System design of multipurpose reusable orbiter suitable for small launch vehicle
- Paper number
IAC-19,D2,3,8,x51553
- Author
Mr. Ryoma Yamashiro, Japan, Japan Aerospace Exploration Agency (JAXA)
- Coauthor
Dr. Shinichiro Tokudome, Japan, Japan Aerospace Exploration Agency (JAXA)
- Coauthor
Dr. Kazuhiko Yamada, Japan, Japan Aerospace Exploration Agency (JAXA)
- Coauthor
Mr. Takayuki Imoto, Japan, Japan Aerospace Exploration Agency (JAXA)
- Year
2019
- Abstract
Many small launch vehicles are being developed and operated to meet the explosively increasing demand for small satellites. Taking this opportunity, we are studying a multipurpose reusable orbiter to be launched by a small launch vehicle. Such orbiter will add further value to small missions and promote space utilization. In this paper, we report the results of the system investigation on a 1.5-ton class reusable orbiter to be launched by the Epsilon Launch Vehicle and then return to the sea after performing its mission in orbit. Generally, mass design for a reusable orbiter is difficult because it needs a propulsion system for deceleration to reentry speed and a TPS (Thermal Protection System) required for reentry. Additionally, a conventional reusable TPS has a downside in operational performance as demonstrated by the Space Shuttle. In order to solve these problems, we conducted a trade-off study of propellant and evaluated the application of our innovative aeroshell system based on its sub-size flight test. These results are also included in this paper.
- Abstract document
- Manuscript document
IAC-19,D2,3,8,x51553.pdf (🔒 authorized access only).
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