Metallurgical Abstracts on Light Metals and Alloys vol.55
Effects of Temperature on Ejecta from UHMwPE Fiber Composites/Aluminum Alloy Plates
Daichi Kimura*, Masahiro Nishida* and Yukihiro Nomura**
*Department of Electrical and Mechanical Engineering, Nagoya Institute of Technology
**Toyobo Co.
[Published in Proceeding of 33rd International Symposium on Space Technology and Science (33rd ISTS), (2022), paper No. 2022–r–21p]
https://archive.ists.ne.jp/upload_pdf/PO-46.pdf
E-mail: nishida.masahiro[at]nitech.ac.jp
Key Words: Space debris, Impact behavior, Temperature effects
The number of space debris increases year by year. The average impact velocity of space debris is approximately 10 km/s in the low Earth orbit. When space debris strike spacecraft at the high velocities, ejecta (fragments) from spacecraft are generated and widely spread in the low Earth orbit. In this study, at first the effects of the high velocities on crater and ejecta from aluminum alloy 6061-T6 plates and the effects of temperature (room temperature and 100°C) were examined. For the purpose of further reduction of ejecta, a plastic sheet (UHMwPE fiber composite) were employed for decreasing ejecta from aluminum alloy plates.
When spherical projectile struck aluminum alloy plates at 2 km/s, temperature only slightly affected crater size and ejecta distribution. Lip size related to elongation were small at the high velocities as well as results of static tensile tests. Crate size on the surface of aluminum alloy plate clearly decreased and the number of ejecta only slightly decreased by the addition of plastic sheet.
The temperature increasing of 100°C slightly affect crate size and the number of ejecta from aluminum alloy 6-61-T6 at hypervelocity impact. They were slightly decreased by the addition of plastic sheet.