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音響放射効率とパネル質量を用いたジョイントアクセプタンスの簡易式による宇宙機構体パネルの音響振動解析
https://jaxa.repo.nii.ac.jp/records/22424
https://jaxa.repo.nii.ac.jp/records/22424f4065c03-f3f7-4105-97df-25309adfa6ea
名前 / ファイル | ライセンス | アクション |
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PA1410060.pdf (663.4 kB)
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Item type | 学術雑誌論文 / Journal Article(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 音響放射効率とパネル質量を用いたジョイントアクセプタンスの簡易式による宇宙機構体パネルの音響振動解析 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Design; Acoustic; Random Vibration; Space Engineering; Joint Acceptance; Diffuse Sound Field | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_6501 | |||||
資源タイプ | journal article | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Vibroacoustic Analysis of Spacecraft Panel Using Simplified Joint Acceptance Employing Radiation Efficiency and Panel Mass | |||||
著者 |
赤城, 弘樹
× 赤城, 弘樹× 安藤, 成将× 施勤, 忠× Akagi, Hiroki× Ando, Shigemasa× Shi, Qinzhong |
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著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
出版者 | ||||||
出版者 | 日本機械学会 | |||||
書誌情報 |
日本機械学會論文集 C編 巻 79, 号 808, p. 4880-4889, 発行日 2013-12 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | In spacecraft development, acoustically induced vibration of spacecraft equipment panel is one of the criticaldesign consideration. The prediction of the vibroacoustics is necessary to specify the environment during spacecraftlaunch. Joint acceptance which is based on the integral calculus with the mode shape has been proposed for theprediction method by the authors. However, the prediction accuracy of the approach is poor for the complex structure inhigh frequency because of the uncertainty in the mathematical model. This paper is concerned with the approach usingsimplified joint acceptance employing radiation efficiency and spacecraft panel mass, not based on the integral calculus.The approach is applied to diffuse acoustical excitation of spacecraft panel, and is compared with the results of acousticexcitation test, conventional approach of joint acceptance and SEA. It is shown that the result provide good predictionsin high frequency. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0387-5024 | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AN00187463 | |||||
DOI | ||||||
関連タイプ | isVersionOf | |||||
識別子タイプ | DOI | |||||
関連識別子 | http://dx.doi.org/10.1299/kikaic.79.4880 | |||||
関連名称 | info:doi/10.1299/kikaic.79.4880 | |||||
権利 | ||||||
権利情報 | (C)2013 日本機械学会 | |||||
著者版フラグ | ||||||
出版タイプ | AM | |||||
出版タイプResource | http://purl.org/coar/version/c_ab4af688f83e57aa | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: PA1410060000 |