{"created":"2023-06-20T15:11:33.645617+00:00","id":41240,"links":{},"metadata":{"_buckets":{"deposit":"b452c671-46be-483a-8347-91b1fb0b9749"},"_deposit":{"created_by":1,"id":"41240","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"41240"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00041240","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["451414","451405","451419","451408","451407","451418","451412","451413","451417","451415","451406","451409","451411","451410","451416","451404"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Application of C/C composites to the combustion chamber of rocket engines. Part 1: Heating tests of C/C composites with high temperature combustion gases"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1995-04","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"15","bibliographicPageStart":"1","bibliographicVolumeNumber":"1264","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所報告"},{"bibliographic_title":"Technical Report of National Aerospace Laboratory","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"炭素繊維強化炭素複合材は、炭素繊維で強化された炭素複合材であり、比重が約2と非常に小さく、1800K以上ではあらゆる耐熱材料の中でも最も高い比強度を有し、しかもその強度を2300K以上まで保持するという、すぐれた特性を有する材料である。このため、熱的、強度的に厳しい環境での軽量構造部材として宇宙往還機のノーズコーンや機体の構造材、そしてロケット燃焼器などへの応用も検討されている。しかし、C/C材単体では高温酸化し、使用環境が限られるためセラミックなどの耐酸化コーティングが必要となる。耐酸化コーティングにあたってはC/C材とセラミックコーティング材の熱膨張率の大きな差異から、コーティング層に亀裂や剥離が生じる問題がある。本研究の目的は、C/C材を貯蔵性2液推進剤用ロケット燃焼器に適用することである。C/C材をロケット燃焼器に適用するためには、燃焼器としての気密性、コーティング層の耐熱、耐食性、噴射器との接合などの問題がある。そこで本報では、耐熱、耐食性の評価を主目的とし、5種類の直径30mmC/C材円板にSiCをコーティングした供試体を製作し、貯蔵性2液推進剤(NTO/MMH)を用いて発生させた燃焼ガスで、供試体を繰返し加熱する評価試験を行なった。その結果、従来型の供試体に比べマトリックス改質型、傾斜機能コーティング型供試体が耐熱、耐食性の向上に有効であることが示された。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Carbon fiber reinforced carbon composite (C/C composite) has various superior properties, such as high specific strength, specific modulus, and fracture strength at high temperatures of more than 1800 K. Therefore, C/C composite is expected to be useful for many structural materials, such as combustion chamber of rocket engines and nose-cone of space-planes, but C/C composite lacks oxidation resistivity in high temperature environments. To meet the lifespan requirement for thermal barrier coating, ceramic coating has been employed in the hot-gas side wall. However, the main drawback to the use of C/C composite is the tendency for delamination to occur between the coating layer on the hot-gas side and the base materials on the cooling side during repeated thermal heating loads. To improve the thermal properties of the thermal barrier coating, five different types of 30-mm diameter C/C composite specimens constructed with Functionally Gradient Materials (FGMs) and a modified matrix coating layer were fabricated. In this test, these specimens were exposed to the combustion gases of the rocket engine using nitrogen tetroxide (NTO) /monomethyl hydrazine (MMH) to evaluate the properties of thermal and erosive resistance on the thermal barrier coating after the heating test. It was observed that modified matrix and coating with FGMs are effective in improving the thermal properties of C/C composite.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0004271000","subitem_description_type":"Other"}]},"item_3_description_33":{"attribute_name":"レポート番号","attribute_value_mlt":[{"subitem_description":"レポート番号: NAL TR-1264","subitem_description_type":"Other"}]},"item_3_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"航空宇宙技術研究所"}]},"item_3_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"National Aerospace Laboratory (NAL)"}]},"item_3_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0389-4010","subitem_source_identifier_type":"ISSN"}]},"item_3_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"航空宇宙技術研究所 角田宇宙推進技術研究センター"},{"subitem_text_value":"航空宇宙技術研究所 角田宇宙推進技術研究センター"},{"subitem_text_value":"航空宇宙技術研究所 角田宇宙推進技術研究センター"},{"subitem_text_value":"航空宇宙技術研究所 角田宇宙推進技術研究センター"},{"subitem_text_value":"航空宇宙技術研究所 角田宇宙推進技術研究センター"},{"subitem_text_value":"川崎重工業"},{"subitem_text_value":"川崎重工業"},{"subitem_text_value":"日本石油"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuda Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuda Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuda Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuda Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuda Research Center"},{"subitem_text_language":"en","subitem_text_value":"Kawasaki Heavy Industries, Ltd"},{"subitem_text_language":"en","subitem_text_value":"Kawasaki Heavy Industries, Ltd"},{"subitem_text_language":"en","subitem_text_value":"Nippon Oil Company, Ltd"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"只野, 真"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"佐藤, 政裕"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"黒田, 行郎"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"日下, 和夫"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"植田, 修一"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"末光, 毅"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"長谷川, 聰"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"久手, 幸徳"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tadano, Makoto","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Sato, Masahiro","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kuroda, Yukio","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kusaka, Kazuo","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ueda, Shuichi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Suemitsu, Takeshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Hasegawa, Satoshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kude, Yukinori","creatorNameLang":"en"}],"nameIdentifiers":[{}]}]},"item_files":{"attribute_name":"ファイル情報","attribute_type":"file","attribute_value_mlt":[{"accessrole":"open_date","date":[{"dateType":"Available","dateValue":"2020-01-27"}],"displaytype":"detail","filename":"naltr01264.pdf","filesize":[{"value":"3.8 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr01264.pdf","url":"https://jaxa.repo.nii.ac.jp/record/41240/files/naltr01264.pdf"},"version_id":"80379b96-0a31-4eda-b6e5-710322aad25b"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"C/C複合材","subitem_subject_scheme":"Other"},{"subitem_subject":"炭素/炭素複合材","subitem_subject_scheme":"Other"},{"subitem_subject":"FGM被覆","subitem_subject_scheme":"Other"},{"subitem_subject":"機能的傾斜材料被覆","subitem_subject_scheme":"Other"},{"subitem_subject":"改質マトリックス被覆","subitem_subject_scheme":"Other"},{"subitem_subject":"燃焼器","subitem_subject_scheme":"Other"},{"subitem_subject":"ロケットエンジン","subitem_subject_scheme":"Other"},{"subitem_subject":"加熱試験","subitem_subject_scheme":"Other"},{"subitem_subject":"高温燃焼ガス","subitem_subject_scheme":"Other"},{"subitem_subject":"比強度","subitem_subject_scheme":"Other"},{"subitem_subject":"破断強度","subitem_subject_scheme":"Other"},{"subitem_subject":"ノーズコーン","subitem_subject_scheme":"Other"},{"subitem_subject":"耐酸化性","subitem_subject_scheme":"Other"},{"subitem_subject":"セラミックス被覆","subitem_subject_scheme":"Other"},{"subitem_subject":"熱障壁被覆","subitem_subject_scheme":"Other"},{"subitem_subject":"C/C composite","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"carbon/carbon composite","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"FGM coating","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"functionally gradient materials coating","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"modified matrix coating","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"combustor","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"rocket engine","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"heating test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"high temperature combustion gas","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"specific strength","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"fracture strength","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"nose cone","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"oxidation resistivity","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"ceramic coating","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"thermal barrier coating","subitem_subject_language":"en","subitem_subject_scheme":"Other"}]},"item_language":{"attribute_name":"言語","attribute_value_mlt":[{"subitem_language":"jpn"}]},"item_resource_type":{"attribute_name":"資源タイプ","attribute_value_mlt":[{"resourcetype":"technical report","resourceuri":"http://purl.org/coar/resource_type/c_18gh"}]},"item_title":"C/C複合材のロケット燃焼器への適用　その1:C/C複合材のロケット燃焼ガス加熱評価試験","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"C/C複合材のロケット燃焼器への適用　その1:C/C複合材のロケット燃焼ガス加熱評価試験"}]},"item_type_id":"3","owner":"1","path":["1893","1917"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"41240","relation_version_is_last":true,"title":["C/C複合材のロケット燃焼器への適用　その1:C/C複合材のロケット燃焼ガス加熱評価試験"],"weko_creator_id":"1","weko_shared_id":1},"updated":"2023-06-20T19:11:28.154217+00:00"}