CN204979214U - Skin structure and have its airfoil and aircraft - Google Patents
Skin structure and have its airfoil and aircraft Download PDFInfo
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- CN204979214U CN204979214U CN201520614571.4U CN201520614571U CN204979214U CN 204979214 U CN204979214 U CN 204979214U CN 201520614571 U CN201520614571 U CN 201520614571U CN 204979214 U CN204979214 U CN 204979214U
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- exterior skin
- skin
- inside panel
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- plane nose
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Abstract
The utility model discloses a skin structure and have its airfoil and aircraft. The outer covering setting of skin structure's first outer covering and second is on the airfoil, and first outer covering and the outer covering of second extend and the first outer covering leading edge of formation that crosses to the other side's direction is crooked respectively from the one end of keeping away from aircraft nose, an inner skin just extends to the aircraft nose orientation keeping away from the first outer covering setting of aircraft nose orientation laminating to keep away from first outer covering gradually, form first packing space, the covering setting outside keeping away from aircraft nose orientation laminating second of the 2nd inner skin, and extend to the aircraft nose orientation to keep away from the outer covering of second gradually, form the second packing space, and an inner skin and the 2nd inner skin cross in nearly aircraft nose orientation, fill the core fill first packing space with in the second packing space. Adopt this kind of structure, under the same condition of weight, for prior art, improved the anti bird of leading edge structure and hit the performance.
Description
Technical field
The utility model relates to space technology field, particularly relates to a kind of stressed-skin construction and has its aerofoil and aircraft.
Background technology
The sandwich construction covering that existing empennage skins front edges comprises aluminum alloy chemical milling covering, fuse is equal thickness, similar structure also has the inner leading edge structure installing two dividing plate.
But above-mentioned several structures, in actual use, all there will be covering breakdown, bird body after penetrating covering remaining energy comparatively large, and be applied on front-axle beam, damage serious phenomenon by making front-axle beam and occur.
Therefore, wish a kind of technical scheme to overcome or at least alleviate at least one above-mentioned defect of prior art.
Utility model content
The purpose of this utility model is at least one the above-mentioned defect providing a kind of stressed-skin construction to overcome or at least alleviate prior art.
For achieving the above object, the utility model provides a kind of stressed-skin construction, for empennage or the wing of aircraft.Described stressed-skin construction comprises: exterior skin, described exterior skin comprises the first exterior skin and the second exterior skin, described first exterior skin and described second exterior skin are arranged on aerofoil, described first exterior skin and described second exterior skin from the one end away from plane nose respectively to described plane nose direction, bendingly to the other side direction extend and cross, form the first exterior skin leading edge; Inside panel, described inside panel is arranged on the empty internal of described exterior skin; Described inside panel comprises the first inside panel and the second inside panel; Described first inside panel is being arranged away from described first exterior skin of described plane nose direction laminating, and extends to described plane nose direction, and gradually away from described first exterior skin, forms the first packing space; Described second inside panel is being arranged away from described second exterior skin of described plane nose direction laminating, and extends to described plane nose direction, and gradually away from described second exterior skin, forms the second packing space; And described first inside panel and described second inside panel cross in nearly described plane nose direction; Filled core, described filled core is filled in described first packing space and described second packing space.
Preferably, described first inside panel from described first exterior skin in one end of described plane nose to the middle of the other end away from described first exterior skin; Described second inside panel from described second exterior skin in one end of described plane nose to the middle of the other end away from described second exterior skin.
Preferably, described first inside panel is connected with described exterior skin with the intersection of described second inside panel in nearly described plane nose direction.
Preferably, described first inside panel and the described second inside panel intersection in nearly described plane nose direction is connected with the intersection of described first exterior skin and the second exterior skin.
Preferably, described first inside panel and described second inside panel have space between the intersection and the intersection of described first exterior skin and the second exterior skin in nearly described plane nose direction, this space is communicated with described first packing space and described second packing space, and this space is called connected space.
Preferably, in described connected space, filled core is filled.
Preferably, extremely brace panel is provided with between described first exterior skin and the intersection of described second exterior skin from the intersection of described first inside panel and described second inside panel.
Preferably, described filled core is made with light weight cellular material.
The utility model additionally provides a kind of aerofoil, and described aerofoil comprises stressed-skin construction as above.
The utility model additionally provides a kind of aircraft, and described aircraft comprises aerofoil as above.
In stressed-skin construction in the utility model, there is between exterior skin and inside panel the first packing space; And second packing space; Filled core, described filled core is filled in described first packing space and described second packing space.Adopt this structure, when weight is identical, relative to prior art, the anti-bird that improve leading edge structure hits performance.
Accompanying drawing explanation
Fig. 1 is the structural representation of the stressed-skin construction according to the utility model one embodiment.
Fig. 2 is the generalized section of the stressed-skin construction shown in Fig. 1.
Reference numeral:
| 1 | Exterior skin | 21 | First inside panel |
| 11 | First exterior skin | 22 | Second inside panel |
| 12 | Second exterior skin | 4 | Filled core |
| 13 | First exterior skin leading edge | ||
| 2 | Inside panel |
Detailed description of the invention
The object implemented for making the utility model, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the utility model embodiment, are further described in more detail the technical scheme in the utility model embodiment.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the utility model part embodiment, instead of whole embodiments.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the utility model, and can not be interpreted as restriction of the present utility model.Based on the embodiment in the utility model, those of ordinary skill in the art are not making the every other embodiment obtained under creative work prerequisite, all belong to the scope of the utility model protection.Below in conjunction with accompanying drawing, embodiment of the present utility model is described in detail.
In description of the present utility model, it will be appreciated that, term " " center ", " longitudinal direction ", " transverse direction ", " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end " " interior ", orientation or the position relationship of the instruction such as " outward " are based on orientation shown in the drawings or position relationship, only the utility model and simplified characterization for convenience of description, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore the restriction to the utility model protection domain can not be interpreted as.
Stressed-skin construction of the present utility model is used in the empennage of aircraft or wing, and can give aircraft protection when bird is hit.Described stressed-skin construction comprises exterior skin, inside panel and filled core.Wherein, exterior skin comprises the first exterior skin and the second exterior skin, first exterior skin and the second exterior skin are arranged on aerofoil, first exterior skin and the second exterior skin from the one end away from plane nose respectively to plane nose direction, bendingly to the other side direction extend and cross, form the first exterior skin leading edge; Inside panel is arranged on the empty internal of exterior skin; Inside panel comprises the first inside panel and the second inside panel; First inside panel is arranged at the first exterior skin of fitting away from plane nose direction, and extends to plane nose direction, and gradually away from the first exterior skin, forms the first packing space; Second inside panel is arranged at the second exterior skin of fitting away from plane nose direction, and extends to plane nose direction, and gradually away from the second exterior skin, forms the second packing space; And the first inside panel and the second inside panel cross in nearly plane nose direction; Filled core is filled in the first packing space and the second packing space.
In stressed-skin construction in the utility model, there is between exterior skin and inside panel the first packing space; And second packing space; Filled core, described filled core is filled in described first packing space and described second packing space.Adopt this structure, when weight is identical, relative to prior art, the anti-bird that improve leading edge structure hits performance.
Fig. 1 is the structural representation of the stressed-skin construction according to the utility model one embodiment.Fig. 2 is the generalized section of the stressed-skin construction shown in Fig. 1.
Stressed-skin construction as shown in Figure 1 comprises exterior skin 1, inside panel 2 and filled core 4.
See Fig. 1, in the present embodiment, exterior skin 1 comprises the first exterior skin 11 and the second exterior skin 12, first exterior skin 11 and the second exterior skin 12 are arranged on aerofoil, first exterior skin 11 and the second exterior skin 12 from the one end away from plane nose respectively to plane nose direction, bendingly to the other side direction extend and cross, form the first exterior skin leading edge 13.
See Fig. 1, in the present embodiment, inside panel 2 is arranged on the empty internal of exterior skin 1; Inside panel 2 comprises the firstth inside panel 21 and the second inside panel 22.
See Fig. 2, in the present embodiment, the first inside panel 21 is arranged at the first exterior skin 11 of fitting away from plane nose direction, and extends to plane nose direction, and gradually away from the first exterior skin 11, forms the first packing space; Second inside panel 22 is arranged at the second exterior skin 12 of fitting away from plane nose direction, and extends to plane nose direction, and gradually away from the second exterior skin 12, forms the second packing space; And the first inside panel 21 and the second inside panel 22 cross in nearly plane nose direction.
Particularly, in the present embodiment, the first inside panel 21 from the first exterior skin 11 in one end of plane nose to the middle of the other end away from the first exterior skin 11; Second inside panel 22 from the second exterior skin 12 in one end of plane nose to the middle of the other end away from the second exterior skin 12.
In an alternative embodiment, the first inside panel is connected with exterior skin with the intersection of the second inside panel in nearly plane nose direction.
In another alternative, the first inside panel and the second inside panel intersection in nearly plane nose direction is connected with the intersection of the first exterior skin and the second exterior skin.
Advantageously, first inside panel and described second inside panel can also be: the first inside panel and the second inside panel have space between the intersection and the intersection of the first exterior skin and the second exterior skin in nearly plane nose direction, this space is communicated with the first packing space and described second packing space, and this space is called connected space.Filled core is filled in this connected space.Thus the intensity of this stressed-skin construction can be improved further.
Advantageously, brace panel is provided with between intersection's to the first exterior skin and the intersection of the second exterior skin of the first inside panel and the second inside panel.Thus the intensity of this stressed-skin construction can be improved further.
See Fig. 1, in the present embodiment, filled core 4 is filled in the first packing space and described second packing space.
Advantageously, in the present embodiment, filled core 4 is made with light weight cellular material.Namely light weight cellular material has impact resistance power, and its lighter weight, can loss of weight.
The utility model additionally provides a kind of aerofoil, and described aerofoil comprises stressed-skin construction as above.
The utility model additionally provides a kind of aircraft, and described aircraft comprises aerofoil as above.
Finally it is to be noted: above embodiment only in order to the technical solution of the utility model to be described, is not intended to limit.Although be described in detail the utility model with reference to previous embodiment, those of ordinary skill in the art is to be understood that: it still can be modified to the technical scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of each embodiment technical scheme of the utility model.
Claims (10)
1. a stressed-skin construction, for empennage or the wing of aircraft, it is characterized in that, described stressed-skin construction comprises:
Exterior skin (1), described exterior skin (1) comprises the first exterior skin (11) and the second exterior skin (12), described first exterior skin (11) and described second exterior skin (12) are arranged on aerofoil, described first exterior skin (11) and described second exterior skin (12) from the one end away from plane nose respectively to plane nose direction, bendingly to the other side direction extend and cross, form the first exterior skin leading edge (13);
Inside panel (2), described inside panel (2) is arranged on the empty internal of described exterior skin (1); Described inside panel (2) comprises the first inside panel (21) and the second inside panel (22);
Described first inside panel (21) is being arranged away from plane nose direction described first exterior skin (11) of laminating, and extend to described plane nose direction, and gradually away from described first exterior skin (11), form the first packing space;
Described second inside panel (22) is being arranged away from described second exterior skin (12) of described plane nose direction laminating, and extend to described plane nose direction, and gradually away from described second exterior skin (12), form the second packing space; And described first inside panel (21) and described second inside panel (22) cross in nearly described plane nose direction;
Filled core (4), described filled core (4) is filled in described first packing space and described second packing space.
2. stressed-skin construction as claimed in claim 1, it is characterized in that, described first inside panel (21) from described first exterior skin (11) in one end of described plane nose to the middle of the other end away from described first exterior skin (11);
Described second inside panel (22) from described second exterior skin (12) in one end of described plane nose to the middle of the other end away from described second exterior skin (12).
3. stressed-skin construction as claimed in claim 1, it is characterized in that, described first inside panel (21) is connected with described exterior skin (1) with the intersection of described second inside panel (22) in nearly described plane nose direction.
4. stressed-skin construction as claimed in claim 3, it is characterized in that, described first inside panel (21) and described second inside panel (22) intersection in nearly described plane nose direction is connected with the intersection of described first exterior skin (11) and the second exterior skin (12).
5. stressed-skin construction as claimed in claim 4, it is characterized in that, described first inside panel (21) and described second inside panel (22) have space between the intersection and the intersection of described first exterior skin (11) and the second exterior skin (12) in nearly described plane nose direction, this space is communicated with described first packing space and described second packing space, and this space is called connected space.
6. stressed-skin construction as claimed in claim 5, is characterized in that, fill filled core (4) in described connected space.
7. stressed-skin construction as claimed in claim 5, it is characterized in that, be extremely provided with brace panel between described first exterior skin (11) and the intersection of described second exterior skin (12) from the intersection of described first inside panel (21) and described second inside panel (22).
8. stressed-skin construction as claimed in claim 1, it is characterized in that, described filled core (4) is made with light weight cellular material.
9. an aerofoil, is characterized in that, described aerofoil comprises stressed-skin construction as claimed in any of claims 1 to 8 in one of claims.
10. an aircraft, is characterized in that, described aircraft comprises aerofoil as claimed in claim 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520614571.4U CN204979214U (en) | 2015-08-14 | 2015-08-14 | Skin structure and have its airfoil and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520614571.4U CN204979214U (en) | 2015-08-14 | 2015-08-14 | Skin structure and have its airfoil and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204979214U true CN204979214U (en) | 2016-01-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520614571.4U Active CN204979214U (en) | 2015-08-14 | 2015-08-14 | Skin structure and have its airfoil and aircraft |
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| CN (1) | CN204979214U (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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2015
- 2015-08-14 CN CN201520614571.4U patent/CN204979214U/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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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |