reducing to 1 mW/cm at the perimeter of the rectenna is compatible with present environmental limit as stated in the program guidelines. I. Mass Statement A summary of the satellite mass properties is presented in Table R-5. The two major segments, the collector array and the antenna section, are nearly equal in mass. The major contributor to the collector array mass is the power source, which includes the solar blanket and the concentrators. The solar blanket is the predominant mass. Antenna section mass properties are driven by the microwave power segment which includes the RF radiators and the klystrons. Total satellite mass, including a 25-percent mass growth factor, is 38.09-mil1 ion kilograms. Propellant resupply for attitude control and stationkeeping is a very small annual mass compared to the satellite mass. J. Space Transportation The transportation system operational regimes include earth to LEO, LEO to GEO, and on-orbit (for short distance and duration flight). These systems must be capable of transporting both crew and cargo. HLLV - SPS transportation requirements from earth to LEO, environmental factors, element of risk and operations complexity and cost led to the selection of two HLLV concepts; a winged two-stage vertical takeoff-horizontal landing configuration (VTO) and a more advanced technology option; an HTO-SSTO configuration . Winged VTO-HLLV - A potential HLLV candidate with equal size (volume) stages is depicted in Figure R-22. The vehicle is a parallel burn configuration with propellant crossfeed from the 1st to 2nd stage and is capable of placing a 225 x 106 kg payload in an orbit of 500 km at an inclination of 28.5°. Both stages have fly-back capability; the 1st stage only employs air breathing engines. The boost phase uses LOX/RP in both stage engines. The 2nd stage employs
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