Japan SPS - Reference System Concept: Update of U.S. Reference system, using modem design and materials Key Features: Silicon Planar SPS Solid State Phased Arrays Floating Raft Rectenna Suggestor/Source: Mitsubishi Research Institute (study coordinator for MITI, NEDO) Discussion This design was the result of a three year feasibility study ocurring in 1990-93, done at the behest of MITI through the agency of the Mitsubishi Research Institute and under the auspices of NEDO. The design selected was essentially a 1 GW (delivered to grid) version of the NASA reference design. Although when initially briefed by MITI in early 1994, the scenario proposed using klystrons as the RF generators, the final design as briefed by Dr. Kudo in late 1995 uses solid state phased arrays. The SPS uses an AC power distribution system derived from US space station design work at LeRC. The large coin-silver slip ring is replaced by a magnetic coupling system, (not defined to our knowledge in any English language report as of yet). The proposition is that components would /be launched using an SSTO from a Pacific Ocean island spaceport and the SPS constnicted in LEO with the Solar Arrays wrapped around the central antenna structure. The entire unit is then moved to GEO via electric propulsion. The Earth to Orbit transportation system is an SSTO with at GLOW of 1800 tons. Payload is 50 tons and propellant is 1600 tons. References 1. Mitsubislii Research Institute, “Feasibility Study on Solar Power Satellites,” 1994. (in Japanese) 2. Maryniak, G., “Preliminary Report on WPT '95,” Futron Corporation Bethesda, MD, 1995. Advantages Disadvantages 1 GW to grid power level is more appropriate to market needs than the US Reference case of 5 GW to grid Designed for high degree of deployment automation Higher specific mass than US reference Requires advancements in solid-state phased arrays.
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