CN204937483U - A kind of wing flap leading edge auxiliary support apparatus and there is its aircraft - Google Patents
A kind of wing flap leading edge auxiliary support apparatus and there is its aircraft Download PDFInfo
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- CN204937483U CN204937483U CN201520614482.XU CN201520614482U CN204937483U CN 204937483 U CN204937483 U CN 204937483U CN 201520614482 U CN201520614482 U CN 201520614482U CN 204937483 U CN204937483 U CN 204937483U
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- auxiliary support
- leading edge
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- 230000008093 supporting effect Effects 0.000 claims description 28
- 230000015572 biosynthetic process Effects 0.000 claims description 4
- 239000010687 lubricating oil Substances 0.000 claims description 3
- 239000003921 oil Substances 0.000 claims description 3
- 230000000153 supplemental effect Effects 0.000 claims 2
- 230000000694 effects Effects 0.000 abstract description 3
- 230000000712 assembly Effects 0.000 abstract 6
- 238000000429 assembly Methods 0.000 abstract 6
- 101100334009 Caenorhabditis elegans rib-2 gene Proteins 0.000 description 6
- 239000000243 solution Substances 0.000 description 5
- 101001017827 Mus musculus Leucine-rich repeat flightless-interacting protein 1 Proteins 0.000 description 4
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 208000032443 Masked facies Diseases 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Abstract
The utility model discloses a kind of wing flap leading edge auxiliary support apparatus and there is its aircraft.Described wing flap leading edge auxiliary support apparatus comprises: auxiliary support assemblies; Described auxiliary support assemblies is connected with aircraft flap leading edge (11); Spacing rib (2); Described spacing rib (2) is arranged on aircraft wing trailing edge, and described spacing rib (2) is provided with channel-shaped structure (21); Wherein, aircraft is under described cruising condition, and described auxiliary support assemblies is suitable for being contained in the channel-shaped structure (21) of described spacing rib (2).Its shape of channel-shaped structure of the present utility model is more suitable for coordinating with auxiliary support assemblies, and channel-shaped structure with between auxiliary support assemblies for face contacts, but not point cantact of the prior art, can not be excessive or too small and cause auxiliary support assemblies cannot enter channel-shaped structure due to the vertical distortion of wing flap, thus cannot desired effects be reached.
Description
Technical Field
The utility model relates to an aircraft technical field especially relates to a wing flap leading edge auxiliary stay device and have its aircraft.
Background
The wing span of the airplane with the large aspect ratio is generally very large, the wing flap usually reaches more than 8 meters, only 2-3 groups of moving components are allowed to be arranged as supports in the aspects of aerodynamics and structure, the wing face rigidity is weak due to the large span of the supporting point, and the wing flap is easy to interfere with the fixed trailing edge of the wing after being deformed in a cruising state.
In the prior art, the deformation of a control flap of an airplane with a large aspect ratio in a cruising state is usually to increase auxiliary support.
The technical scheme has the defects that in the process of retracting the flap in the air, the flap deforms too much or too little in the vertical direction, so that the guide strips cannot enter between the two rollers, the auxiliary supporting effect cannot be achieved, and the supporting rollers can be damaged.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
SUMMERY OF THE UTILITY MODEL
It is an object of the present invention to provide a flap leading edge supplementary support device that overcomes or at least alleviates at least one of the above-mentioned drawbacks of the prior art.
To achieve the above object, the present invention provides a flap leading edge auxiliary supporting device. The flap leading edge auxiliary supporting device is used for assisting an airplane to support a flap in a cruising state, and comprises: an auxiliary support assembly; the auxiliary support assembly is connected with the leading edge of the airplane flap; a spacing rib; the limiting rib is arranged on the trailing edge of the airplane wing, and a groove-shaped structure is arranged on the limiting rib; wherein the auxiliary support assembly is adapted to be received in the channel-like formation of the spacing rib in the cruise condition of the aircraft.
Preferably, the auxiliary support assembly comprises: a joint having one end connected to the aircraft flap leading edge; a roller disposed on the other end of the joint.
Preferably, one end of the roller connected with the joint is connected with the eccentric bolt.
Preferably, an adjusting plectrum is mounted on a bolt head of the eccentric bolt and is used for adjusting the eccentric position of the eccentric bolt by rotating the eccentric bolt.
Preferably, the groove-shaped structure on the limiting rib is shaped to guide the motion track of the auxiliary support assembly when the flap is switched from the take-off and landing state of the airplane to the cruise state of the airplane, so that the auxiliary support assembly is accommodated in the groove-shaped structure.
Preferably, an oil injection hole is formed in the eccentric bolt for injecting lubricating oil.
Preferably, one end of the roller connected with the joint is connected through an eccentric bushing.
Preferably, an adjusting plectrum is installed on the periphery of the eccentric bushing and is used for adjusting the eccentric position of the eccentric bushing by rotating the eccentric bushing.
Preferably, the groove-shaped structure on the limiting rib comprises a first guide strip and a second guide strip, when the flap is switched to a cruise state of the aircraft in a take-off and landing state of the aircraft, the auxiliary support assembly moves along the flap and has a preset movement track, and the first guide strip and the second guide strip are used for limiting the movement track of the auxiliary support assembly so that the auxiliary support assembly moves in the preset movement track.
The utility model also provides an aircraft, the aircraft includes as above the supplementary strutting arrangement of flap leading edge.
The utility model provides an among the supplementary strutting arrangement of flap leading edge, supplementary supporting component is suitable for the holding in the groove-shaped structure of spacing rib, for the centre gripping mode of the upper and lower gyro wheel among the prior art, the utility model discloses an its shape of groove-shaped structure more is suitable for and supplementary supporting component cooperation, and is surface contact between groove-shaped structure and the supplementary supporting component, and the point contact among the non-prior art, and can not lead to supplementary supporting component can't get into groove-shaped structure because the vertical deformation of flap is too big or undersize to can't reach predetermined effect. Compared with the prior art, the utility model provides a supplementary strutting arrangement of flap leading edge can allow the flap to have certain deflection.
Drawings
Fig. 1 is a schematic structural view of a flap leading edge auxiliary supporting device according to an embodiment of the present invention.
FIG. 2 is an enlarged view of the flap leading edge auxiliary support device shown in FIG. 1.
Reference numerals:
| 1 | flap | 212 | Second guide strip |
| 11 | Aircraft flap leading edge | 3 | Joint |
| 2 | Spacing rib | 4 | Roller wheel |
| 21 | Groove-like structure | 5 | Eccentric bushing |
| 211 | First guide strip | 6 | Adjustable shifting piece |
Detailed Description
In order to make the purpose, technical solution and advantages of the present invention clearer, the following will combine the drawings in the embodiments of the present invention to perform more detailed description on the technical solution in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present invention, and should not be construed as limiting the present invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "central", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience of description and for simplicity of description, and do not indicate or imply that the device or element so referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be considered as limiting the scope of the invention.
The utility model discloses a flap leading edge auxiliary supporting device is used for the aircraft auxiliary supporting flap under cruising condition, the flap leading edge auxiliary supporting device includes auxiliary supporting component and spacing rib, wherein, auxiliary supporting component is connected with aircraft flap leading edge; the limiting rib is arranged on the trailing edge of the airplane wing, and a groove-shaped structure is arranged on the limiting rib; the auxiliary support assembly is adapted to be received in the channel-like formation of the spacing rib when the aircraft is in cruise conditions.
The utility model provides an among the supplementary strutting arrangement of flap leading edge, supplementary supporting component is suitable for the holding in the groove-shaped structure of spacing rib, for the centre gripping mode of the upper and lower gyro wheel among the prior art, the utility model discloses an its shape of groove-shaped structure more is suitable for and supplementary supporting component cooperation, and is surface contact between groove-shaped structure and the supplementary supporting component, and the point contact among the non-prior art, and can not lead to supplementary supporting component can't get into groove-shaped structure because the vertical deformation of flap is too big or undersize to can't reach predetermined effect. Compared with the prior art, the utility model provides a supplementary strutting arrangement of flap leading edge can allow the flap to have certain deflection.
When the landing and taking-off state of the airplane is changed to the cruising state of the airplane, the airplane flap is usually moved towards the trailing edge of the airplane wing.
Fig. 1 is a schematic structural view of a flap leading edge auxiliary supporting device according to an embodiment of the present invention. FIG. 2 is an enlarged view of the flap leading edge auxiliary support device shown in FIG. 1.
The flap leading edge auxiliary supporting device shown in fig. 1 and 2 comprises an auxiliary supporting component and a limiting rib 2, wherein the auxiliary supporting component is connected with a flap leading edge 11 of an airplane; the limiting rib 2 is arranged on the trailing edge of the airplane wing, and a groove-shaped structure 21 is arranged on the limiting rib 2; wherein the auxiliary support assembly is adapted to be received in the channel-like formation 21 of the spacing rib 2 when the aircraft is cruising.
Referring to fig. 1, in the present embodiment, the auxiliary support assembly includes: a joint 3 and a roller 4, wherein one end of the joint 3 is connected with a leading edge 11 of the airplane flap; a roller 4 is provided on the other end of the joint.
Referring to fig. 2, in the present embodiment, one end of the roller 4 connected to the joint 3 is connected through an eccentric bushing 5. And an adjustment dial 6 is mounted on an outer circumference of the eccentric bush 5 for adjusting an eccentric position of the eccentric bush 5 by rotating the eccentric bush 5.
In an alternative embodiment, the end of the roller connected to the joint is connected by an eccentric bolt.
It will be appreciated that in another alternative embodiment, the bolt is a plain bolt, i.e. without an eccentric angle.
In the embodiment with the eccentric bolt, an adjusting plectrum is arranged on the bolt head of the eccentric bolt and is used for adjusting the eccentric position of the eccentric bolt by rotating the eccentric bolt.
Specifically, by rotating the eccentric bolt, the eccentric position of the eccentric bolt is adjusted, thereby adjusting the assembly gap between the roller and the limiting rib.
In the embodiment with the eccentric bolt, an oil injection hole is provided on the eccentric bolt for injecting lubricating oil.
It will be appreciated that the end of the roller to which the joint is attached may also be attached by a combination of an eccentric bolt and an eccentric bushing.
Referring to fig. 1, in the present embodiment, the groove-shaped structure 21 on the limiting rib 2 is shaped such that when the flap 1 is switched from the landing state to the cruising state of the aircraft, the groove-shaped structure 21 can guide the motion track of the auxiliary support assembly, so that the auxiliary support assembly is accommodated in the groove-shaped structure 21. In particular, the channel-like structure 21 enables the auxiliary support assembly to follow the shape of the channel-like structure 21 by imparting a moment opposite to the trajectory of movement of the auxiliary support assembly. More specifically, referring to fig. 1, in the present embodiment, the groove-shaped structure 21 on the limiting rib 2 includes a first guide strip 211 and a second guide strip 212, the auxiliary support component follows the movement of the flap when the flap is switched from the landing state to the cruise state of the aircraft, and the first guide strip 211 and the second guide strip 212 are used for limiting the movement track of the auxiliary support component, so that the auxiliary support component moves in the preset movement track.
In this way, when the flap 1 is deformed in the vertical direction, the flap 1 can be guided by the first guide strip 211 and the second guide strip 212 into the slot-like structure 21, and the flap 1 can be prevented from being deformed and becoming unable to fit the slot-like structure 21.
The utility model also provides an aircraft, the aircraft includes as above the supplementary strutting arrangement of flap leading edge.
Finally, it should be pointed out that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit it. Although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention in its corresponding aspects.
Claims (10)
1. A flap leading edge auxiliary support device is used for auxiliary supporting of a flap (1) in a cruising state of an airplane; characterized in that the flap leading edge auxiliary supporting device comprises:
an auxiliary support assembly; the auxiliary support component is connected with the leading edge (11) of the airplane flap;
a spacing rib (2); the limiting rib (2) is arranged on the trailing edge of the airplane wing, and a groove-shaped structure (21) is arranged on the limiting rib (2); wherein,
the auxiliary support assembly is adapted to be received in a groove-like formation (21) of the spacing rib (2) when the aircraft is in the cruise condition.
2. The flap leading edge supplemental support device of claim 1, wherein the supplemental support assembly comprises:
a joint (3), one end of the joint (3) being connected to the aircraft flap leading edge (11);
a roller (4), the roller (4) being disposed on the other end of the joint (3).
3. The flap leading edge auxiliary support device according to claim 2, characterized in that the end of the roller (4) connected to the joint (3) is connected by an eccentric bolt.
4. The flap leading edge auxiliary supporting device as claimed in claim 3, characterized in that an adjusting pull tab is mounted on the bolt head of the eccentric bolt for adjusting the eccentric position of the eccentric bolt by rotating the eccentric bolt.
5. The flap leading edge auxiliary support device according to claim 1, characterized in that the shape of the groove-shaped structure (21) on the limiting rib (2) is suitable for enabling the groove-shaped structure (21) to guide the motion track of the auxiliary support assembly when the flap (1) is switched from the take-off and landing state to the cruise state of the aircraft, so that the auxiliary support assembly is accommodated in the groove-shaped structure (21).
6. The flap leading edge auxiliary supporting device as claimed in claim 3, characterized in that an oil filling hole is arranged on the eccentric bolt for filling lubricating oil.
7. The flap leading edge auxiliary support device according to claim 2, characterized in that the end of the roller connected to the joint is connected via an eccentric bushing (5).
8. The flap leading edge auxiliary support device according to claim 7, characterized in that an adjustment paddle (6) is mounted on the outer circumference of the eccentric bushing (5) for adjusting the eccentric position of the eccentric bushing (5) by rotating the eccentric bushing (5).
9. The flap leading edge auxiliary support device according to claim 5, characterized in that the groove-shaped structure (21) on the limiting rib comprises a first guide strip (211) and a second guide strip (212), when the flap (1) is switched from the take-off and landing state of the aircraft to the cruise state of the aircraft, the auxiliary support component follows the movement of the flap and has a preset movement track, and the first guide strip (211) and the second guide strip (212) are used for limiting the movement track of the auxiliary support component so that the auxiliary support component moves in the preset movement track.
10. An aircraft, characterized in that the aircraft comprises a flap leading edge auxiliary support device according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520614482.XU CN204937483U (en) | 2015-08-14 | 2015-08-14 | A kind of wing flap leading edge auxiliary support apparatus and there is its aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520614482.XU CN204937483U (en) | 2015-08-14 | 2015-08-14 | A kind of wing flap leading edge auxiliary support apparatus and there is its aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204937483U true CN204937483U (en) | 2016-01-06 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520614482.XU Active CN204937483U (en) | 2015-08-14 | 2015-08-14 | A kind of wing flap leading edge auxiliary support apparatus and there is its aircraft |
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| Country | Link |
|---|---|
| CN (1) | CN204937483U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109353490A (en) * | 2018-11-06 | 2019-02-19 | 中国科学院工程热物理研究所 | A kind of airscrew with wing flap device |
| CN109606638A (en) * | 2018-11-07 | 2019-04-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of sinking hinge type wing flap rocker supporting structure |
| CN110539882A (en) * | 2019-07-16 | 2019-12-06 | 中国航空研究院 | Method and device for optimizing flow at junction of leading edge bending flap and leading edge slat |
| CN114379769A (en) * | 2022-01-20 | 2022-04-22 | 中国商用飞机有限责任公司 | Slat supporting and limiting device |
-
2015
- 2015-08-14 CN CN201520614482.XU patent/CN204937483U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109353490A (en) * | 2018-11-06 | 2019-02-19 | 中国科学院工程热物理研究所 | A kind of airscrew with wing flap device |
| CN109606638A (en) * | 2018-11-07 | 2019-04-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of sinking hinge type wing flap rocker supporting structure |
| CN110539882A (en) * | 2019-07-16 | 2019-12-06 | 中国航空研究院 | Method and device for optimizing flow at junction of leading edge bending flap and leading edge slat |
| CN110539882B (en) * | 2019-07-16 | 2021-07-16 | 中国航空研究院 | Method and device for optimizing flow at junction of leading edge bending flap and leading edge slat |
| CN114379769A (en) * | 2022-01-20 | 2022-04-22 | 中国商用飞机有限责任公司 | Slat supporting and limiting device |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |