排序方式: 共有4条查询结果,搜索用时 15 毫秒
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Michihiro Takami Motohide Tamura Keigo Enya Takafumi Ootsubo Misato Fukagawa Mitsuhiko Honda Yoshiko Okamoto Shigehisa Sako Takuya Yamashita Sunao Hasegawa Hirokazu Kataza Hideo Matsuhara Takao Nakagawa Javier R. Goicoechea Kate Isaak Bruce Swinyard 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2010
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Kobayashi Masanori Shibata Hiromi Nogami Ken’ichi Fujii Masayuki Hasegawa Sunao Hirabayashi Masatoshi Hirai Takayuki Iwai Takeo Kimura Hiroshi Miyachi Takashi Nakamura Maki Ohashi Hideo Sasaki Sho Takechi Seiji Yano Hajime Krüger Harald Lohse Ann-Kathrin Srama Ralf Strub Peter Grün Eberhard 《Space Science Reviews》2020,216(8):1-49
Space Science Reviews - In this chapter, we review the contribution of space missions to the determination of the elemental and isotopic composition of Earth, Moon and the terrestrial planets, with... 相似文献
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Honoka Tomizaki Ryohei Kobayashi Mayumi Suzuki Nanami Karasawa Sunao Hasegawa Kanjuro Makihara 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2021,67(5):1526-1534
Deorbit methods have been employed to remove space debris from orbit. One of these methods is to utilize atmospheric drag. In this method, a membrane loaded into the spacecraft is expanded to increase atmospheric drag. Although this method works without requiring fuel, it has the disadvantage of a high risk of collision with other debris owing to its larger area. Area-time product and energy-to-mass ratio have been used as indices to evaluate the risk of collisions between spacecraft and debris. However, the evaluation criteria were uncertain because these two indices are independent. In this paper, we propose a new evaluation index, single-sheet collision factor (SSCF), that comprehensively evaluates the collision risk based on experiments simulating debris collisions. As a result of the hypervelocity collision experiment, we found that the penetration-area mass of the spacecraft affects the severity of debris collisions. In this paper, the product of the exterior-wall thickness, the exterior-wall density, and the space debris cross-sectional area defines the penetration-area mass of the spacecraft. Furthermore, we compare and evaluate various deorbit methods using SSCF. The comparison showed that the penetration-area mass of the SSCF could be quantitatively determined for the debris-collision severity due to difference in structural materials of spacecraft. SSCF will be used to create rules for space-environment conservation with the expansion of the space-development market. 相似文献
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Akira Fujiwara Naomi Onose Masato Setoh Akiko M. Nakamura Kensuke Hiraoka Sunao Hasegawa Kyoko Okudaira 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2014
The cylindrical column of brittle material processed from soil and rock is a fundamental component of architectures on the surface of solid bodies in the solar system. One of the most hazardous events for the structure is damaging by hypervelocity impacts by meteoroids and debris. In such a background, cylindrical columns made of plaster of Paris and glass-bead-sintered ceramic were impacted by spherical projectiles of nylon, glass, and steel at velocity of about 1–4.5 km/s. Measured crater radii, depth, and excavated mass expressed by a function of the cylinder radius are similar irrespective of the target material, if those parameters are normalized by appropriate parameters of the crater produced on the flat-surface target. The empirical scaling relations of the normalized crater radii and depth are provided. Using them, crater dimensions and excavated mass of crater on cylindrical surface of any radius can be predicted from the existing knowledge of those for flat surface. Recommendation for the minimum diameter of a cylinder so as to resist against a given impact is provided. 相似文献
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