A high energy propel 1 ant composition which had 150 mm/sec of burning rate ATTACHMENT : was developed successfully from the results of this study. Titles Development of Japanese RJ-1 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. 1-3) Authors: Miyata, Mafumi; Horiuchi, Setsui; Kato, Akira; Izumita, Masayuki; ^National Space Development Agency of Japan/ and Iwamuro, Takeyo; Fuji so, Tokuo; '(Nippon Oil Co. > and Hirooka, Seiji; <Nippon Petrochemical Co.> Date: 12-13-82 Classification: u K eywor d s: t r a n s p o r t a t i o n Abstract: RJ-1 is a rocket fuel used for the first stage of the current N series launch vehicle. It will also be used for the future H-I vehicle. This propellant is now imported from Shell Oil Company of the United States. The National Space Development Agency of Japan (NASDA) has been conducting ATTACHMENT : development work for the domestic production of RJ-1 to guarentee the source of supply in the event that a U.S. supplier stops production of this propellant in the future. Title: Ignition and flame propagatoin in cryogenic oxyhydrogen mixtures 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. 1-4) Authors: Fujiwara, Toshitaka; Nakata, Yasushi; Sasaki, Yasuhiko; Akiyama, Katsuhiko; -^Department of Aeronautical Engineering, Nagoya University, Nagoya 464, Japan> Date: 12-13-82 Classification: u Keywords: transportation Abstract: The present preliminary experiment was performed to yield the reasonable minimum ignition energy of oxyhydrogen mixtures at cryogenic conditions. At temperatures about 100 K, the minimum ignition energy was 0.1 mJ for an equi-molar oxyhydrogen at p(0)=260 torr. Simultaneously, numerical ATTACHMENT : analysis was also done to simulate the ignition and subsequent flame propagation in a two-dimensional constant-volume reaction chamber. Title: Development of NASDA solid rocket motorSource: 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. 1-5) Authors: Saito, Norio; Sano, Noboru; Eguchi, Akihiro; Takahashi, Michio; <National Space Development Agency of Japan (NASDA)> Date: 12-13-82 Classification: u Keywords: transportation
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