{"created":"2023-06-20T15:14:04.384242+00:00","id":44044,"links":{},"metadata":{"_buckets":{"deposit":"4bf831e2-9646-45b0-a854-37104eee5bdd"},"_deposit":{"created_by":1,"id":"44044","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"44044"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00044044","sets":["1887:1893","1896:1898:1913:1916"]},"author_link":["467248","467254","467257","467250","467244","467253","467245","467255","467256","467251","467259","467249","467247","467246","467258","467252"],"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1982-03","bibliographicIssueDateType":"Issued"},"bibliographicPageStart":"36","bibliographicVolumeNumber":"461","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所資料"},{"bibliographic_title":"Technical Memorandum of National Aerospace Laboratory","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"LE-5型エンジンの約1/13.6リニアスケールのノズルをもつ酸素・水素推進薬のモデルロケットエンジンを用いて,宇宙開発事業団の高空燃焼試験設備(以下「NASDA HATS」という)排気系の超音速デフューザ等についてモデル試験をおこなった。推進薬混合比5.5におけるブレークダウン圧力比(燃焼室圧/デフューザ背圧)は約65であり,混合比によるブレークダウン圧力比の変化はわずかであった。定常時のデフューザ作動圧力比がブレークダウン圧力比の1.1倍以上では着火時のスタート圧力比はブレークダウン圧力比と同程度であり,NASDA HATSのコンフィグレーションは十分な余裕をもつ。低圧室圧力は13torr以下が期待できる。デフューザの熱流束はセカンドスロート後端から拡大部の始めにかけて最大となり,超音速部の熱流束の5倍以上になり得る。燃焼ガス冷却用スプレイ水流量のプロペラント流量に対する比の設計値3.08は十分安全な値とみなすことができる。また上記の比2.7～3.2の範囲ではスプレイ水量の変化によるデフューザ背圧およびエゼクタ吸入圧の変化はわずかであった。","subitem_description_type":"Abstract"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: NALTM0461000","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 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