CN202783772U - Butt-joint structure of airplane wing body - Google Patents
Butt-joint structure of airplane wing body Download PDFInfo
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- CN202783772U CN202783772U CN 201220086864 CN201220086864U CN202783772U CN 202783772 U CN202783772 U CN 202783772U CN 201220086864 CN201220086864 CN 201220086864 CN 201220086864 U CN201220086864 U CN 201220086864U CN 202783772 U CN202783772 U CN 202783772U
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Abstract
The utility model relates to a butt-joint structure for an airplane wing body. A special butt-joint structure is unavailable for connection of a single-wing fly center wing and an airplane body in the conventional large-size airplane and medium-size airplane, so that the existing butt-joint structure has the disadvantages that 1, the wing structure is complex to design and heavy in weight due to the fact that the butt-joint part is an intersecting line on a center wing structure; 2, a stress concentration point is increased at the center wing structure; and 3, more space in the airplane body is occupied. In order to solve the technical problems, the butt-joint of the wing body is realized by adopting the butt-joint structure for the airplane wing in the utility model. The structure consists of a small airplane wing butt-joint bridge, a web plate, an airplane body through-connection long joist, an upper joint and a lower joint. A 'T'-shaped straight edge of the small airplane wing butt-joint bridge is connected with the web plate, the lower end of the web plate is connected with the upper edge of the airplane body through-connection long joist, and the lower edge of the airplane body through-connection long joist is connected with the airplane body structure; an airplane body circumferential structural member is connected with the small airplane wing butt-joint bridge through the lower joint and the upper joint; and through the through connection, the stress concentration of a lower wall plate of the center wing can be greatly reduced, the local fatigue performance can be improved, and the space in the airplane body can be increased.
Description
Technical field
The utility model relates to the aircraft connection structure, specifically, is the structure of docking with fuselage about large and medium-sized high wing airplane wing.
Background technology
Large and medium-sized high wing airplane central wing is docked with fuselage, and traditional mode is direct docking, directly is connected at the tangent place of fuselage and central wing exactly, does not have special docking structure.This structural advantages is simple in structure, and weak point one is owing to switching is gained in weight in the central wing structure; The 2nd, because fuselage directly is connected with central wing, it is less to transmit load transmitting very large load near the fuselage hoop framing member place of fuselage front at the fuselage hoop framing member place of close fuselage back, and central wing structure has been increased focal point of stress; The 3rd, taken space in the more fuselage.
Summary of the invention
The technical matters that the utility model solves: traditional large and medium-sized high wing airplane central wing is docked with airframe structure, owing to there is not special docking structure, weak point shortcoming one is because joint is intersection in the central wing structure, so place, wing structure rib position needs to increase exchanging structure, thereby makes the central wing complex structure and increased weight; The 2nd, because fuselage directly is connected with central wing, it is less to transmit load transmitting very large load near the fuselage hoop framing member place of fuselage front at the fuselage stress members near the fuselage back, central wing structure has been increased focal point of stress, and this has certain influence to the central wing structure life-span; The 3rd, taken space in the more fuselage, be unfavorable for the special pipelines layouts such as the interior system of fuselage.
The technical solution of the utility model: in order to solve the problems of the technologies described above, the utility model is achieved through the following technical solutions: adopt a kind of wing body docking structure 18 to realize the docking of wing body.This structure is docked girder 9, web 4, the long purlin 12 of fuselage switching, is formed with the 17 the same number of top connections 11 of fuselage hoop framing member and lower adaptor 16 by wing.
The long purlin 12 of fuselage switching is comprised of three limits, the square section is " ↑ " shape in obtuse angle, each edge lengths is greater than central wing course length, it is parallel and be connected with web 4 that the vertical edge parallel edges 3 of the long purlin of its middle machine body switching and wing docking girder and wing dock the "T"-shaped vertical edge of girder 5, the long purlin of fuselage switching fuselage connection side 1 is parallel with the fuselage course and connect altogether with fuselage hoop framing member 17, lower adaptor 16, the long purlin of fuselage switching be stiffened edge along the fuselage normal along the stiffened edge 2 of fuselage normal, has a plurality of fuselages switchings to grow purlin reinforced rib 20 between three limits;
The beneficial effects of the utility model: compare with traditional approach, advantage one of the present utility model is: after adopting wing body docking structure 18, because wing docking girder 9 and central wing 8 finned surface parallelism structurals, it no longer is former intersection form, reduced the complexity of central wing 8 lower wall integral panel structure designs, reduce technological requirement, alleviated central wing 8 structural weights; The 2nd, improved the local stress distribution, prolong central wing 8 structural life-times; The 3rd, increased usage space in the fuselage, be beneficial to the interior systematic pipeline of fuselage and lay.
Description of drawings
Fig. 1 is wing body docking structure figure
Fig. 2 is the wing body docking scheme drawing that contains airtight load
Fig. 3 is wing body docking structure exterior view
Fig. 4 is wing docking girder sectional views
Fig. 5 is the long purlin of fuselage switching tangent plane scheme drawing
Fig. 6 is the top connection constructional drawing
Fig. 7 is the lower adaptor constructional drawing
Wherein purlin fuselage connection side is grown in the switching of 1-fuselage; The long purlin of 2-fuselage switching is along the stiffened edge of fuselage normal; The vertical edge parallel edges of girder is docked in the long purlin of 3-fuselage switching with wing; The 4-web; The "T"-shaped vertical edge of 5-wing docking girder; 6-wing docking girder reinforced rib; The "T"-shaped horizontal edge of 7-wing docking girder; The 8-central wing; 9-wing docking girder; The vertical edge parallel edges of 10-top connection and " T " girder; The 11-top connection; The long purlin of 12-fuselage switching; 13-top connection and lower adaptor top board connection side; 14-lower adaptor top board; 15-lower adaptor and fuselage hoop stress members connection side; The 16-lower adaptor; 17-fuselage hoop stress members; 18-wing body docking structure; The 19-airframe; The long purlin of 20-fuselage switching reinforced rib.
The specific embodiment
Below in conjunction with accompanying drawing the utility model is described in further detail.
Traditional plate web girder structure is comprised of upper and lower edge strip and web, is a kind of typical structure.Special being in one of the distortion plate web girder structure that the utility model adopts is that the position is special, at wing body joint; The 2nd, this place's stress form is complicated, needs special shape could satisfy intensity, rigidity, requirement fatigue life that wing body docks, so adopted the upper and lower edge strip of special shape.
As shown in Figure 2, because airframe structure is interrupting with the wing joint, this locates flex point of stressed appearance.Fuselage hoop framing member reaches wing by lower adaptor, top connection with hoop load, airtight load is subjected to the curved fuselage reinforced bulkhead that reaches by the long purlin of fuselage switching, because span is larger, so must there be enough flexing resistances the long purlin of fuselage switching, could satisfy intensity, rigidity, requirement fatigue life of the docking of wing body.Concrete structure is as follows:
Under central wing lower wall integral panel 8 structures, increase wing body docking structure, dock girder 9, web 4, the long purlin 12 of fuselage switching, form with the 17 the same number of top connections 11 of fuselage hoop framing member and lower adaptor 16 by wing.
The long purlin 12 of fuselage switching is comprised of three limits, the square section is " ↑ " shape in obtuse angle, each edge lengths is greater than central wing course length, it is parallel and be connected with web 4 that the vertical edge parallel edges 3 of the long purlin of its middle machine body switching and wing docking girder and wing dock the "T"-shaped vertical edge of girder 5, the long purlin of fuselage switching fuselage connection side 1 is parallel with the fuselage course and connect altogether with fuselage hoop framing member 17, lower adaptor 16, the long purlin of fuselage switching be stiffened edge along the fuselage normal along the stiffened edge 2 of fuselage normal, has a plurality of fuselages switchings to grow purlin reinforced rib 20 between three limits.The effect that strengthens the bending resistant section coefficient has been played along the stiffened edge 2 of fuselage normal in its long purlin of middle machine body switching, and weight increases less under this distribution form.
Because fuselage hoop framing member 17 interrupts, be connected with fuselage hoop framing member 17 by upper and lower joint 16,11, web 4, the switching of fuselage circumferential force is reached wing docking girder 9,9 switchings reach central wing 8 lower wall panels through the docking girder again, reduce to a great extent central wing 8 lower wall panels stress and concentrated, improved the local fatigue performance.
Claims (1)
1. aircraft wing body docking structure is characterized in that: described docking structure is docked girder (9), web (4), the long purlin (12) of fuselage switching, is formed with the same number of top connection of fuselage hoop framing member (17) (11) and lower adaptor (16) by wing; Wing docking girder (9) length is identical with central wing (8) course length, it is "T"-shaped that the square section is, the wing docking "T"-shaped vertical edge of girder (5) connects altogether with web (4), top connection (11), and the wing docking "T"-shaped horizontal edge of girder (7) is to be connected along the curved surface of central wing (8) lower wall panels profile and with central wing (8) lower wall panels; On wing docking girder (9), the position that is connected with fuselage top connection (11) thickens, and there are a plurality of wing docking girder reinforced ribs (6) at the place of thickening, and wing docking girder reinforced rib (6) number is identical with fuselage hoop framing member (17) number;
The fuselage long purlin of switching (12) is comprised of three limits, the square section is " ↑ " shape in obtuse angle, each edge lengths is greater than central wing course length, it is parallel and be connected with web (4) that the vertical edge parallel edges (3) of the long purlin of its middle machine body switching and wing docking girder and wing dock the "T"-shaped vertical edge of girder (5), the long purlin fuselage connection side of fuselage switching (1) parallel with the fuselage course and with fuselage hoop framing member (17), lower adaptor (16) connects altogether, the long purlin of fuselage switching be stiffened edge along the fuselage normal along the stiffened edge (2) of fuselage normal, has a plurality of fuselages switchings to grow purlin reinforced ribs (20) between three limits;
Top connection (11) is connected to form by two limits, the square section is " L " shape in obtuse angle, top connection is parallel with the wing docking "T"-shaped vertical edge of girder (5) with the vertical edge parallel edges (10) of " T " girder and be connected web (4), and its length is that the wing lower surface is to the distance of fuselage; Top connection is connected with lower adaptor (16) with lower adaptor top board connection side (13), and length is identical with fuselage hoop framing member (17) tangent plane height;
Lower adaptor (16) is comprised of with the lower adaptor top board (14) parallel with section in the fuselage hoop stress members (17) the lower adaptor identical with fuselage hoop framing member (17) tangent plane and fuselage hoop stress members connection side (15), and all link to each other with all limits of fuselage hoop framing member (17), each edge lengths is between 70～120 millimeters; Lower adaptor top board (14) is identical with the middle cross-sectional area of fuselage hoop framing member (17).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220086864 CN202783772U (en) | 2012-03-09 | 2012-03-09 | Butt-joint structure of airplane wing body |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220086864 CN202783772U (en) | 2012-03-09 | 2012-03-09 | Butt-joint structure of airplane wing body |
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| Publication Number | Publication Date |
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| CN202783772U true CN202783772U (en) | 2013-03-13 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN 201220086864 Expired - Lifetime CN202783772U (en) | 2012-03-09 | 2012-03-09 | Butt-joint structure of airplane wing body |
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| CN (1) | CN202783772U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105314087A (en) * | 2014-06-13 | 2016-02-10 | 陕西飞机工业（集团）有限公司 | Connection structure between central wing and fuselage |
| 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 |
| CN109808868A (en) * | 2018-11-22 | 2019-05-28 | 成都飞机工业（集团）有限责任公司 | A kind of interior outer wing docking structure of small drone |
| CN110091978A (en) * | 2019-04-12 | 2019-08-06 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of stringer banjo fixing butt jointing, wing upper wall board connecting structure and aircraft |
| CN111086622A (en) * | 2019-12-19 | 2020-05-01 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft with variable wing pitch angle and implementation method |
-
2012
- 2012-03-09 CN CN 201220086864 patent/CN202783772U/en not_active Expired - Lifetime
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105314087A (en) * | 2014-06-13 | 2016-02-10 | 陕西飞机工业（集团）有限公司 | Connection structure between central wing and fuselage |
| 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 |
| CN109808868A (en) * | 2018-11-22 | 2019-05-28 | 成都飞机工业（集团）有限责任公司 | A kind of interior outer wing docking structure of small drone |
| CN110091978A (en) * | 2019-04-12 | 2019-08-06 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of stringer banjo fixing butt jointing, wing upper wall board connecting structure and aircraft |
| CN111086622A (en) * | 2019-12-19 | 2020-05-01 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft with variable wing pitch angle and implementation method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130313 |