CN103895854B - Composite wing and fuselage connection - Google Patents
Composite wing and fuselage connection Download PDFInfo
- Publication number
- CN103895854B CN103895854B CN201410166347.3A CN201410166347A CN103895854B CN 103895854 B CN103895854 B CN 103895854B CN 201410166347 A CN201410166347 A CN 201410166347A CN 103895854 B CN103895854 B CN 103895854B
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- bulkhead
- splice
- beam splice
- back rest
- hole
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Abstract
A kind of composite wing and fuselage connection, including eyelid covering, front-axle beam, front beam splice, front-axle beam bulkhead, the back rest, rear beam splice and back rest bulkhead, described front-axle beam is shape of the mouth as one speaks beam, between front beam splice and the upper and lower edge strip of front-axle beam with bolts, between front beam splice and front-axle beam left and right web for glued joint；Described front-axle beam bulkhead is made up of front bulkhead and front connector, and the two ends of front connector are respectively and with bolts between front beam splice and front bulkhead；The described back rest is i-shaped beams, with bolts between rear beam splice and the upper and lower edge strip of the back rest, for glueing joint between rear beam splice and rear web；Described back rest bulkhead is made up of rear bulkhead and rear connectors, with bolts between two ends and rear beam splice and the rear bulkhead of rear connectors.The wing that the present invention provides and fuselage connection have the advantage that safety of structure is high, lightweight, be easily worked.
Description
Technical field
The present invention relates to a kind of wing and fuselage connection.
Background technology
Wing and the connection of fuselage, be divided into periphery connect dispersion power transmission and concentrate power transmission according to its power transmission form, owing to its most different performance may be used for the aircraft of different purposes.Wherein, the bolt quantity that periphery connects dispersion power transmission is more, and advantage is to give full play to the power transmission efficiency of airfoil root eyelid covering, it is not necessary to special complicated jointing, is conducive to alleviating structure design weight；Shortcoming is the increase in the wing-body and is linked and packed with heavy work load, it is necessary to add the fit tolerance of king-bolt and hole, makes Transfer of Shear and fatigue strength bring adverse effect.Power transmission is concentrated exactly wing to be coupled together with several points with fuselage, bigger power and moment can be transmitted, wing reduced with the man-hour that is linked and packed of fuselage, and can be made of one by the wing-body jointing, such beam is wing and the connecting elements of wing body is also the load support point of the plug-in and internal loading of wing；The benefit of its shortcoming mainly root eyelid covering can not give full play to, and machine dosage is big, and waste of material is many.
Summary of the invention
For the deficiencies in the prior art, the invention provides a kind of safety of structure is high, lightweight, be easily worked composite wing and body connection structure.
It is an object of the invention to be achieved through the following technical solutions:
A kind of composite wing and fuselage connection, including eyelid covering, front-axle beam, front beam splice, front-axle beam bulkhead, the back rest, rear beam splice and back rest bulkhead, described front-axle beam is shape of the mouth as one speaks beam, with bolts between front beam splice and the upper and lower edge strip of front-axle beam, for glueing joint between front beam splice and front web；Described front-axle beam bulkhead is made up of front bulkhead and front connector, and the two ends of front connector are respectively and with bolts between front beam splice and front bulkhead；The described back rest is i-shaped beams, with bolts between rear beam splice and the upper and lower edge strip of the back rest, for glueing joint between rear beam splice and rear web；Described back rest bulkhead is made up of rear bulkhead and rear connectors, and the two ends of rear connectors are respectively and with bolts between rear beam splice and rear bulkhead.
The present invention is directed to the attachment means of composite high aspect ratio two-beam type wing and fuselage, this attachment means is individually to process, then is connected by secondary solidification and wing.The present invention uses concentration mode of transfer force, the form that attachment means is connected by vertical auricle fork ear with fuselage be connected, this bolt is cut along course horizontal positioned, bolt.Attachment means uses screw to be connected and glued joint connection with wing, attachment means bears the power from wing and moment, deformation direction in view of wing is mainly perpendicular to aerofoil surface, front-axle beam uses shape of the mouth as one speaks beam, the back rest uses i-shaped beams, use between web and joint and glued joint, between upper and lower edge strip and joint, use screw to connect.This connected mode has the following characteristics that
(1) joint uses aluminium alloy, it is simple to processing, improves the reliability connected；
(2) use splicing between joint and web, alleviate connection weight；
(3) given full play to the power transmission efficiency of root eyelid covering, but requirement to covering forming quality simultaneously is higher.
Accompanying drawing explanation
Fig. 1 is shape of the mouth as one speaks beam (front-axle beam) schematic diagram in the present invention；
Fig. 2 is I-beam in the present invention (back rest) schematic diagram；
Fig. 3 is the joint schematic diagram (visual angle one) of front-axle beam in the present invention；
Fig. 4 is the joint schematic diagram (visual angle two) of front-axle beam in the present invention；
Fig. 5 is the schematic diagram that in the present invention, front-axle beam assembles with front beam splice；
Fig. 6 is the joint schematic diagram of the back rest in the present invention；
Fig. 7 is the back rest and the schematic diagram of rear beam splice in the present invention；
Fig. 8 is front-axle beam bulkhead schematic diagram in the present invention；
Fig. 9 is back rest bulkhead schematic diagram in the present invention；
Figure 10 is each part assembling drawing schematic diagram in the present invention.
Detailed description of the invention
Below in conjunction with the accompanying drawings technical scheme is further described; but it is not limited thereto; every technical solution of the present invention is modified or equivalent, without deviating from the spirit and scope of technical solution of the present invention, all should contain in protection scope of the present invention.
Fig. 1 and Fig. 2 sets forth front-axle beam 1 and the structural representation of the back rest 2 in the present invention, wherein front-axle beam 1 and the back rest 2 are composite plys molding, because there is potential difference between carbon fiber and metal material, it may appear that galvanic corrosion, so internal layer is for peeling off fiber laying, outside is carbon fiber laying.It is equipped with several holes 1 on the edge strip up and down of front-axle beam 1 one end, the edge strip up and down of the back rest 2 one end is equipped with several holes 2 102.
Fig. 3 and Fig. 4 gives the schematic diagram of beam splice 3 before in the present invention, front beam splice 3 is formed by metal material processing, one end of front beam splice 3 is the shape of the mouth as one speaks, several holes 4 104 are had in the top and bottom of shape of the mouth as one speaks end, hole 4 104 is for connection to front beam splice 3 and front-axle beam 1, the other end of front beam splice 3 has several holes 3 103, hole 3 103 is for connection to front beam splice 3 and front-axle beam bulkhead 6, and between hole 4 104 and hole 3 103, the left and right sides of front beam splice 3 has the right side and alleviate groove 105 and a left side alleviates groove 106.
Fig. 5 gives front-axle beam 1 and the schematic diagram of front beam splice 3 assembling in the present invention, connected by bolt by hole 1 and hole 4 104 between edge strip up and down and the front beam splice 3 of front-axle beam 1, it is attached by adhesive 10 between web and the front beam splice 3 of front-axle beam 1, if because the shearing of advocating of transmission between front beam splice 3 and front-axle beam about 1 web, so by glueing joint.
Fig. 6 gives the schematic diagram of beam splice 4 after in the present invention, rear beam splice 4 is formed by metal material processing, one end of rear beam splice 4 is I shape, several holes 5 108 are had in the top and bottom of I shape end, hole 5 108 is for connection to rear beam splice 4 and the back rest 2, groove 107 after the rigidity of beam splice 4, carries out loss of weight to whole rear beam splice 4 after meeting.If the other end of rear beam splice 4 opens dry hole 6 110, hole 6 110 is for connection to rear beam splice 4 and back rest bulkhead 8, and between hole 5 108 and hole 6 110, the side of rear beam splice 4 has and alleviate groove 109.
Fig. 7 gives the back rest 2 and the schematic diagram of rear beam splice 4 assembling in the present invention, connected by bolt by hole 2 102 and hole 5 108 between edge strip up and down and the rear beam splice 4 of the back rest 2, it is attached by adhesive 11 between web and the rear beam splice 4 of the back rest 2, if because the shearing of advocating of transmission between rear beam splice 4 and the back rest 2 web, so by glueing joint.
Fig. 8 gives the schematic diagram of front-axle beam bulkhead in the present invention, front-axle beam bulkhead is made up of front bulkhead 6 and front connector 5, one end of front connector 5 has hole 7 111, hole 7 111 is to connect front beam splice 3 and front connector 5, the other end of front connector 5 has hole 8 112, and hole 8 112 is to connect front connector 5 and front bulkhead 6.
Fig. 9 gives the schematic diagram of back rest bulkhead in the present invention, back rest bulkhead is made up of rear bulkhead 8 and rear connectors 7, one end of rear connectors 7 has hole 9 113, hole 9 113 is for beam splice 4 and rear connectors 7 after connecting, the other end of rear connectors 7 has hole 10, and hole 10 is to connect rear connectors 7 and rear bulkhead 8.
Figure 10 gives the overall structure schematic diagram of the present invention, and entirety is made up of eyelid covering 9, front-axle beam 1, the back rest 2, front beam splice 3, rear beam splice 4, front bulkhead 6, front connector 5, rear bulkhead 8 and rear connectors 7.
Claims (8)
1. a composite wing and fuselage connection, including eyelid covering, front-axle beam, front beam splice, front-axle beam bulkhead, the back rest, rear beam splice and back rest bulkhead, it is characterized in that described front-axle beam is shape of the mouth as one speaks beam, between front beam splice and the upper and lower bar of front-axle beam with bolts, between front beam splice and front web for glued joint；The described back rest is i-shaped beams, with bolts between rear beam splice and the upper and lower bar of the back rest, for glueing joint between rear beam splice and rear web；One end of described front beam splice is the shape of the mouth as one speaks, several are had for the Kong Si connecting front beam splice and front-axle beam in the top and bottom of shape of the mouth as one speaks end, the other end of front beam splice have several for the hole three connecting front beam splice and front-axle beam bulkhead, between Kong Si and hole three, the left and right sides of front beam splice has the right side and alleviates groove and a left side alleviates groove；One end of described rear beam splice is I shape, several holes five for beam splice after connecting and the back rest are had in the top and bottom of I shape end, the other end of rear beam splice opens several holes six for beam splice after connecting and back rest bulkhead, and between hole five and hole six, the side of rear beam splice has and alleviate groove.
Composite wing the most according to claim 1 and fuselage connection, it is characterised in that described front-axle beam is composite plys molding, internal layer is glass fibre laying, and outside is carbon fiber laying.
Composite wing the most according to claim 1 and fuselage connection, it is characterised in that the described back rest is composite plys molding, internal layer is glass fibre laying, and outside is carbon fiber laying.
Composite wing the most according to claim 1 and fuselage connection, it is characterised in that described front-axle beam bulkhead is made up of front bulkhead and front connector, the two ends of front connector are respectively and with bolts between front beam splice and front bulkhead.
Composite wing the most according to claim 4 and fuselage connection, it is characterised in that one end of described front connector has beam splice and the hole seven of front connector before connection, the other end of front connector has connector and the hole eight of front bulkhead before connection.
Composite wing the most according to claim 1 and fuselage connection, it is characterised in that described back rest bulkhead is made up of rear bulkhead and rear connectors, the two ends of rear connectors are respectively and with bolts between rear beam splice and rear bulkhead.
Composite wing the most according to claim 6 and fuselage connection, it is characterised in that one end of described rear connectors has beam splice and the hole nine of rear connectors after connection, the other end of rear connectors has connection rear connectors and the hole ten of rear bulkhead.
Composite wing the most according to claim 1 and fuselage connection, it is characterised in that the material of described front beam splice and rear beam splice is aluminium alloy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410166347.3A CN103895854B (en) | 2014-04-24 | 2014-04-24 | Composite wing and fuselage connection |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410166347.3A CN103895854B (en) | 2014-04-24 | 2014-04-24 | Composite wing and fuselage connection |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103895854A CN103895854A (en) | 2014-07-02 |
| CN103895854B true CN103895854B (en) | 2016-10-05 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410166347.3A Expired - Fee Related CN103895854B (en) | 2014-04-24 | 2014-04-24 | Composite wing and fuselage connection |
Country Status (1)
| Country | Link |
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| CN (1) | CN103895854B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105366025A (en) * | 2015-11-17 | 2016-03-02 | 江西洪都航空工业集团有限责任公司 | Attachment joint for aircraft wing and fuselage of three-beam type monoplane |
| CN105644771B (en) * | 2015-12-29 | 2017-09-29 | 中恒天信（天津）航空科技有限公司 | Inside bearing structure of unmanned aerial vehicle wing |
| CN108100218B (en) * | 2017-11-16 | 2021-04-16 | 中国航空工业集团公司西安飞机设计研究所 | Take dismantled radome bearing structure of wing section |
| CN112478124B (en) * | 2020-11-24 | 2022-08-05 | 航天特种材料及工艺技术研究所 | High-bearing airfoil joint load transmission structure |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1998015455A1 (en) * | 1996-10-07 | 1998-04-16 | Xinyun Wang | Prestressed structure for aircraft and the method of producing the same |
| US6056237A (en) * | 1997-06-25 | 2000-05-02 | Woodland; Richard L. K. | Sonotube compatible unmanned aerial vehicle and system |
| ES2265760B1 (en) * | 2005-03-31 | 2008-01-16 | GAMESA INNOVATION & TECHNOLOGY, S.L. | SHOVEL FOR WIND GENERATORS. |
| CN100497088C (en) * | 2007-12-28 | 2009-06-10 | 北京航空航天大学 | Connecting structure for unmanned aerial vehicle body and wing |
| JP5237170B2 (en) * | 2009-03-30 | 2013-07-17 | 三菱重工業株式会社 | COMPOSITE TANK, WING, AND METHOD FOR PRODUCING COMPOSITE TANK |
| CN202593851U (en) * | 2012-03-27 | 2012-12-12 | 南京航空航天大学 | All-moving wing aircraft without control plane |
| CN102730182B (en) * | 2012-06-20 | 2014-10-01 | 中国航天时代电子公司 | Unmanned aerial vehicle wing and body connection apparatus |
| CN103292640A (en) * | 2013-06-09 | 2013-09-11 | 江西洪都航空工业集团有限责任公司 | Single beam and rib integrated structure of missile wing framework |
| CN103434638A (en) * | 2013-09-16 | 2013-12-11 | 哈尔滨工业大学 | Method for hybrid connection of center sill and reinforcing rib of wing of composite material |
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2014
- 2014-04-24 CN CN201410166347.3A patent/CN103895854B/en not_active Expired - Fee Related
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| Publication number | Publication date |
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| CN103895854A (en) | 2014-07-02 |
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| SE01 | Entry into force of request for substantive examination | ||
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Granted publication date: 20161005 Termination date: 20210424 |