissipation of 2.4w and a specific heat capacity of 880 jkgk the two circular ends are polished aluminum while the curved cylindrical surface is completely covered with solar cells. the thermo-optical properties of the surfaces are as follows solar absorptivity of aluminum 10 % infra-red emissivity of aluminum 5% solar absorptivity of solar cells 90% 95% infra-red emissivity of solar cells given the following data as 5.67 x 108 wm2k stefan-boltzman constant 1400 wm2 maximum solar flux find the maximum eguilibrium temperature of spacecraft due to the sum of insolation and the internal power dissipation alone firstly, with the sun shining orthogonally to the long: axis of the cylinder secondly, with the sun shining directly along the long axis of the cylinder given that the satellite has reached its maximum temperature, calculate the initial rate of change immediately after entering the earth's shadow.