CN103895856A - Composite-material I beam connecting device of aerofoils and aeroplane body - Google Patents
Composite-material I beam connecting device of aerofoils and aeroplane body Download PDFInfo
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- CN103895856A CN103895856A CN201410166382.5A CN201410166382A CN103895856A CN 103895856 A CN103895856 A CN 103895856A CN 201410166382 A CN201410166382 A CN 201410166382A CN 103895856 A CN103895856 A CN 103895856A
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- girder
- attaching parts
- bulkhead
- connecting device
- connecting element
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Abstract
The invention discloses a composite-material I beam connecting device of aerofoils and an aeroplane body. The composite-material I beam connecting device of aerofoils and an aeroplane body comprises an I beam, an I beam connecting element and a beam bulkhead, wherein an I beam connecting element and upper and lower flanges of the I beam are connected by adopting bolts; the I beam connecting element and an I beam web plate are cemented; the beam bulkhead consists of a bulkhead and a connecting element; two ends of the connecting element are respectively connected with the I beam connecting element and the bulkhead by adopting bolts. An aluminum alloy is adopted for the I beam connecting element provided by the invention, so that the I beam connecting element is convenient to machine, and the connection reliability is improved; the I beam connecting element and the web plate are cemented, and the connection weight is lightened; the force transmitting efficiency of root skin is developed fully, and meanwhile, the requirement on the skin forming quality is high.
Description
Technical field
The present invention relates to the connecting device of a kind of H-girder wing and fuselage.
Background technology
Wing is connected with fuselage, is divided into periphery connects and disperse power transmission and concentrated power transmission according to its power transmission form, and due to it, different performance can be for the aircraft of different purposes separately.Wherein, periphery connection disperses the bolt quantity of power transmission more, and advantage is to give full play to the power transmission efficiency of wing root covering, does not need special complicated jointing, is conducive to alleviate structure design weight; Shortcoming is to have increased the wing-body to be linked and packed with heavy work loadly, must add the tolerance on fit in king bolt and hole, makes Transfer of Shear and strength at repeated alternation bring adverse effect.Concentrate power transmission exactly wing and fuselage to be coupled together with several points, can transmit larger force and moment, reduce the man-hour that is linked and packed of wing and fuselage, and the wing-body jointing can be made of one, like this beam be the transom of wing and wing body be also the load resting point of the plug-in and inner loading of wing; Its shortcoming is mainly that the benefit of root covering can not be given full play to, and machine dosage is large, and waste of material is many.
Summary of the invention
For the deficiencies in the prior art, the invention provides that a kind of safety of structure is high, lightweight, the H-girder connection structure of the composite wing of easy processing and fuselage.
The object of the invention is to be achieved through the following technical solutions:
A H-girder connecting device for composite wing and fuselage, comprises H-girder, H-girder attaching parts and beam bulkhead, with bolts between described H-girder attaching parts and the upper and lower edge strip of H-girder, is splicing between H-girder attaching parts and I-beam web; Described beam bulkhead is made up of bulkhead and attaching parts, and the two ends of attaching parts respectively and with bolts between H-girder attaching parts and bulkhead.
The connecting device that the present invention is directed to composite material high aspect ratio two-beam type wing and fuselage, this connecting device is to process separately, then connects by regelate and wing.The present invention adopts concentrated mode of transfer force, the form that connecting device and fuselage are connected by vertical auricle fork ear be connected, this bolt is along course horizontal positioned, bolt is cut.Connecting device adopts screw to be connected and to glued joint connection with wing, connecting device bears the force and moment from wing, the deformation direction of considering wing is mainly perpendicular to wing aerofoil, adopt i-shaped beams, between web and H-girder attaching parts, adopt and glued joint, between upper and lower edge strip and H-girder attaching parts, adopt screw to connect.This connection mode has following characteristics:
(1) H-girder attaching parts adopts aluminum alloy, is convenient to processing, improves the reliability connecting;
(2) between H-girder attaching parts and web, adopt and glued joint, alleviated connection weight;
(3) given full play to the power transmission efficiency of root covering, but having relatively high expectations to covering forming quality simultaneously.
Accompanying drawing explanation
Fig. 1 is H-girder schematic diagram in the present invention;
Fig. 2 is the joint schematic diagram of H-girder in the present invention;
Fig. 3 is the schematic diagram of H-girder and H-girder attaching parts in the present invention;
Fig. 4 is central sill bulkhead schematic diagram of the present invention;
Fig. 5 is each part assembling drawing schematic diagram in the present invention.
The specific embodiment
Below in conjunction with accompanying drawing, technical scheme of the present invention is further described; but be not limited to this; every technical solution of the present invention is modified or is equal to replacement, and not departing from the spirit and scope of technical solution of the present invention, all should be encompassed in protection scope of the present invention.
Fig. 1 has provided the structural representation of H-girder 2 in the present invention, wherein H-girder 2 is compound material laying formable layer, because there is difference of potential between carbon fiber and metallic material, there will be galvanic corrosion, so internal layer is for peeling off fiber laying, outside is carbon fiber laying.On the edge strip up and down of H-girder 2 one end, be equipped with several holes 2 102.
Fig. 2 has provided the schematic diagram of H-girder attaching parts 4 in the present invention, H-girder attaching parts 4 is formed by metal material processing, one end of H-girder attaching parts 4 is I shape, have several holes 5 108 in the top and bottom of I shape end, hole 5 108 is used for connecting H-girder attaching parts 4 and H-girder 2, groove 107 is meeting after the rigidity of H-girder attaching parts 4, and whole H-girder attaching parts 4 is carried out to loss of weight.The other end of H-girder attaching parts 4 is opened some holes 6 110, and hole 6 110 is used for connecting H-girder attaching parts 4 and beam bulkhead 8, between hole 5 108 and hole 6 110, a side of H-girder attaching parts 4 has and alleviate groove 109.
Fig. 3 has provided the schematic diagram that in the present invention, H-girder 2 and H-girder attaching parts 4 assemble, between the edge strip up and down of H-girder 2 and H-girder attaching parts 4, be connected by bolt with hole 5 108 by hole 2 102, between the web of H-girder 2 and H-girder attaching parts 4, connect by adhesion agent 11, if because the shearing of advocating transmitting between H-girder attaching parts 4 and H-girder 2 webs, so by glueing joint.
Fig. 4 has provided the schematic diagram of central sill bulkhead of the present invention, beam bulkhead is made up of bulkhead 8 and attaching parts 7, one end of attaching parts 7 has hole 9 113, hole 9 113 is in order to connect H-girder attaching parts 4 and attaching parts 7, the other end of attaching parts 7 has hole 10, and hole 10 is in order to connect attaching parts 7 and bulkhead 8.
Fig. 5 has provided integral structure schematic diagram of the present invention, and entirety is made up of H-girder 2, H-girder attaching parts 4, bulkhead 8 and attaching parts 7.
Claims (6)
1. the H-girder connecting device of a composite wing and fuselage, comprise H-girder, H-girder attaching parts and beam bulkhead, it is characterized in that between described H-girder attaching parts and the upper and lower edge strip of H-girder with bolts, between H-girder attaching parts and I-beam web for glued joint.
2. the H-girder connecting device of composite wing according to claim 1 and fuselage, is characterized in that described H-girder is compound material laying formable layer, and internal layer is for peeling off fiber laying, and outside is carbon fiber laying.
3. the H-girder connecting device of composite wing according to claim 1 and fuselage, the one end that it is characterized in that described H-girder attaching parts is I shape, have the hole five that several are used for connecting H-girder attaching parts and H-girder in the top and bottom of I shape end, the other end of H-girder attaching parts is opened several and is used for connecting the hole six of H-girder attaching parts and beam bulkhead, between hole five and hole six, a side of H-girder attaching parts has and alleviate groove.
4. according to the H-girder connecting device of the composite wing described in claim 1 or 3 and fuselage, it is characterized in that described beam bulkhead is made up of bulkhead and attaching parts, the two ends of attaching parts respectively and with bolts between H-girder attaching parts and bulkhead.
5. the H-girder connecting device of composite wing according to claim 4 and fuselage, is characterized in that one end of described attaching parts has the hole nine that connects H-girder attaching parts and attaching parts, and the other end of attaching parts has the hole ten that connects attaching parts and bulkhead.
6. the H-girder connecting device of composite wing according to claim 1 and 2 and fuselage, the material that it is characterized in that described H-girder attaching parts is aluminum alloy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410166382.5A CN103895856A (en) | 2014-04-24 | 2014-04-24 | Composite-material I beam connecting device of aerofoils and aeroplane body |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410166382.5A CN103895856A (en) | 2014-04-24 | 2014-04-24 | Composite-material I beam connecting device of aerofoils and aeroplane body |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103895856A true CN103895856A (en) | 2014-07-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410166382.5A Pending CN103895856A (en) | 2014-04-24 | 2014-04-24 | Composite-material I beam connecting device of aerofoils and aeroplane body |
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| CN (1) | CN103895856A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105253289A (en) * | 2015-11-10 | 2016-01-20 | 康福斯（苏州）航空工业有限公司 | Wing and body connecting structure of airplane |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4120998A (en) * | 1977-02-03 | 1978-10-17 | Northrop Corporation | Composite structure |
| EP1584817A1 (en) * | 2004-04-07 | 2005-10-12 | Gamesa Eolica, S.A. (Sociedad Unipersonal) | Wind turbine blade |
| CN101151458A (en) * | 2005-03-31 | 2008-03-26 | 歌美飒创新技术公司 | Blade for wind-power generators |
| CN102365216A (en) * | 2009-03-30 | 2012-02-29 | 三菱重工业株式会社 | Composite tank, manufacturing method therefor, and wing |
| CN102454539A (en) * | 2010-10-29 | 2012-05-16 | 通用电气公司 | Joint design for rotor blade segments of a wind turbine |
| CN102730182A (en) * | 2012-06-20 | 2012-10-17 | 中国航天时代电子公司 | Unmanned aerial vehicle wing and body connection apparatus |
| CN102963521A (en) * | 2012-11-09 | 2013-03-13 | 北京航空航天大学 | Central wing of horizontal tail of civil airplane |
-
2014
- 2014-04-24 CN CN201410166382.5A patent/CN103895856A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4120998A (en) * | 1977-02-03 | 1978-10-17 | Northrop Corporation | Composite structure |
| EP1584817A1 (en) * | 2004-04-07 | 2005-10-12 | Gamesa Eolica, S.A. (Sociedad Unipersonal) | Wind turbine blade |
| CN101151458A (en) * | 2005-03-31 | 2008-03-26 | 歌美飒创新技术公司 | Blade for wind-power generators |
| CN102365216A (en) * | 2009-03-30 | 2012-02-29 | 三菱重工业株式会社 | Composite tank, manufacturing method therefor, and wing |
| CN102454539A (en) * | 2010-10-29 | 2012-05-16 | 通用电气公司 | Joint design for rotor blade segments of a wind turbine |
| CN102730182A (en) * | 2012-06-20 | 2012-10-17 | 中国航天时代电子公司 | Unmanned aerial vehicle wing and body connection apparatus |
| CN102963521A (en) * | 2012-11-09 | 2013-03-13 | 北京航空航天大学 | Central wing of horizontal tail of civil airplane |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105253289A (en) * | 2015-11-10 | 2016-01-20 | 康福斯（苏州）航空工业有限公司 | Wing and body connecting structure of airplane |
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Application publication date: 20140702 |
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| WD01 | Invention patent application deemed withdrawn after publication |