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Tetsuya Yoshida Daisuke Akita Hideyuki Fuke Akira Kadokura Jiro Kawada Tomomi Kawasaki Issei Ijima Naoki Izutsu Yukihiko Matsuzaka Eiichi Mizuta Michiyoshi Namiki Naoki Nonaka Shigeo Ohta Yoshitaka Saito Motoharu Seo Michihiko Toriumi Kazuhiko Yamada Takamasa Yamagami 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2008
The Scientific Balloon Center of ISAS/JAXA has carried out two balloon campaigns at Sanriku, Iwate, Japan every year. Ten to twelve balloon vehicles are launched annually for scientific and engineering experiments. Since 2005, a Brazilian balloon campaign has also been conducted in cooperation with INPE. In the 2006 Brazilian campaign, large and heavy payloads up to 1500 kg for astronomy will be launched. New generation balloons, such as super-pressure balloons and high-altitude balloons with ultra-thin films, are being developed. The current status and prospect of the Japanese scientific ballooning are discussed. 相似文献
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H. Fuke N. Izutsu D. Akita I. Iijima Y. Kato J. Kawada K. Matsushima Y. Matsuzaka E. Mizuta M. Namiki N. Nonaka S. Ohta Y. Saito T. Sato M. Seo Y. Shoji A. Takada K. Tamura M. Toriumi K. Yamada T. Yamagami T. Yoshida 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2011
The super-pressure balloon (SPB) has been expected to be a flight vehicle that can provide a long flight duration to science. Since 1997, we have developed the SPB. Now we are at the phase of developing an SPB of a practical size. In 2009, we carried out a test flight of a pumpkin-shaped SPB with a 60,000 m3 volume. The undesirable result of this flight aroused us to resolve the deployment instability of the pumpkin-shaped SPB, which has been known as one of the most challenging issues confronting SPB development. To explore this deployment issue, in 2010, we carried out a series of ground tests. From results of these tests, we found that an SPB design modified from pumpkin, named “tawara”, can be a good candidate to greatly improve the deployment stability of the lobed SPB. 相似文献
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Y. Saito D. Akita H. Fuke I. Iijima N. Izutsu Y. Kato J. Kawada Y. Matsuzaka E. Mizuta M. Namiki N. Nonaka S. Ohta T. Sato M. Seo A. Takada K. Tamura M. Toriumi T. Yamagami K. Yamada T. Yoshida K. Matsushima S. Tanaka 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2012
Development of a balloon to fly at higher altitudes is one of the most attractive challenges for scientific balloon technologies. After reaching the highest balloon altitude of 53.0 km using the 3.4 μm film in 2002, a thinner balloon film with a thickness of 2.8 μm was developed. A 5000 m3 balloon made with this film was launched successfully in 2004. However, three 60,000 m3 balloons with the same film launched in 2005, 2006, and 2007, failed during ascent. The mechanical properties of the 2.8 μm film were investigated intensively to look for degradation of the ultimate strength and its elongation as compared to the other thicker balloon films. The requirement of the balloon film was also studied using an empirical and a physical model assuming an axis-symmetrical balloon shape and the static pressure. It was found that the film was strong enough. A stress due to the dynamic pressure by the wind shear is considered as the possible reason for the unsuccessful flights. A 80,000 m3 balloon with cap films covering 9 m from the balloon top will be launch in 2011 to test the appropriateness of this reinforcement. 相似文献
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K. Enya T. Kotani K. Haze K. Aono T. Nakagawa H. Matsuhara H. Kataza T. Wada M. Kawada K. Fujiwara M. Mita S. Takeuchi K. Komatsu S. Sakai H. Uchida S. Mitani T. Yamawaki T. Miyata S. Sako T. Nakamura K. Asano T. Yamashita N. Narita T. Matsuo M. Tamura J. Nishikawa E. Kokubo Y. Hayano S. Oya M. Fukagawa H. Shibai N. Baba N. Murakami Y. Itoh M. Honda B. Okamoto S. Ida M. Takami L. Abe O. Guyon P. Bierden T. Yamamuro 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2011
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On 1992 we started the study of 500kg-class satellite mainly for technology demonstration mission which contributes to mitigate the project risk. It goes without saying that this class of satellite is characterized by low cost and fast turn-around-time, but are different from the same class satellites which we'd developed in the '80s.
In this paper, we present the outline of this class of satellites, and focusing to Space Environments and Effects Observation Satellite(SEES) under pre-phase A. A lot of failures which have happened on orbit are caused by space environments. So it is necessary to understand in detail the behavior, and to develop technology to endure them. 相似文献
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