PBS: Post-Boost Stage JAXA

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1 morita.yasuhiro@jaxa.jp F

2 PBS: Post-Boost Stage JAXA

3 IT IT 3 2 JAXA

4 C/C SRB-A H2A M-V H2A PBS 24 m/2.5 m 92 ton LEO km : 1.2 ton SSO 500 km : 450 kg USC

5 3 M-V M-V 1 SRB-A 2 3 M-V3 CFRP M-VH2A/B Responsive Operation Support Equipment; ROSE 2Launch Control System; LSC ROSE HUB

6 ROSE ROSE ROSE MT 2 M-V MIDLEE PBS

7 2 500 km PBS km km PBS 2 M-V PBS SRB-A 50 Hz PAF PAF M-VM-V H 1214 NASA 50 m CFD 12 m

8 5 FT DOL DR

9 3 4 3 PBS 26 m/2.5 m TBD TBD 95 ton 200 km km : 365 kg TBD SSO 500 km : 600 kg TBD TBD CFRP CPU TBD USC RINA H2A

10 JAXA M-V H-IIA CFRP

11 9 CFRP CFRP PBS CFRP LTP JAXA 20 X

12 Morita Y., Imoto T., Ohtsuka H., 2010, Development of Japan s Next Generation Solid Rocket Launcher the Epsilon Rocket, 61st Congress of the International Astronautical Federation IAC Prague, Czech Republic 5 Morita Y., Imoto T., Tokudome S., Ohtsuka H., 2013, First Launch in Months: Japan s Epsilon Launcher and Its Evolution, 29th International Symposium on Space Technology and Science ISTS Nagoya, Japan 6 Morita Y., Imoto T., Tokudome S., Ohtsuka H., 2011, Development Status of Japan s Epsilon Solid Rocket Launcher and Its Evolution, 62nd Congress of the International Astronautical Federation IAC Capetown, SA Morita Y., Imoto T., Ohtsuka H., 2012, A Year to Launch: Japan s Epsilon Launcher and Its Evolution, 63rd Congress of the International Astronautical Federation IAC, Naples, Italy Tanaka K., Otsuka H., Saito K., Tamura T., Ishii N., Maeda Y., Morita Y., 2009, PBS Post Boost Stage Design of the Advanced Solid Rocket, 27th International Symposium on Space Technology and Science ISTS, Tsukuba, Japan 12 Morita Y., 2011, On the Guidance and Control System of Epsilon Solid Rocket Launcher, Proceedings of the 21st Workshop on Astrodynamics and Flight Mechanics, ISAS 13 Morita Y., 2012, ROBUST CONTROL OF THE AD- VANCED SOLID ROCKET LAUNCHER, First IAA Conference on Dynamics and Control of Space Sys

, Tokudome S., Ohtsuka H., 2013, First Launch in Months: Japan s Epsilon Launcher and Its Evolution, 29th International Symposium on Space Technology and Science ISTS Nagoya, Japan 6 Morita Y.

13 tems DyCoSS1, Porto, Portugal 14 Ohtsuka H., Tanaka K., Morita Y., Tamura M., 2012, The Responsive and Mobile Concept of Guidance & Control System of Epsilon Rocket, 13th International Space Conference of Pacific Basin Societies ISCOPS, Kyoto, Japan 15 Morita Y., Imoto T., Tokudome S., Ohtsuka H., 2011, Epsilon Rocket Launcher and Future Solid Rocket Technologies, 28th International Symposium on Space Technology and Science ISTS, Okinawa, Japan, JAXA 17 Morita Y., Hori K., Imoto T., Ohtsuka H., Fukuchi A., Akiba R., 2010, Advanced Solid Rocket Launcher and beyond, 12th International Space Conference of Pacific Basin Societies ISCOPS Montreal, Canada, 2010/Advances in the Astronautical Sciences, American Astronautical Society, Washington, D.C. 18 JAXA, IA HASTIC, 2012, Morita Y., 2010, Advanced Solid Rocket Propellant for Cost Effective Launchers, IAA 50th Anniversary Celebration Symposium, Nagoya, Japan 21 Hori K., Tsutsumi A., Morita Y., Akiba R., Hasegawa H., Sasaki K., Kato N., 2011, A Study on Low Melting Point Thermoplastic Solid Propellant, 28th International Symposium on Space Technology and Science ISTS, Okinawa, Japan First Flight Results of the Epsilon Launch Vehicle and Its Evolution Plan Yasuhiro Morita JAXA, Japan, Yoshinodai, Chuo-ku, Sagamihara , Japan Abstract: The Epsilon launch vehicle successfully had its first flight in September 14, 2013, carrying HISA- KI, the world first extreme ultra-violet planetary telescope satellite, onboard. The purpose of the Epsilon rocket is to provide small satellites with a responsive launch, which means a cost effective, user friendly and ultimately efficient launch system. To realize this, the design concept of the Epsilon involves various innovative next generation technologies: highly intelligent mobile launch control and the enhanced user-friendly characteristics. This paper deals with the first flight results of the Epsilon launch vehicle and its evolution plan

36 581/2 2012

36 581/2 2012 4 Development of Optical Ground Station System 4-1 Overview of Optical Ground Station with 1.5 m Diameter KUNIMORI Hiroo, TOYOSHMA Morio, and TAKAYAMA Yoshihisa The OICETS experiment, LEO Satellite-Ground