INVESTIGATION OF REPAIR TECHNIQUE FOR AIRCRAFT COMPOSITE WING PANEL WITH DISCRETE-SOURCE DAMAGE
Since the wing is the principle bearing structure of aircraft,wing skin is repaired by using mechanically fastened joints. In this paper,scheme design,experimental verification,finite element analysis and design improvement investigation of aircraft composite wing panel with discrete-source damage w...
| Main Authors: | , , , , , |
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| Format: | Article |
| Language: | zho |
| Published: |
Editorial Office of Journal of Mechanical Strength
2017-01-01
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| Series: | Jixie qiangdu |
| Subjects: | |
| Online Access: | http://www.jxqd.net.cn/thesisDetails#10.16579/j.issn.1001.9669.2017.03.010 |
| _version_ | 1797767886906851328 |
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| author | CHEN XiangMing ZHANG AYing CHAI YaNan LIU HongWu WANG LiLi YU Fei |
| author_facet | CHEN XiangMing ZHANG AYing CHAI YaNan LIU HongWu WANG LiLi YU Fei |
| author_sort | CHEN XiangMing |
| collection | DOAJ |
| description | Since the wing is the principle bearing structure of aircraft,wing skin is repaired by using mechanically fastened joints. In this paper,scheme design,experimental verification,finite element analysis and design improvement investigation of aircraft composite wing panel with discrete-source damage were carried out. Firstly,the specimen with discrete-source damage and the repaired which used fastened joint repair method were designed and manufactured. Experimental verification of scheme design was performed. Load-carrying capacity of the repaired specimen increases about 124%,compared to the unrepaired,which fully meet the design requirements. Then,for further analysis,two different specimens’ FEM models were established.The results showed that the initial repaired scheme was conservative,and the cost of structure weight was increased. Finally,three improved design configurations were proposed,and the load-carrying capacity of configuration II increased by 4. 7%,its structure weight decreased by 3. 9%. This repaired scheme provides reference for the repair design of aircraft composite wing panel with discrete-source damage. |
| first_indexed | 2024-03-12T20:46:27Z |
| format | Article |
| id | doaj.art-bb9475503ef541039977565df89255f0 |
| institution | Directory Open Access Journal |
| issn | 1001-9669 |
| language | zho |
| last_indexed | 2024-03-12T20:46:27Z |
| publishDate | 2017-01-01 |
| publisher | Editorial Office of Journal of Mechanical Strength |
| record_format | Article |
| series | Jixie qiangdu |
| spelling | doaj.art-bb9475503ef541039977565df89255f02023-08-01T07:44:28ZzhoEditorial Office of Journal of Mechanical StrengthJixie qiangdu1001-96692017-01-013955155630598457INVESTIGATION OF REPAIR TECHNIQUE FOR AIRCRAFT COMPOSITE WING PANEL WITH DISCRETE-SOURCE DAMAGECHEN XiangMingZHANG AYingCHAI YaNanLIU HongWuWANG LiLiYU FeiSince the wing is the principle bearing structure of aircraft,wing skin is repaired by using mechanically fastened joints. In this paper,scheme design,experimental verification,finite element analysis and design improvement investigation of aircraft composite wing panel with discrete-source damage were carried out. Firstly,the specimen with discrete-source damage and the repaired which used fastened joint repair method were designed and manufactured. Experimental verification of scheme design was performed. Load-carrying capacity of the repaired specimen increases about 124%,compared to the unrepaired,which fully meet the design requirements. Then,for further analysis,two different specimens’ FEM models were established.The results showed that the initial repaired scheme was conservative,and the cost of structure weight was increased. Finally,three improved design configurations were proposed,and the load-carrying capacity of configuration II increased by 4. 7%,its structure weight decreased by 3. 9%. This repaired scheme provides reference for the repair design of aircraft composite wing panel with discrete-source damage.http://www.jxqd.net.cn/thesisDetails#10.16579/j.issn.1001.9669.2017.03.010Composite wing;Stiffened panel;Discrete-source damage;Repair design;Scheme Improvement |
| spellingShingle | CHEN XiangMing ZHANG AYing CHAI YaNan LIU HongWu WANG LiLi YU Fei INVESTIGATION OF REPAIR TECHNIQUE FOR AIRCRAFT COMPOSITE WING PANEL WITH DISCRETE-SOURCE DAMAGE Jixie qiangdu Composite wing;Stiffened panel;Discrete-source damage;Repair design;Scheme Improvement |
| title | INVESTIGATION OF REPAIR TECHNIQUE FOR AIRCRAFT COMPOSITE WING PANEL WITH DISCRETE-SOURCE DAMAGE |
| title_full | INVESTIGATION OF REPAIR TECHNIQUE FOR AIRCRAFT COMPOSITE WING PANEL WITH DISCRETE-SOURCE DAMAGE |
| title_fullStr | INVESTIGATION OF REPAIR TECHNIQUE FOR AIRCRAFT COMPOSITE WING PANEL WITH DISCRETE-SOURCE DAMAGE |
| title_full_unstemmed | INVESTIGATION OF REPAIR TECHNIQUE FOR AIRCRAFT COMPOSITE WING PANEL WITH DISCRETE-SOURCE DAMAGE |
| title_short | INVESTIGATION OF REPAIR TECHNIQUE FOR AIRCRAFT COMPOSITE WING PANEL WITH DISCRETE-SOURCE DAMAGE |
| title_sort | investigation of repair technique for aircraft composite wing panel with discrete source damage |
| topic | Composite wing;Stiffened panel;Discrete-source damage;Repair design;Scheme Improvement |
| url | http://www.jxqd.net.cn/thesisDetails#10.16579/j.issn.1001.9669.2017.03.010 |
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