AMO, 28°C, and the sizing of the array is based on 125°C operating temperature (18.2% cell efficiency). The total output of the array is 10.3 GW with a voltage output of 45.5 kv for each array panel. The solar blanket weight is 7.65 x 10^6 kg, and the total array weight (including the concentrator) is 8.83 x 10^6 kg. This weight is based on a specific weight for the blanket of 0.25 kg/m and 61.2 x 10^6 m^2 cell area. A cross-section of the solar cell is also shown (Figure R-4). The 20-pm synthetic sapphire (Al2O3) substrate, used in an inverse orientation, also acts as the cell cover. The solar blanket layout is shown in Figure R-5. The solar panel in the top trough (effective cell area) measures 600 x 750 m x 2 for 900,000 m . Twelve panels are required for the top trough. The panels for the two lower troughs 2 are slightly smaller in width and measure 550 x 750 m x 2 for 825,000 m (effective cell area). Twenty-four panels are required for the bottom troughs. The total deployed solar area for the SPS is 30.6 x 10 m which is comprised of 10.8 x 10^6 m^2 in the top troughs and 19.8 x 10^6 m in the bottom troughs. The basic building block is a 1 m2 module configuration and the cells are connected together in a series parallel arrangement. The voltage output of each 1 m module is 30.3 V with a current of 11.11 amps. The module output is calculated to be 336.6 W/m^2 at the end of life. D. Solar Array and Structure Reflectors - Thin reflector membranes are used on the SPS to reflect the sun onto the solar cell surfaces and obtain a nominal concentration ratio of 2. The reflector is made of 12.5 pm (0.5 mil) aluminized Kapton. Reflectivity of the reflector was taken at 0.9 BOL and 0.72 EOL. The reflector membrane has a mass of 0.018 kg/m^2 . The reflective membranes are mounted on the structure using attachments and tensioning devices. Tensioning based on structural limit of the existing beam design (with safety factor of 1.5) indicates that tensioning of up to 75 psi can be used. The selected design concept is the 60° Vee trough configuration. The point design solar array sizing allows for 20% reflectivity degradation over 30 years. Figure R-6 presents a cross-sectional view of the satellite.
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