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Strength Test of CFRP Box Beam Model
https://jaxa.repo.nii.ac.jp/records/45316
https://jaxa.repo.nii.ac.jp/records/45316e19427a0-5fdb-4e75-8bbf-a676688de5a0
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
naltr01057.pdf (3.2 MB)
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| Item type | テクニカルレポート / Technical Report(1) | |||||||||||
|---|---|---|---|---|---|---|---|---|---|---|---|---|
| 公開日 | 2015-03-26 | |||||||||||
| タイトル | ||||||||||||
| タイトル | Strength Test of CFRP Box Beam Model | |||||||||||
| 言語 | en | |||||||||||
| 言語 | ||||||||||||
| 言語 | eng | |||||||||||
| 資源タイプ | ||||||||||||
| 資源タイプ識別子 | http://purl.org/coar/resource_type/c_18gh | |||||||||||
| 資源タイプ | technical report | |||||||||||
| その他のタイトル | ||||||||||||
| その他のタイトル | CFRP箱形構造模型の静強度試験 | |||||||||||
| 著者 |
機体部
× 機体部× 構造力学部
× Airframe, Division
× Structural, Mechanics Division
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| 著者所属 | ||||||||||||
| 航空宇宙技術研究所機体部 | ||||||||||||
| 著者所属 | ||||||||||||
| 航空宇宙技術研究所構造力学部 | ||||||||||||
| 著者所属（英） | ||||||||||||
| en | ||||||||||||
| Airframe Division, National Aerospace Laboratory(NAL) | ||||||||||||
| 著者所属（英） | ||||||||||||
| en | ||||||||||||
| Structural Mechanics Division, National Aerospace Laboratory(NAL) | ||||||||||||
| 出版者 | ||||||||||||
| 出版者 | 航空宇宙技術研究所 | |||||||||||
| 出版者（英） | ||||||||||||
| 出版者 | National Aerospace Laboratory(NAL) | |||||||||||
| 書誌情報 |
航空宇宙技術研究所報告 en : Technical Report of National Aerospace Laboratory TR-1057 巻 1057, p. 21, 発行日 1990-02 |
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| 抄録（英） | ||||||||||||
| 内容記述タイプ | Other | |||||||||||
| 内容記述 | A technical research, ″Research on Structures″, has been conducted at NAL to obtain basic design data and technical information on applying advanced composites to primary structures of an aircraft for weight saving. As a part of this research, static and fatigue tests were performed on CFRP spar rib models with corrugated web and four types of CFRP joint assembly models which are typical joints for a tailplane structure. The detailed procedures of the tests and their results have already been reported in references (1)through(5). In addition to the above, strength tests of a CFRP Box Beam model with sweptback angle(BBmodel) were conducted and this report describes some results of the experimental study on this model. The purpose of the tests were to evaluate ultimate strength and strain distributions in critical parts, as well as to investigate behavior of deformation initiation of damages, and sequence of failure. The model consists of two spars with sinusoidal wave webs, three ribs, stiffened panels for upper and lower skins made of CFRP and metallic fixture at the root, which were assembled using mechanical fasteners such as rivets and bolts. The model was fixed in cantilever configuration through the root fixtures which were bolted to rigid plate and loading was applied downward at the center of the wing tip. The first failure was panel buckling of the lower skin near the kink corner, just where FEM analysis had predicted that filure would occur. Clipping of lower stringers occurred next with delamination of their webs. Detailed examination of strain behavior and observation of the video record of the tests made clear the sequence of failure. It was concluded that utilization of CFRP as primary structural elements for a tailplane is promising. | |||||||||||
| ISSN | ||||||||||||
| 収録物識別子タイプ | ISSN | |||||||||||
| 収録物識別子 | 0389-4010 | |||||||||||
| 資料番号 | ||||||||||||
| 内容記述タイプ | Other | |||||||||||
| 内容記述 | 資料番号: NALTR1057000 | |||||||||||
| レポート番号 | ||||||||||||
| 内容記述タイプ | Other | |||||||||||
| 内容記述 | レポート番号: NAL TR-1057 | |||||||||||
