Tokyo Tech Separation Demonstration TSD as M-V Rocket Sub-Payload for Nanosatellite Separation Mechanism
- Paper number
IAC-05-B5.6.A.03
- Author
Mr. Kei Miyamoto, Tokyo Institute of Technology, Japan
- Coauthor
Mr. Kyoichi Ui, Tokyo Institute of Technology, Japan
- Coauthor
Mr. Naoki Miyashita, Tokyo Institute of Technology, Japan
- Coauthor
Mr. Masafumi Iai, Tokyo Institute of Technology, Japan
- Coauthor
Prof. Saburo Matunaga, Tokyo Institute of Technology, Japan
- Coauthor
Mr. Takeshi Usuda, Tokyo Institute of Technology, Japan
- Year
2005
- Abstract
Nano-satellites have received worldwide attention as new technology and science demonstrators as well as space business. For example, CubeSats, 10cm cubic 1kg pico-satellites, are now being developed, launched and operated by many universities and institutes as well as industries around the world, because their small size can make costs less and developing-period shorter. When launching a satellite with a rocket, a separation mechanism is necessary to hold it at liftoff and release into an orbit from the rocket. Nano-satellites are generally piggy-back satellites, and the corresponding separation systems matching interface of the rockets are required to prepare or develop by nano-satellite developers. Thus, Laboratory for Space Systems (LSS) in Tokyo Tech has developed an original separation mechanism for first Tokyo Tech CubeSat “CUTE-I” and resulted in releasing into orbit successfully. LSS is now continuing to research and develop new separation mechanisms for a variety of nano-satellites. LSS got a chance to conduct an experiment using the JAXA/ISAS rocket M-V-6 scheduled to launch in early summer 2005. We use a space for a balance weight to adjust the rocket alignment, so this is called sub-payload. In the experiment, we will conduct a demonstration experiment of a modified separation mechanism matching with the M-V rocket interface, because LSS aims at a launch of the Tokyo Tech second satellite using M-V-8 sub-payload in very near future. In this paper, we describe the modified separation mechanism, the mechanical and electronic interfaces, telemetry simulator to test communications, several functional and environment tests, and flight experiment procedures at launch in detail. Also we will report about the result of on-orbit demonstration experiment used the sub-payload of M-V-6.
- Abstract document
- Manuscript document
IAC-05-B5.6.A.03.pdf (🔒 authorized access only).
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