A Concept of a Reusable Sounding Rocket
- Paper number
IAC-05-D2.4.08
- Author
Dr. Hiroyuki Ogawa, Japan Aerospace Exploration Agency (JAXA)/ISAS, Japan
- Coauthor
Dr. Yoshihiro Naruo, Japan Aerospace Exploration Agency (JAXA)/ISAS, Japan
- Coauthor
Dr. Satoshi Nonaka, Japan Aerospace Exploration Agency (JAXA)/ISAS, Japan
- Coauthor
Prof. Yoshifumi Inatani, Japanese Rocket Society, Japan
- Year
2005
- Abstract
A baseline system of a reusable sounding rocket conducted in ISAS (Institute of Space and Astronautical Science) / JAXA (Japan Aerospace Exploration Agency) is presented. The vehicle adopts a vertical take-off and vertical landing (VTVL) system to minimize ground support equipments (GSE) and turn-around time. An integrated propulsion system which consists of four 2-ton-class liquid-hydrogen / liquid-oxygen (LH2/LOX) expander cycle engines, a gaseous-hydrogen / gaseous-oxygen (GH2/GOX) reaction control system (RCS) and an auxiliary power unit (APU) are introduced to simplify ground operations. The vehicle is designed to meet the requirements of carrying 100kg payload on a round trip to 100km and repeating the mission within 24 hours. The airframe shape is basically axisymmetric; wings are excluded or minimum. The two ways of descent, i.e., nose-forward and base-forward descents, are discussed according to the vehicle system requirements. Since the downrange requirement is not met for the base-forward descent, the nose-forward descent is adopted.
- Abstract document
- Manuscript document
IAC-05-D2.4.08.pdf (🔒 authorized access only).
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