{"created":"2023-06-20T15:11:33.779154+00:00","id":41242,"links":{},"metadata":{"_buckets":{"deposit":"617b6a77-0662-45bb-b72f-89a0870ad5c7"},"_deposit":{"created_by":1,"id":"41242","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"41242"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00041242","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["451436","451423","451426","451425","451428","451434","451422","451435","451427","451432","451424","451431","451433","451429","451430","451437"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"C/C composites for rocket chamber applications. Part 2: Fabrication and evaluation tests of rocket chamber"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1995-05","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"17","bibliographicPageStart":"1","bibliographicVolumeNumber":"1268","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":"HOPE,スペースプレーンなどの宇宙往還機用構造材や、ロケット燃焼器材には、熱的、機械的に厳しい環境下で耐えることに加え、軽量であることが要求される。炭素繊維強化炭素複合材(C/C材)は、このような条件を満足する材料として非常に有望なもののひとつである。C/C材を酸化雰囲気中で使用するときは、耐酸化コーティングが不可欠である。しかし、これまでの耐酸化コーティングでは、ロケット燃焼器のような高温環境で使用する場合、C/C材とコーティング材との熱膨張率の差により、コーティング層に亀裂、剥離が生じ易く、信頼性、耐久性に問題があった。本研究では、HOPEなどで姿勢制御用として作動する反応制御システム(RCS)用ロケット燃焼器に対するC/C材の適用性を実証することを目的に、(1)従来型、(2)マトリックス改質型、(3)傾斜機能コーティング型の3種類のC/C材燃焼器供試体を製作し、燃焼器としての気密性、コーティング層の耐熱、耐食性、インジェクタとの接合などを調べるため、RCS推進剤として有力なモノメチルヒドラジン(MMH)/4酸化2窒素(NTO)の貯蔵性2液推進剤を用い、燃焼評価試験を行った。この結果、従来型燃焼器供試体は、内壁温度1940Kでコーティング層に侵食、剥離などの損傷は認められなかった。マトリックス改質型燃焼器供試体は、内壁温度1875Kでコーティング層に侵食、剥離などの損傷は認められなかったものの、インジェクタフランジの一部に亀裂が発生した。傾斜機能コーティング型燃焼器供試体は、内壁温度1940K2回の試験でコーティング層に侵食、剥離などの損傷はなく健全であることが確認された。インジェクタと燃焼器間のシール材として、グラメット付グラファイトパッキンが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 matrix (C/C) composites coated with SiC are promising candidates for use in the main structural materials of the body of spaceplanes and combustion chambers of rocket engines, because of their superior properties of high specific strength, specific modulus, and fracture strength at high temperatures. However, C/C composite has poor resistance to oxidation, and protection from the oxidating environment is crucial. Conventional C/C composites for use in the high-temperature components of rocket engines are coated with SiC. However, due to the difference in the thermal expansion rates of the SiC coating layer and the base materials, cracks occur in the SiC coating layer during the coating process, and oxygen diffuses to the base material through the cracks during repeated temperature cycling in the rocket combustion environment. To protect the base materials from oxidation at high temperatures, SiC C/C-coated composites with a modified matrix have been employed and also SiC C/C Functionally Gradient Materials (FGMs) have been developed. In this test series, three kinds of combustion chambers were constructed for the Reaction Control System (RCS) subscale engine of H-2 Orbiting Plane (HOPE): (1) conventional C/C composites, (2) SiC C/C-coated composites with a modified matrix, and (3) SiC C/C FGMs. Firing tests were performed at sea level at a temperature around 2000 K using nitrogen tetroxide (NTO) /monomethyl hydrazine (MMH) propellant to evaluate the durability of these chambers. This test series showed that conventional C/C composite developed no microcracks and delamination in the coating layer at 1940 K. Modified matrix C/C composite also did not suffer microcracks and delamination at the boundary between the SiC and the base materials when the inner surface temperature was 1875 K. However, microcracks were observed at injector flange surface after these test cycles. In the test series of FGMs chamber, it was shown that coating with FGMs seemed to effectively prevent permeation by the combustion gases after two cycles of 1940 K and that the FGMs chamber is a promising candidate for low thrust storable bipropellant engines. Graphite packing coupled with Gramet, which applied to the injector sealing also seemed to be effective at assuring gas tightness in the test conditions.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0004273000","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-1268","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":"佐藤, 政裕"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"只野, 真"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"植田, 修一"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"黒田, 行郎"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"日下, 和夫"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"末光, 毅"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"長谷川, 聰"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"久手, 幸徳"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Sato, Masahiro","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tadano, Makoto","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ueda, Shuichi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kuroda, Yukio","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kusaka, Kazuo","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":"naltr01268.pdf","filesize":[{"value":"3.9 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr01268.pdf","url":"https://jaxa.repo.nii.ac.jp/record/41242/files/naltr01268.pdf"},"version_id":"2c25d1b3-db87-4bb1-8783-24cbf2996dd8"}]},"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":"RCSサブスケールエンジン","subitem_subject_scheme":"Other"},{"subitem_subject":"反応制御システム","subitem_subject_scheme":"Other"},{"subitem_subject":"RCS","subitem_subject_scheme":"Other"},{"subitem_subject":"FGMs室","subitem_subject_scheme":"Other"},{"subitem_subject":"機能的傾斜材料室","subitem_subject_scheme":"Other"},{"subitem_subject":"ロケット燃焼器","subitem_subject_scheme":"Other"},{"subitem_subject":"評価試験","subitem_subject_scheme":"Other"},{"subitem_subject":"SiC","subitem_subject_scheme":"Other"},{"subitem_subject":"シリコーンカーバイト","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":"H-2ロケット打上げ型有翼回収機","subitem_subject_scheme":"Other"},{"subitem_subject":"4酸化2窒素","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":"RCS subscale engine","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"reaction control system","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"RCS","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"FGMs chamber","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"functionally gradient materials chamber","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"rocket chamber","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"evaluation test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"SiC","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"silicon carbide","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":"H 2 orbiting plane","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"nitrogen tetroxide","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2:ロケット燃焼器の試作および評価試験","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2:ロケット燃焼器の試作および評価試験"}]},"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":"41242","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2:ロケット燃焼器の試作および評価試験"],"weko_creator_id":"1","weko_shared_id":1},"updated":"2023-06-20T19:11:25.974810+00:00"}