operational orbit of 1,400 km, sun-synchronous, at a transmitted RF power level sufficient to produce a 50 MW output from a ground-based planar rectenna. Total beam-steering capability is 60 degrees (+ 30 degrees). A single transmitting ‘element’ is therefore projected to be a hexagonal surface less than 4 cm in ‘diameter’, with a nominal 12.5 W input power level @ 80% conversion efficiency yielding an output of about 10W. These elements are pre-integrated into ‘sub-assemblies’ for final assembly on orbit. For 50 MW transmitted RF power, the transmitter array is an ‘element and sub-assembly -tiled plane’ that is essentially circular, approximately 106 meters in diameter, with a Fractal matrix power distribution grid on the backplane, totaling approximately 1.0 meters in thickness. For the MEO-based Sun Tower concept, the operational orbit is about 6,000 km inclined 30-50 degrees, and its transmitted power is greater, producing 250 MW at the ground she. Using the same 5.8 GHZ, 10 W transmitting devices as above, with similar beam-steering capability, the transmitter array for this system would have a diameter of approximately 260 meters. “SUN TOWER” SPACE SOLAR POWER — MEO CONCEPT Figure 3-3 The Sun Tower SSP Space Segment Concept Sunlight-to-electrical power conversion must be modular and deployable in “units” approximately 75 meters in diameter with a net 1.3 MW electrical output (approximately). The primary technology option is a gossamer-structure based reflector with non-dynamic conversion at the focus (e.g., advanced PV); this reference is subject to trade studies. These collection systems are presumed to be always sun-facing (with the system in a sun-synchronous orbh) and to be attached regularly in pairs along the length of a structural/power transmitting tether to the back-plane of the transmitter array. Heat rejection for power conversion and conditioning systems is assumed to be modular and integrated with power conversion systems. With the Sun Towers in an inclined MEO orbit, the collection systems must be capable of rotating (nodding) along a single axis while the satellite maintains a continuous one rotation per orbit roll maneuver to maintain constant sun-track.
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