A sail deployment mechanism for active prevention and reduction of space debries

Toshinori Kuwahara, Kazuya Yoshida, Yuji Sakamoto, Yoshihiro Tomioka, Kazufumi Fukuda, Yuta Tanabe, Masato Fukuyama

研究成果: Conference contribution

2 被引用数 (Scopus)

抄録

Recently small satellite development activities became popular throughout the world and the number of satellites being developed and launched a year is becoming larger. Many of these satellites are launched into orbits where they remain orbiting around the Earth for centuries in vain even after their mission life time. It became recently a world's serious concern that these space debris prevent human beings from safe space development and exploration activities in the near future. Therefore there is a great interest on debris prevention and reduction methods. Tohoku University has been very active in satellite development activities for years and has already successfully developed, tested, and launched its first microsatellite SPRITE-SAT (renamed as RISING-1 after the launch) in 2009, and is completing the second microsatellite RISING-2. Due to the above mentioned background, Tohoku University has also initiated a development activity of sail deployment mechanisms in order to de-orbit the used microsatellite mainly by means of the residual atmospheric drags. The mechanism itself has a cylinder form and utilizes unique deployable booms which can be folded down very compactly. The stored thin film inside the mechanism is pulled out of the case by the deployment force produced by the booms. The engineering model of this mechanism is now under development, which exemplary has a diameter of 20 cm, a thickness of 5cm, and a mass of about 0.5 kg for deploying a 1.5 m square thin film. This size is meant to be sufficient for de-orbiting of the second microsatellite RISING-2 with a mass of about 41kg within 25 years. It is estimated that the volume of the mechanism can be reduced down to 2/3 for the flight model. The third microsatellite RISESAT with a mass of about 50 kg is planned to be equipped with a 4.5 m square sail. The important characteristic of this mechanism is that the size of the sail can be modified very easily depending on the requirements of the spacecraft. Preparing deferent size of sails, this kind of de-orbit mechanism can become the standard prevention and reduction measures of space debris. This paper describes the basic idea of this sail deployment mechanism, the results of initial functional verification of the test model, and proposes an efficient way of space debris mitigation for future space activities.

本文言語English
ホスト出版物のタイトル62nd International Astronautical Congress 2011, IAC 2011
ページ2178-2184
ページ数7
出版ステータスPublished - 2011 12 1
イベント62nd International Astronautical Congress 2011, IAC 2011 - Cape Town, South Africa
継続期間: 2011 10 32011 10 7

出版物シリーズ

名前62nd International Astronautical Congress 2011, IAC 2011
3

Other

Other62nd International Astronautical Congress 2011, IAC 2011
CountrySouth Africa
CityCape Town
Period11/10/311/10/7

ASJC Scopus subject areas

  • Aerospace Engineering

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