タイトル（掲載誌）航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-1082
一般注記Experimental regeneratively cooled bipropellant engines, with a vacuum thrust of 2000N at a chamber pressure of 0.98 MPa and an area ratio of 240:1, were fired with hydrazine-MMH mixed fuels to evaluate potential performance and cooling improvement. Regeneratively cooled engine tests were conducted with 80％ hydrazine-20％ MMH mixed fuels as well as with MMH single fuel, utilizing optimized injectors for each fuel. The chamber pressure was varied in a range from 0.6 to 0.9 MPa. Long duration firing tests of 160s were conducted to evaluate heat soak back level and demonstrate safe shutdowns of a mixed fuel regeneratively cooled engine. The peak specific impulses of the mixed fuel was more than 322s, while that of MMH was 308s. Regenerative cooling with the mixed fuel seemed to be particularly advantageous in that the temperature increase through the cooling channels was smaller than that of MMH; this reduced performance degradation due to reactive stream separation(′blow apart′) at higher chamber pressures. No indication of explosion in the coolant channels or manifolds at engine shutdown was observed during long firing tests of the improved chamber.
資料番号: NALTR1082000
レポート番号: NAL TR-1082
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=45341&item_no=1&attribute_id=31&file_no=1
連携機関・データベース国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
提供元機関・データベース宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ