subsystems including energy conversion, power distribution, attitude control and stationkeeping, and antenna. Energy conversion Figure 6 shows the configuration of the SPS point design solar array wing structure. The concept is a coplanar, three-trough system. The structure is made up of tri-beam girders whose longitudinal members and transverse struts are fabricated on orbit by a beam machine. Shear stabilization of the tri-beam girders and the wing itself is achieved by the use of X-tension cables. Current structure material is composites. The dimensions indicated have been verified to be adequate when the vehicle is subjected to a worst-case forces and torques environment in geosynchronous orbit. Figure 7 shows the solar array blanket description and array characteristics. The point design utilizes a GaAlAs solar cell efficiency of 20% AMO, 28°C, and the sizing of the array is based on 113°C operating temperature (17.6% cell efficiency). The total output of the array is 9.94 GW with a voltage output of 45.7 kV for each array panel. The solar blanket weight is 7.41 x 10® kg, and the total array weight (including Table 2. Satellite Mass Summary Table 1. Recommended Satellite Concept Description
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