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titleSPSデブリシールド開発のための超高速度斜め衝突実験
Other TitleOblique hypervelocity impact experiment on debris shield for solar power satellite
Author(jpn)上山, 潤; 田中, 孝治; 塩田, 一路; 佐々木, 進
Author(eng)Ueyama, Jun; Tanaka, Koji; Shiota, Ichiro; Sasaki, Susumu
Author Affiliation(jpn)工学院大学; 宇宙航空研究開発機構宇宙科学研究本部; 工学院大学; 宇宙航空研究開発機構宇宙科学研究本部
Author Affiliation(eng)Kogakuin University; Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS); Kogakuin University; Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)
Issue Date2009-06
PublisherInstitute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)
宇宙航空研究開発機構宇宙科学研究本部
Publication titleSpace Energy Symposium
宇宙エネルギーシンポジウム
Volume28
Publication date2009-06
Languagejpn
eng
AbstractSpace dusts, such as natural meteoroids or man made orbiting debris, are recognized as a serious and growing threat to man's utilization and exploration of space. Debris larger than 10 cm in diameter is detected by ground based radars and optical observations. But it is impossible to detect debris smaller than 10 cm by ground-based observations using existing technologies. Typical debris impacts are thought to occur at a velocity of around 10 km/s. Shiota proposed a new concept on the debris protection system applying a principle of the ducks and drakes for the large space craft or the solar power satellite. We have carried out the experiments for the research on the oblique hyper velocity impact experiment using several materials. Especially, we have interests in the CFRP materials that have unique anisotropic properties. A two stage light gas gun was used. Ejectors were monitored by the high speed video camera and the shielding plate. The experiment chamber consists of an impact section with a viewing port and several feed-through flanges. The chamber is evacuated to several ten Pa using the vacuum pump system. Typical velocity of the projectile for our experiments was about 4 km/s. The projectile is made of aluminum with a diameter of around 1 mm and a weight of around 0.004 g. We confirmed recoiled conditions of the projectile, and observed breakdown phenomena of the CFRP plate for the several incident angles.
Description会議情報: 第28回宇宙エネルギーシンポジウム(2009年3月9日, 宇宙航空研究開発機構宇宙科学研究本部相模原キャンパス)
Meeting Information: The twenty-eight Space Energy Symposium (March 9, 2009. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, Sagamihara)
Document TypeConference Paper
JAXA Categoryシンポジウム・研究会
NCIDAN10324356
SHI-NOAA0064295018
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/14672


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