Title: A preliminary concept of main structures of the 10 MW SPS Source: Proceedings of the Second ISAS Space Energy Symposium, Institute of Space & Astronautical Science, 4-6-1 Komaba, Meguro-ku, Tokyo 153, Japan, Dec. 13-14, 1982. (Paper No. 11-5) Authors: Nagatomo, Makoto; < Institute of Space and Astronaut i cal Science)- and Sakai, Yoshinori; Matsuzaki, Yoshio; Kato, Sumio; <Kawasaki Heavy Industries, Ltd. > Date: 12-13-82 Classification: u Keywords: structure and design, prototype systems Abstract: A concept of the main structure of the 10 MW SPS Experimental Satellite is described. The structure is a rather conventional truss structure made of carbon fibre reinforced polysalfone resin. The mechanical characteristics of the structure, production of the truss beam and construction ATTACHMENT : procedures have been discussed. Title: Cryogenic power distribution in SPS Source: Proceedings of the Second ISAS Space Energy Symposium, Institute of Space & Astronautical Science, 4-6-1 Komaba, Meguro-ku, Tokyo 153, Japan, Dec. 13-14, 1982. (Paper No. II-6) Authors: Kudo, Isao; Ishii, Itaru; Kimura, Yoichi; <E1ectrotechnical Laboratory) and Higuchi, Noboru; <Brookhaven National Laboratory) Date: 12-13-82 Classification: u Keywords: onboard power storage and distribution Abstract: Application of superconducting cables for power distribution of a space power station is considered. It is found that low voltage DC superconducting power distribution subsystem is feasible for a giant power station. Title: Electric propulsion system for orbital transfer Source: Proceedings of the Second ISAS Space Energy Symposium, Institute of Space & Astronautical Science, 4-6-1 Komaba, Meguro-ku, Tokyo 153, Japan, Dec. 13-14, 1982. (Paper No. 11-9) Authors: Kuriki, Kyoichi; <Institute of Spate and Astronautical Science) and Sasao, Yoshio; Kondo, Yoshiro; <Ishikawajima-Harima Heavy Industries Co.,Ltd.> Date: 12-13-82 Classification: u Keyword s: tr an sp or t at ion Abstract: In order to transfer a SPS from LEO to GEO, the electric propulsion system has been studied. The study was foremost on the influence of specific impulse (Isp) and thrust level on the payload weight. The results from the study indicated that Magneto Plasma Dynamic (MPD) Arcjet was a favorable ATTACHMENT : candidate and therefore the following study was focused on the MPD propulsion system. The MPD arc jet can use a variety of propellants and its performance was evaluated with respect to each propellant.
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