F-1505 宇宙機用途のセラミックス基複合材料の開発(S54-2 耐熱材料・耐熱構造(2))(S54 耐熱材料・耐熱構造)

概要

論文の詳細を見る
Ceramic Matrix Composite (CMC) is one of the candidates for thermal protection materials of space re-entry vehicles. In order to fix the fabricating process, some mechanical tests were performed on CMCs, which made by various process conditions, before and after thermal exposure simulating re-entry conditions. In comparison with the change of mechanical properties with process conditions by thermal exposure, it was confirmed that interface treatment (CVI-C/SiC) between SiC fiber and SiC matrix and several repeating of densification process (PIP) were required for CMCs using for thermal protection materials. Trial parts have also been fabricated successfully in the shape of a leading edge and TPS curved panel with the high accuracy by the fabricating process using the conditions selected above.
一般社団法人日本機械学会の論文
2001-08-22