CN212448043U - Wing structure - Google Patents
Wing structure Download PDFInfo
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- CN212448043U CN212448043U CN202021619830.XU CN202021619830U CN212448043U CN 212448043 U CN212448043 U CN 212448043U CN 202021619830 U CN202021619830 U CN 202021619830U CN 212448043 U CN212448043 U CN 212448043U
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- wing
- skin
- edge patch
- rear wall
- wing body
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Abstract
An embodiment of the utility model discloses a wing structure, wing structure includes: the wing comprises a wing body, an upper skin, a lower skin and a leading edge patch; the upper skin is attached to the upper surface of the wing body, and the lower skin is attached to the lower surface of the wing body; the front edge patch is provided with a groove, the front edge patch is sleeved on the wing body through the groove, and a seam between the upper skin and the lower skin is positioned in the groove. The wing structure can reduce the probability of delamination or cracking at the joint of the upper skin and the lower skin of the wing.
Description
Technical Field
The utility model relates to an aircraft field, concretely relates to wing structure.
Background
In recent years, unmanned military equipment almost permeates into various fields of battlefield space, unmanned aerial vehicles become important and critical forces influencing the battle progress and are paid more and more attention from countries, and military departments of many countries place the development of unmanned aerial vehicles in priority.
At present, the wing structure of the composite material is basically a structure of upper and lower skins and a framework. The joint of the upper skin and the lower skin of the wing leading edge has the problems of delamination and cracking in the using process.
Therefore, there is a need to develop a wing structure that reduces the probability of delamination or cracking at the joint between the upper and lower skins of the wing.
The information disclosed in this background section of the invention is only for enhancement of understanding of the general background of the invention and should not be taken as an acknowledgement or any form of suggestion that this information constitutes prior art already known to a person skilled in the art.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a wing structure, this wing structure can reduce the probability that the delaminating or the fracture phenomenon took place in covering junction about the wing.
In order to achieve the above object, according to the utility model provides a wing structure, wing structure includes: the wing comprises a wing body, an upper skin, a lower skin and a leading edge patch;
the upper skin is attached to the upper surface of the wing body, and the lower skin is attached to the lower surface of the wing body;
the front edge patch is provided with a groove, the front edge patch is sleeved on the wing body through the groove, and a seam between the upper skin and the lower skin is positioned in the groove.
Preferably, the leading edge patch is of an integrally formed structure, the section of the leading edge patch is V-shaped, and under the condition that the leading edge patch is sleeved on the wing body, the tip of the V-shaped is deviated from the wing body.
Preferably, the wing body comprises a front beam, a rear wall, a rib plate and a bearing main beam;
the front beam and the rear wall are oppositely arranged, the bearing main beam is connected to the front beam and the rear wall, one end of the rib plate is connected to the rear wall, the other end of the rib plate is connected to the bearing main beam or the front beam, and the rib plate is located between the front beam and the rear wall.
Preferably, the wing structure further comprises: the tenon holes are formed in the front beam and the rear wall, and the rib plates and the force bearing main beams are in tenon joint with the rear wall and the front beam through the tenon holes.
Preferably, the cross section of the bearing main beam is in an i shape, the upper end face of the i shape is attached to the upper skin, and the lower end face of the i shape is attached to the lower skin.
Preferably, the top of the bearing girder is provided with a first connecting surface, the bottom of the bearing girder is provided with a second connecting surface, the first connecting surface is attached to the upper skin, the second connecting surface is attached to the lower skin, and the first connecting surface and the second connecting surface are planes.
Preferably, the wing structure further comprises: and the adhesive layer is arranged between the upper skin and the front edge patch and between the lower skin and the front edge patch.
Has the advantages that:
1) the utility model provides a wing structure is through nested leading edge patch on the wing body for in the seam of last covering and lower covering is in the leading edge patch, play the guard action to the junction of last covering and lower covering, the delaminating or the fracture phenomenon take place for the covering junction about avoiding the wing.
2) The utility model provides a wing structure, the cross-section of bearing girder is the I shape, has increased bearing girder and last covering and the area of covering contact down, and then has increased lifting surface area, has improved bearing girder stress concentration's problem. Make unmanned aerial vehicle operation safer.
Drawings
Fig. 1 is an exploded view of a wing structure according to an embodiment of the present invention.
Fig. 2 is a schematic structural diagram of a wing structure according to an embodiment of the present invention.
Fig. 3 is a schematic cross-sectional view of a load-bearing spar of a wing structure according to an embodiment of the invention.
Description of reference numerals:
1. covering the skin; 2. a lower skin; 3. leading edge patch; 4. a front beam; 5. a rear wall; 6. a rib plate; 7. a load-bearing main beam.
Detailed Description
The technical scheme of the utility model is described in detail with the accompanying drawings.
According to the utility model discloses an aspect provides a wing structure, wing structure includes: the wing comprises a wing body, an upper skin, a lower skin and a leading edge patch;
the upper skin is attached to the upper surface of the wing body, and the lower skin is attached to the lower surface of the wing body;
the front edge patch is provided with a groove, the front edge patch is sleeved on the wing body through the groove, and a seam between the upper skin and the lower skin is positioned in the groove.
The utility model provides a wing structure is through nested leading edge patch on the wing body for in the seam of last covering and lower covering is in the leading edge patch, play the guard action to the junction of last covering and lower covering, the delaminating or the fracture phenomenon take place for the covering junction about avoiding the wing.
The utility model provides a wing structure, through covering in the upper surface laminating of wing body, covering under the lower surface laminating of wing body plays the effect of protection wing body, can reduce wing structure's windage simultaneously for unmanned aerial vehicle or the aircraft that are equipped with this wing structure move more steadily, and the energy consumption is lower.
Preferably, the leading edge patch is of an integrally formed structure, the section of the leading edge patch is V-shaped, and the tip of the V-shaped structure deviates from the wing body under the condition that the leading edge patch is sleeved on the wing body.
In this technical scheme, the structure of leading edge patch is further provided, and leading edge patch cross-section is the V font, and the pointed end of V font deviates from in the wing body for unmanned aerial vehicle or the aircraft that are equipped with this wing structure operate more steadily, and the energy consumption is lower. Meanwhile, the front edge patch is of an integrally formed structure, so that the mechanical strength of the front edge patch is improved, and the safety factor of the use of the wing structure is guaranteed.
Preferably, the wing body comprises a front beam, a rear wall, a rib plate and a bearing main beam;
the front beam and the rear wall are oppositely arranged, the bearing main beam is connected to the front beam and the rear wall, one end of the rib plate is connected to the rear wall, the other end of the rib plate is connected to the bearing main beam or the front beam, and the rib plate is located between the front beam and the rear wall.
In this technical scheme, further provided the structure of wing body, wing body has included front-axle beam, back wall, floor and load girder, has played the effect of undertaking the main stress, through the setting of floor, has further ensured the intensity of wing structure.
Preferably, the wing structure further comprises: the tenon holes are formed in the front beam and the rear wall, and the rib plates and the force bearing main beams are in tenon joint with the rear wall and the front beam through the tenon holes.
In the technical scheme, the wing structure further comprises tenon holes, the front beam, the rear wall, the rib plates and the bearing main beam are connected through tenons, on one hand, the wing body is convenient to assemble and install, and on the other hand, the wing body has high mechanical strength.
Preferably, the cross section of the bearing main beam is in an I shape, the upper end face of the I shape is attached to the upper skin, and the lower end face of the I shape is attached to the lower skin.
In the technical scheme, the cross section of the bearing main beam is I-shaped, so that the contact area of the bearing main beam with the upper skin and the lower skin is increased, the bearing area is increased, and the problem of stress concentration of the bearing main beam is solved. Make unmanned aerial vehicle operation safer.
As a preferred scheme, a first connecting surface is arranged at the top of the bearing main beam, a second connecting surface is arranged at the bottom of the bearing main beam, the first connecting surface is attached to the upper skin, the second connecting surface is attached to the lower skin, and the first connecting surface and the second connecting surface are planes.
In the technical scheme, the first connecting surface is arranged at the top of the bearing girder, and the second connecting surface is arranged at the bottom of the bearing girder, so that the contact area of the bearing girder with the upper skin and the lower skin is increased, the stress area is increased, and the problem of stress concentration of the bearing girder is solved. Make unmanned aerial vehicle operation safer.
Preferably, the wing structure further comprises: and the adhesive layer is arranged between the upper skin and the front edge patch and between the lower skin and the front edge patch.
In the technical scheme, the wing structure further comprises an adhesive layer, and the leading edge patch is more firmly fixed through the arrangement of the adhesive layer, so that the wing structure is safer to use.
Example 1
Fig. 1 is an exploded view of a wing structure according to an embodiment of the present invention. Fig. 2 is a schematic structural diagram of a wing structure according to an embodiment of the present invention. Fig. 3 is a schematic cross-sectional view of a load-bearing spar of a wing structure according to an embodiment of the invention.
As shown in fig. 1 to 3, the wing structure includes: the wing comprises a wing body, an upper skin 1, a lower skin 2 and a leading edge patch 3;
the upper skin 1 is attached to the upper surface of the wing body, and the lower skin 2 is attached to the lower surface of the wing body;
the leading edge patch 3 is provided with a groove, the leading edge patch 3 is sleeved on the wing body through the groove, and a joint of the upper skin 1 and the lower skin 2 is positioned in the groove.
The leading edge patch 3 is of an integrally formed structure, the section of the leading edge patch 3 is V-shaped, and under the condition that the leading edge patch 3 is sleeved on the wing body, the tip of the V-shaped structure deviates from the wing body.
The wing body comprises a front beam 4, a rear wall 5, a rib plate 6 and a bearing main beam 7;
the front beam 4 and the rear wall 5 are arranged oppositely, the force-bearing main beam 7 is connected to the front beam 4 and the rear wall 5, one end of the rib plate 6 is connected to the rear wall 5, the other end of the rib plate is connected to the force-bearing main beam 7 or the front beam 4, and the rib plate 6 is located between the front beam 4 and the rear wall 5.
Wherein, the wing structure still includes: the tenon holes are formed in the front beam 4 and the rear wall 5, and the rib plates 6 and the force bearing main beams 7 are in tenon joint with the rear wall 5 and the front beam 4 through the tenon holes.
The section of the bearing girder 7 is I-shaped, the upper end face of the I-shaped is attached to the upper skin 1, and the lower end face of the I-shaped is attached to the lower skin 2.
Wherein, the wing structure still includes: and the adhesive layer is arranged between the upper skin 1 and the front edge patch 3 and between the lower skin 2 and the front edge patch 3.
As shown in figure 1, the utility model divides the front edge of the wing, and the front edge of the wing is made into an integral part, namely a front edge patch 3; the bearing girder 7 is formed in one step by a mould, and the upper surface and the lower surface of the bearing girder 7 are connected with the upper skin 1 and the lower skin 2. The force-bearing main beam 7, the front beam 4 and the ribbed plate 6 are connected through tenon holes, and are glued with the rear wall 5 and then glued with the lower skin 2 and the upper skin 1 to form a whole, and then the front edge patch 3 and the whole wing body after mould assembly are positioned and glued to form a complete wing structure.
In the embodiment, the front edge patch 3 is integrally formed, and wraps the joint line of the upper skin 1 and the lower skin 2 to prevent the joint line from being influenced by the outside, so that the aim of preventing the joint of the matched molds from delaminating and cracking is fulfilled. As shown in fig. 3, the force-bearing girder 7 is in an i-shaped structure, and the upper part and the lower part of the force-bearing girder are respectively contacted with the upper skin 1 and the upper skin 1, so that the force-bearing area is increased, and the problem of stress concentration of the force-bearing girder 7 is solved.
Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described in the foregoing embodiments, or equivalents may be substituted for elements thereof. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. A wing structure, characterized in that it comprises: the wing comprises a wing body, an upper skin, a lower skin and a leading edge patch;
the upper skin is attached to the upper surface of the wing body, and the lower skin is attached to the lower surface of the wing body;
the front edge patch is provided with a groove, the front edge patch is sleeved on the wing body through the groove, and a seam between the upper skin and the lower skin is positioned in the groove.
2. The wing structure of claim 1, wherein the leading edge patch is an integrally formed structure, the leading edge patch has a V-shaped cross-section, and a tip of the V-shape is oriented away from the wing body when the leading edge patch is sleeved on the wing body.
3. The wing structure of claim 1, wherein the wing body includes a front spar, a rear wall, a rib plate, and a load-bearing main spar;
the front beam and the rear wall are oppositely arranged, the bearing main beam is connected to the front beam and the rear wall, one end of the rib plate is connected to the rear wall, the other end of the rib plate is connected to the bearing main beam or the front beam, and the rib plate is located between the front beam and the rear wall.
4. The wing structure of claim 3, further comprising: the tenon holes are formed in the front beam and the rear wall, and the rib plates and the force bearing main beams are in tenon joint with the rear wall and the front beam through the tenon holes.
5. The wing structure of claim 3, wherein the cross-section of the load-bearing spar is I-shaped, the upper end face of the I-shape being attached to the upper skin and the lower end face being attached to the lower skin.
6. The wing structure of claim 3, wherein the top of the force-bearing main girder is provided with a first connection surface, the bottom of the force-bearing main girder is provided with a second connection surface, the first connection surface is attached to the upper skin, the second connection surface is attached to the lower skin, and the first connection surface and the second connection surface are planes.
7. The wing structure of claim 1, further comprising: and the adhesive layer is arranged between the upper skin and the front edge patch and between the lower skin and the front edge patch.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021619830.XU CN212448043U (en) | 2020-08-06 | 2020-08-06 | Wing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021619830.XU CN212448043U (en) | 2020-08-06 | 2020-08-06 | Wing structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212448043U true CN212448043U (en) | 2021-02-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021619830.XU Active CN212448043U (en) | 2020-08-06 | 2020-08-06 | Wing structure |
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| CN (1) | CN212448043U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111762310A (en) * | 2020-08-06 | 2020-10-13 | 四川跃纳科技有限公司 | Wing structure |
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2020
- 2020-08-06 CN CN202021619830.XU patent/CN212448043U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111762310A (en) * | 2020-08-06 | 2020-10-13 | 四川跃纳科技有限公司 | Wing structure |
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