{"created":"2023-06-20T15:10:39.819799+00:00","id":40241,"links":{},"metadata":{"_buckets":{"deposit":"76be2399-84bd-4543-9958-7cbbb42a22e7"},"_deposit":{"created_by":1,"id":"40241","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"40241"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00040241","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["446989","446986","446988","446987"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Structural weight estimation method for winged vehicles"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1998-08","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"43","bibliographicPageStart":"1","bibliographicVolumeNumber":"1351","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":"宇宙往還機などのシステム検討時のパラメトリックスタディに有効な高精度の機体主構造重量推算法を研究し、それに基づいた解析プログラムを既知のFEM(有限要素法)重量解析結果に適用し結果を比較した。本解析プログラムの重量推算結果とFEM解析結果との誤差は15%程度であり、本重量推算手法の有効性を検証した。本重量推算法では、荷重条件、機体形状、主構造部材配置、使用材料などを入力データとして、機体各部位の部材寸度を強度計算で求めて重量を積算する解析的な推算手法を用いた。本解析プログラムにより、ある設計条件での機体構造重量を迅速に求めるだけでなく、重量を最小にするような設計条件を見いだすことも容易なため、システム検討などのパラメトリックスタディに有効である。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"This research aims at developing a structural weight estimation computer program which is useful for parametric studies, etc. The weight estimation method uses the process of piling up structural elements' (skin, stringer, etc) weights which are determined by strength analysis. The input parameters are vehicle geometry, structure arrangements, load conditions and material data. This weight estimation method is compared to an FEM (Finite Element Method) weight analysis with the same condition. The estimated weight difference between this method and FEM weight analysis is about 15 percent. This weight estimation computer program can calculate the structural weight's change against the input parameter's change quickly. Therefore, this program is useful not only for one point weight estimation but also for parametric studies.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0001571000","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-1351","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 新型航空機研究グループ"},{"subitem_text_value":"航空宇宙技術研究所 機体部"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Advanced Aircraft Research Group"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Airframe Division"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"菅野, 義就"}],"nameIdentifiers":[{"nameIdentifier":"446986","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"岩崎, 和夫"}],"nameIdentifiers":[{"nameIdentifier":"446987","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"Kanno, Yoshitsugu","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"446988","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"Iwasaki, Kazuo","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"446989","nameIdentifierScheme":"WEKO"}]}]},"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":"naltr0001351.pdf","filesize":[{"value":"501.7 kB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr0001351.pdf","url":"https://jaxa.repo.nii.ac.jp/record/40241/files/naltr0001351.pdf"},"version_id":"f52cc2f3-e5d6-49e7-88dd-9bb2ef9126e5"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"機体構造重量","subitem_subject_scheme":"Other"},{"subitem_subject":"重量推算法","subitem_subject_scheme":"Other"},{"subitem_subject":"パラメトリックスタディー","subitem_subject_scheme":"Other"},{"subitem_subject":"重量解析プログラム","subitem_subject_scheme":"Other"},{"subitem_subject":"HOPE-X","subitem_subject_scheme":"Other"},{"subitem_subject":"宇宙往還技術試験機","subitem_subject_scheme":"Other"},{"subitem_subject":"荷重分布","subitem_subject_scheme":"Other"},{"subitem_subject":"内部荷重","subitem_subject_scheme":"Other"},{"subitem_subject":"有限要素法","subitem_subject_scheme":"Other"},{"subitem_subject":"structual weight","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"weight estimation method","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"parametric study","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"weight analysis program","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"HOPE X","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"H 2 Orbiting Plane Experiment","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"load distribution","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"internal load","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"finite element method","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":"宇宙往還機の機体主構造重量推算法の研究","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"宇宙往還機の機体主構造重量推算法の研究"}]},"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":"40241","relation_version_is_last":true,"title":["宇宙往還機の機体主構造重量推算法の研究"],"weko_creator_id":"1","weko_shared_id":1},"updated":"2023-06-20T19:16:32.732507+00:00"}