2. BOEING AEROSPACE COMPANY The following is a description of the SPS concept produced by the Boeing Aerospace Company under contract to the NASA Johnson Space Center. A. Guidelines and Assumptions The guidelines and assumptions for this study were essentially the same as for the Reference System. The only exception is that the SPS size is 10 GW using two 5 GW ground power output microwave transmission and reception systems. B. System Overview Figure B-l shows the satellite configuration, which is a photovoltaic SPS without solar concentrators employing glass-encapsulated, single crystal silicon solar cells. The nominal ground output is 10 GW through two microwave power transmission links each rated at 5 GW. A summary of the nominal efficiency chain for this concept is presented in Table B-l. The satellite microwave antenna employs klystron microwave generators, a Gaussian power distribution and a 2 maximum power density at the rectenna of 23 mw/cm . The rectenna land area, 2 without a buffer zone, in 100 km . The satellite is constructed at low earth orbit in 8 elements employing a crew of approximately 500. The satellite elements are transferred to geosynchronous orbit using electric thrusters powered by partially deployed SPS solar arrays. Elements of the approximately 100,000 metric ton SPS are launched into low earth orbit by 2-staged, winged, land-landing heavy lift launch vehicles, each with a 400 metric ton payload. Kennedy Space Center was assumed as the reference launch complex, pending further study. Configuration - As illustrated in figure B-l, the configuration is a 2 simple planar structure supporting approximately 102 km of solar arrays. The solar blanket is divided into 256 bays, each 667.5 meters square. The bays are grouped into eight modules each having four by eight bays. A 1000-meter diameter transmitter antenna is located at each end of the 5300 m X 21280 m solar
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