{"created":"2023-06-20T15:02:44.741941+00:00","id":31827,"links":{},"metadata":{"_buckets":{"deposit":"7ceb55aa-f506-4027-a70b-3bffb6276983"},"_deposit":{"created_by":1,"id":"31827","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"31827"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00031827","sets":["1887:1890","1896:1898:1899:1910"]},"author_link":["406383","406384"],"item_9_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Static Firing Tests of HT-110 Engines"}]},"item_9_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1966-06","bibliographicIssueDateType":"Issued"},"bibliographicIssueNumber":"2_B","bibliographicPageEnd":"653","bibliographicPageStart":"627","bibliographicVolumeNumber":"2","bibliographic_titles":[{"bibliographic_title":"東京大学宇宙航空研究所報告"}]}]},"item_9_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"The characteristics of this rocket are its high slender ratio designed by Prof. Ikeda and the use of the slow burning polyurethane propellant developed by Prof. Yamazaki et al. To proceed the engine test step by step, we were planning to complete the test of a 3/4 size rocket at first. Experimental runs from A-l to A-12 are belonged to this series and they are charged with the propellant without softener. By changing throat diameter and free port area systematically, a stable region in which the propellant burns normally was determined. Succeeding to this, the reproducibility of the firing test of the engine whose working conditions were specified uniquely was checked. After completion of the 3/4 size engine tests, a series of full size engine test was performed with runs from A-13 to A-20. In the latter case, the cross section of the propellant was changed stepwisely in the axial direction at about 3/4 of a full length. This change was accepted to decrease Ki at the nozzle end and to reduce the initial peak. Moreover, to minimize the chance to trigger the fatal oscillatory burning, the cylindrical igniter made of cellulose acetate was replaced by a cage type igniter and the more rubber-like propellant containing a small amount of softener was used throughout the full size engine tests. The use of the longer grain length promotes the erosive burning and induces the extremely long tailoff period and the sharp, strong initial peak. To refine these undesirable points, a portion of the propellant inner surface was coated with a thin restrictor layer. For the protection of the severe erosion, it was preferable to apply the restrictor to the nozzle end surface and to prevent the coated surface from burning for a while after ignition. During these experimental runs, a correlation between the physical properties of propellants and the combustion instability of engines was derived.","subitem_description_type":"Other"}]},"item_9_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: SA0124882000","subitem_description_type":"Other"}]},"item_9_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"東京大学宇宙航空研究所"}]},"item_9_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0563-8100","subitem_source_identifier_type":"ISSN"}]},"item_9_source_id_24":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AN00161914","subitem_source_identifier_type":"NCID"}]},"item_9_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"SSR委員会:東京大学宇宙航空研究所原動機部"}]},"item_9_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"SSR Committee:the Institute of Space and Aeronautical Science University of Tokyo"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"倉谷, 健治"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"KURATANI, Kenji","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":"2020-01-24"}],"displaytype":"detail","filename":"SA0124882.pdf","filesize":[{"value":"1.6 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"SA0124882.pdf","url":"https://jaxa.repo.nii.ac.jp/record/31827/files/SA0124882.pdf"},"version_id":"e856d80b-1d4f-48e3-8e63-48614674f6f9"}]},"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":"departmental bulletin paper","resourceuri":"http://purl.org/coar/resource_type/c_6501"}]},"item_title":"II.2.1 エンジンの燃焼性能について(2 エンジン)(II.関連研究)","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"II.2.1 エンジンの燃焼性能について(2 エンジン)(II.関連研究)"}]},"item_type_id":"9","owner":"1","path":["1890","1910"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"31827","relation_version_is_last":true,"title":["II.2.1 エンジンの燃焼性能について(2 エンジン)(II.関連研究)"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T00:49:25.287473+00:00"}