Flexural behavior of CFRP-aluminum fuselage frames with bolted splice joints
Few work concerned on the flexural strength of carbon fiber reinforced plastic (CFRP)-aluminum fuselage frames with bolted splice joints used in aeronautical industry. To provide help for the design of CFRP aircraft strcutures, this paper investigated the flexural behavior of CFRP-aluminum fuselage...
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| Veröffentlicht in: | Journal of physics. Conference series 2022-09, Vol.2342 (1), p.12002 |
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| creator | He, Boling Lu, Yuwei Liu, Yupeng |
| description | Few work concerned on the flexural strength of carbon fiber reinforced plastic (CFRP)-aluminum fuselage frames with bolted splice joints used in aeronautical industry. To provide help for the design of CFRP aircraft strcutures, this paper investigated the flexural behavior of CFRP-aluminum fuselage frames with bolted splice joints experimentally. Firstly, CFRP-aluminum fuselage frames were fabricated with mid-span bolted splice joints. The joints comprised: reinforced or unreinforced aluminum splice plates bolted to the fuselage frames. The bolt diameters were 4.76mm and 6.35mm. Then, the effects of splice plate and bolt dimeter on flexural behavior of CFRP-aluminum fuselage frames with bolted splice joints were investigated through four-point bending test. It has been shown that the introduction of reinforced splice plate improves the structural load capacity. However, increasing bolt diameter lowers the flexural strength of CFRP-aluminum fuselage frames with bolted splice joints. This splice jointed structure is a representative part of the rear fuselage, and the experimental results will be commonly instructive for the the aeronautical CFRP joining applications. |
| doi_str_mv | 10.1088/1742-6596/2342/1/012002 |
| format | Article |
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To provide help for the design of CFRP aircraft strcutures, this paper investigated the flexural behavior of CFRP-aluminum fuselage frames with bolted splice joints experimentally. Firstly, CFRP-aluminum fuselage frames were fabricated with mid-span bolted splice joints. The joints comprised: reinforced or unreinforced aluminum splice plates bolted to the fuselage frames. The bolt diameters were 4.76mm and 6.35mm. Then, the effects of splice plate and bolt dimeter on flexural behavior of CFRP-aluminum fuselage frames with bolted splice joints were investigated through four-point bending test. It has been shown that the introduction of reinforced splice plate improves the structural load capacity. However, increasing bolt diameter lowers the flexural strength of CFRP-aluminum fuselage frames with bolted splice joints. This splice jointed structure is a representative part of the rear fuselage, and the experimental results will be commonly instructive for the the aeronautical CFRP joining applications.</description><identifier>ISSN: 1742-6588</identifier><identifier>EISSN: 1742-6596</identifier><identifier>DOI: 10.1088/1742-6596/2342/1/012002</identifier><language>eng</language><publisher>Bristol: IOP Publishing</publisher><subject>Aeronautics ; Aircraft design ; Airframes ; Aluminum ; Bolted joints ; Carbon fiber reinforced plastics ; Flexural strength ; Frames ; Fuselages ; Modulus of rupture in bending ; Physics</subject><ispartof>Journal of physics. Conference series, 2022-09, Vol.2342 (1), p.12002</ispartof><rights>Published under licence by IOP Publishing Ltd</rights><rights>Published under licence by IOP Publishing Ltd. This work is published under http://creativecommons.org/licenses/by/3.0/ (the “License”). 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Conference series</title><addtitle>J. Phys.: Conf. Ser</addtitle><description>Few work concerned on the flexural strength of carbon fiber reinforced plastic (CFRP)-aluminum fuselage frames with bolted splice joints used in aeronautical industry. To provide help for the design of CFRP aircraft strcutures, this paper investigated the flexural behavior of CFRP-aluminum fuselage frames with bolted splice joints experimentally. Firstly, CFRP-aluminum fuselage frames were fabricated with mid-span bolted splice joints. The joints comprised: reinforced or unreinforced aluminum splice plates bolted to the fuselage frames. The bolt diameters were 4.76mm and 6.35mm. Then, the effects of splice plate and bolt dimeter on flexural behavior of CFRP-aluminum fuselage frames with bolted splice joints were investigated through four-point bending test. It has been shown that the introduction of reinforced splice plate improves the structural load capacity. However, increasing bolt diameter lowers the flexural strength of CFRP-aluminum fuselage frames with bolted splice joints. This splice jointed structure is a representative part of the rear fuselage, and the experimental results will be commonly instructive for the the aeronautical CFRP joining applications.</description><subject>Aeronautics</subject><subject>Aircraft design</subject><subject>Airframes</subject><subject>Aluminum</subject><subject>Bolted joints</subject><subject>Carbon fiber reinforced plastics</subject><subject>Flexural strength</subject><subject>Frames</subject><subject>Fuselages</subject><subject>Modulus of rupture in bending</subject><subject>Physics</subject><issn>1742-6588</issn><issn>1742-6596</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2022</creationdate><recordtype>article</recordtype><sourceid>O3W</sourceid><sourceid>BENPR</sourceid><recordid>eNqFkNtKxDAQQIMouK5-gwHfhNqkaZv0UYrrhQUXL88hTSdul3ZTk9bL39tSWREE52UG5syFg9ApJReUCBFSHkdBmmRpGLE4CmlIaERItIdmu87-rhbiEB15vyGEDcFnaLmo4aN3qsYFrNVbZR22BueLh1Wg6r6ptn2DTe-hVi-AjVMNePxedWtc2LqDEvu2rjTgja22nT9GB0bVHk6-8xw9L66e8ptgeX99m18uAx2NbwAUWSpMqjnQpCjThHIeJ4VQmYESSqYU0Rqo4kxwQZQuKSuFzuJ46FMDGZujs2lv6-xrD76TG9u77XBSRpwmNGYx5QPFJ0o7670DI1tXNcp9SkrkqE6OUuQoSI7qJJWTumHyfJqsbPuz-m6VP_4GZVuaAWZ_wP-d-AIH3X5Y</recordid><startdate>20220901</startdate><enddate>20220901</enddate><creator>He, Boling</creator><creator>Lu, Yuwei</creator><creator>Liu, Yupeng</creator><general>IOP Publishing</general><scope>O3W</scope><scope>TSCCA</scope><scope>AAYXX</scope><scope>CITATION</scope><scope>8FD</scope><scope>8FE</scope><scope>8FG</scope><scope>ABUWG</scope><scope>AFKRA</scope><scope>ARAPS</scope><scope>AZQEC</scope><scope>BENPR</scope><scope>BGLVJ</scope><scope>CCPQU</scope><scope>DWQXO</scope><scope>H8D</scope><scope>HCIFZ</scope><scope>L7M</scope><scope>P5Z</scope><scope>P62</scope><scope>PIMPY</scope><scope>PQEST</scope><scope>PQQKQ</scope><scope>PQUKI</scope><scope>PRINS</scope></search><sort><creationdate>20220901</creationdate><title>Flexural behavior of CFRP-aluminum fuselage frames with bolted splice joints</title><author>He, Boling ; Lu, Yuwei ; Liu, Yupeng</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-c2742-eeb968f6c7e15bd6517745b8a9feded3aa0cce1a738780acd13d8c9449fe1fe93</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2022</creationdate><topic>Aeronautics</topic><topic>Aircraft design</topic><topic>Airframes</topic><topic>Aluminum</topic><topic>Bolted joints</topic><topic>Carbon fiber reinforced plastics</topic><topic>Flexural strength</topic><topic>Frames</topic><topic>Fuselages</topic><topic>Modulus of rupture in bending</topic><topic>Physics</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>He, Boling</creatorcontrib><creatorcontrib>Lu, Yuwei</creatorcontrib><creatorcontrib>Liu, Yupeng</creatorcontrib><collection>IOP Publishing Free Content</collection><collection>IOPscience (Open Access)</collection><collection>CrossRef</collection><collection>Technology Research Database</collection><collection>ProQuest SciTech Collection</collection><collection>ProQuest Technology Collection</collection><collection>ProQuest Central (Alumni Edition)</collection><collection>ProQuest Central UK/Ireland</collection><collection>Advanced Technologies & Aerospace Collection</collection><collection>ProQuest Central Essentials</collection><collection>ProQuest Central</collection><collection>Technology Collection</collection><collection>ProQuest One Community College</collection><collection>ProQuest Central Korea</collection><collection>Aerospace Database</collection><collection>SciTech Premium Collection</collection><collection>Advanced Technologies Database with Aerospace</collection><collection>Advanced Technologies & Aerospace Database</collection><collection>ProQuest Advanced Technologies & Aerospace Collection</collection><collection>Publicly Available Content Database</collection><collection>ProQuest One Academic Eastern Edition (DO NOT USE)</collection><collection>ProQuest One Academic</collection><collection>ProQuest One Academic UKI Edition</collection><collection>ProQuest Central China</collection><jtitle>Journal of physics. Conference series</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>He, Boling</au><au>Lu, Yuwei</au><au>Liu, Yupeng</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Flexural behavior of CFRP-aluminum fuselage frames with bolted splice joints</atitle><jtitle>Journal of physics. Conference series</jtitle><addtitle>J. Phys.: Conf. Ser</addtitle><date>2022-09-01</date><risdate>2022</risdate><volume>2342</volume><issue>1</issue><spage>12002</spage><pages>12002-</pages><issn>1742-6588</issn><eissn>1742-6596</eissn><abstract>Few work concerned on the flexural strength of carbon fiber reinforced plastic (CFRP)-aluminum fuselage frames with bolted splice joints used in aeronautical industry. To provide help for the design of CFRP aircraft strcutures, this paper investigated the flexural behavior of CFRP-aluminum fuselage frames with bolted splice joints experimentally. Firstly, CFRP-aluminum fuselage frames were fabricated with mid-span bolted splice joints. The joints comprised: reinforced or unreinforced aluminum splice plates bolted to the fuselage frames. The bolt diameters were 4.76mm and 6.35mm. Then, the effects of splice plate and bolt dimeter on flexural behavior of CFRP-aluminum fuselage frames with bolted splice joints were investigated through four-point bending test. It has been shown that the introduction of reinforced splice plate improves the structural load capacity. However, increasing bolt diameter lowers the flexural strength of CFRP-aluminum fuselage frames with bolted splice joints. This splice jointed structure is a representative part of the rear fuselage, and the experimental results will be commonly instructive for the the aeronautical CFRP joining applications.</abstract><cop>Bristol</cop><pub>IOP Publishing</pub><doi>10.1088/1742-6596/2342/1/012002</doi><tpages>5</tpages><oa>free_for_read</oa></addata></record> |
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| subjects | Aeronautics Aircraft design Airframes Aluminum Bolted joints Carbon fiber reinforced plastics Flexural strength Frames Fuselages Modulus of rupture in bending Physics |
| title | Flexural behavior of CFRP-aluminum fuselage frames with bolted splice joints |
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