CN218751357U - Anti-collision sleeve for protecting aircraft skin edge - Google Patents
Anti-collision sleeve for protecting aircraft skin edge Download PDFInfo
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- CN218751357U CN218751357U CN202223254870.0U CN202223254870U CN218751357U CN 218751357 U CN218751357 U CN 218751357U CN 202223254870 U CN202223254870 U CN 202223254870U CN 218751357 U CN218751357 U CN 218751357U
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- collision sleeve
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Abstract
The utility model discloses a protection aircraft skin is anticollision cover for edge belongs to aircraft skin protection technical field. The anti-collision sleeve is a multi-fold-angle structure formed by a plurality of clamping edges, the profile of the anti-collision sleeve is matched with the profile of the edge of an aircraft skin, a clamping groove is formed in the inner side of the anti-collision sleeve, the clamping groove is a structure gradually reduced from the groove bottom to the opening, the upper surface and the lower surface of the anti-collision sleeve incline inwards along with the clamping groove, the outer side of the anti-collision sleeve is provided with an arc surface, and the anti-collision sleeve is integrally formed by an elastomer material. The utility model provides a current aircraft skin edge be difficult to the problem of protection, adopt elastomer material to make the corresponding anticollision cover of shape, its simple structure, easily deposit, the use cost that has significantly reduced to the applicable same anticollision cover of aircraft skin to the different thickness of same shape.
Description
Technical Field
The utility model belongs to the technical field of aircraft skin protection, in particular to protection aircraft skin is anticollision cover for edge.
Background
The aircraft skin is a dimensional member which surrounds the exterior of the aircraft framework structure and is fixed to the framework by adhesives or rivets to form the aerodynamic profile of the aircraft. Damage to the skin material is one of the most severe forms of damage to aircraft, which seriously threatens the safety of flight. The use scene of aircraft covering is complicated changeable, and operating personnel very easily makes it receive the damage and collide with in demolising, transport, storage and the installation, and the covering is extremely important component to the aircraft, in case impaired, has very big potential safety hazard, and the fibrous layer damage on its surface can not reverse simultaneously, finally causes huge economic loss.
The aircraft skin has no regular shape, and has different shapes according to different parts of the framework of the aircraft, wherein part of the skin has edges with unique shapes, and the edges of the skin are easily worn when the skin is used, transported or stored, so that the edges of the aircraft skin need to be protected and treated.
The measure of protection covering edge uses disposable foam pipe at present, twines it and glues firmly fixedly with modes such as sticky tape after the covering edge is supplementary, but self no elasticity and add the holding power, and fall the sediment easily, not only causes a large amount of discarded rubbish after tearing it open and getting it, can't reuse, also lifts covering surface fiber layer easily, all wraps up back use cost too high with aircraft covering edge, also is difficult to deposit.
Therefore, a protective sheath which can effectively protect the edge of the skin and can be recycled is needed.
Disclosure of Invention
For solving the technical problem, an object of the utility model is to provide a protection aircraft skin is anticollision cover for edge has effectively protected the edge of aircraft skin, avoids itself to the skin and to the injury that operating personnel caused, and its convenient to use, easily collection deposit, circulated use simultaneously, use cost is low.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
the utility model provides a protection aircraft skin is crashproof cover for edge, crashproof cover is many dog-ear structures that many centre gripping limits constitute, and the profile and the marginal profile phase-match in aircraft skin of this crashproof cover, the inboard of crashproof cover is opened there is the centre gripping groove, the centre gripping groove is the structure that reduces gradually to the opening by the tank bottom, and the upper surface and the lower surface of crashproof cover incline to the inboard along with the centre gripping groove, the crashproof cover outside sets up to the arc surface, and the crashproof cover wholly adopts elastomer material integrated into one piece. The cross section of the corner sleeve is of a water-drop-like shape, and the larger end of the corner sleeve can play a role in heightening and increasing the skin clearance when skins are stacked.
Further: the clamping groove equally divides the inner side into an upper inner side surface and a lower inner side surface, and the ratio of the width of the upper inner side surface or the lower inner side surface to the opening width of the clamping groove is 9.
Further, the method comprises the following steps: the side wall of the clamping groove is a frosted surface.
Further: and corresponding concave or convex parts are arranged on the inner sides of the folded corner edges of the anti-collision sleeves according to the convex or concave parts of the edges of the skins. The convex or concave part of the edge of the aircraft skin is flexibly and effectively protected.
Further: each right-angle side of the anti-collision sleeve is set to be a round angle. Each right-angle side sets up to the fillet, and is more pleasing to the eye in the vision, has improved the security after getting rid of sharp limit.
Further: the upper surface and the lower surface are inclined inward at an angle α of 10 °.
Further: the width of the opening of the clamping groove is 1.5-2 mm, the width of the groove bottom is 2-2.5 mm, and the anti-collision sleeve is suitable for skins with the edge thickness of 2 +/-0.5 mm. The same crash sleeve can be used for aircraft skins of the same shape and different thicknesses.
Further: any clamping edge of the anti-collision sleeve is independently arranged for use.
Further: the Shore hardness of the elastomer material is 40-60HD. The elastic material has high flexibility and flexibility, and simultaneously has excellent anti-collision performance, corrosion resistance and long service life.
Further: the surface of anticollision cover is provided with the warning layer. The use of the obvious color can be easily found by operators and is not easy to lose.
Compared with the prior art, the technical scheme of the utility model following beneficial effect has:
1) The utility model has independent protection function for the special edge of the aircraft skin, and the corresponding anti-collision sleeves are arranged in different edge shapes;
2) The utility model adopts the elastomer material with high flexibility and high flexibility, which not only has high self-holding power and strong impact resistance, but also can be applied to the same anti-collision sleeve for the aircraft skins with the same shape and different thicknesses;
3) The utility model has simple structure, low use cost, easy storage and flexible use; furthermore the utility model discloses a centre gripping inslot lateral wall sets up to the frosting, can effectively increase the frictional force of anticollision cover and covering through this frosting for the combination of anticollision cover and covering is inseparabler.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention, and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
Fig. 1 is a schematic structural diagram of an anti-collision sleeve for protecting an edge of an aircraft skin provided in embodiment 1 of the present invention.
Fig. 2 is a schematic structural diagram of an anti-collision sleeve for protecting the edge of an aircraft skin provided in embodiment 2 of the present invention.
Fig. 3 is a schematic structural diagram of an anti-collision sleeve for protecting an edge of an aircraft skin provided in embodiment 3 of the present invention.
Fig. 4 is a schematic structural diagram of an anti-collision sleeve for protecting an edge of an aircraft skin provided in embodiment 4 of the present invention.
Fig. 5 is a schematic cross-sectional view of an anti-collision sleeve for protecting the edge of an aircraft skin provided by embodiments 1 to 4 of the present invention
The labels in the figure are respectively:
1. the clamping groove, 2, the arc surface, 3, the upper surface, 4, the lower surface, 5, the upper inner side surface and 6, the lower inner side surface.
Detailed Description
To make the objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention are clearly and completely described below, and it is obvious that the described embodiments are some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work all belong to the protection scope of the present invention. Thus, the detailed description of the embodiments of the present invention provided below is not intended to limit the scope of the claimed invention, but is merely representative of selected embodiments of the present invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it may not be further defined and explained in subsequent figures.
Example 1:
as shown in fig. 5, the anti-collision sleeve for protecting the edge of the aircraft skin is a multi-fold angle structure formed by a plurality of clamping edges, the outline of the anti-collision sleeve is matched with the outline of the edge of the aircraft skin, a clamping groove 1 is formed in the inner side of the anti-collision sleeve, the clamping groove 1 is a structure gradually reduced from the bottom of the groove to an opening, the upper surface 3 and the lower surface 4 of the anti-collision sleeve incline inwards along with the clamping groove 1, an arc surface 2 is arranged on the outer side of the anti-collision sleeve, the anti-collision sleeve is integrally formed by adopting an elastomer material, the cross section of the corner sleeve is in a water-drop-like shape, and the larger end of the anti-collision sleeve can play a role of increasing the skin gap by raising the height when the skins are stacked;
furthermore, the clamping groove 1 equally divides the inner side into an upper inner side surface 5 and a lower inner side surface 6, and the ratio of the width of the upper inner side surface 5 or the lower inner side surface 6 to the opening width of the clamping groove 1 is 9; the side wall of the clamping groove 1 is provided with a frosted surface; corresponding recesses or protrusions are arranged on the inner sides of the folded corner edges of the anti-collision sleeves according to the protrusions or the recessed parts of the edges of the skins; each right-angle side of the anti-collision sleeve is provided with a round angle; the angle alpha of the inward inclination of the upper surface 3 and the lower surface 4 is 10 degrees; the width of the opening of the clamping groove 1 is 1.5-2 mm, and the width of the groove bottom is 2-2.5 mm; the anti-collision sleeve is suitable for a skin with the edge thickness of 2 +/-0.5 mm; the Shore hardness of the elastomer material is 40-60HD, and a silica gel material is preferred; the color of the anti-collision sleeve is selected from the colors which are in sharp contrast with the environmental color.
As shown in fig. 1, the structure and the profile of the crash sleeve in this embodiment correspond to the skin edge profile of the lower fender of the left and right pillars of the aircraft, wherein the opening width of the clamping groove 1 is 1.5mm, the groove bottom width is 2mm, the ratio of the width of the upper inner side surface 5 or the lower inner side surface 6 to the opening width of the clamping groove 1 is 9; the anti-collision sleeve is suitable for skins with the edge thickness of 2 +/-0.5 mm, the outer surface of the anti-collision sleeve is provided with a red warning layer, silica gel is selected as a material of the anti-collision sleeve, and the Shore hardness of the anti-collision sleeve is 40HD.
Example 2:
as shown in fig. 2, the structural shape of the anti-collision sleeve in this embodiment corresponds to the shape of the skin edge of the left and right wheel guard plates of the aircraft, corresponding recesses or protrusions are provided on the inner side of the bevel edge according to the protrusions or recesses of the skin edge, wherein the sidewall of the clamping groove 1 is set as a frosted surface, the friction force is increased on the original basis, the opening width of the clamping groove 1 is 1.8mm, the groove bottom width is 2.3mm, the ratio of the width of the upper inner side surface 5 or the lower inner side surface 6 to the opening width of the clamping groove 1 is 9, that is, the widths of the upper inner side surface 5 and the lower inner side surface 6 are both 4.1mm (1 decimal is reserved), the angle α of the inward inclination of the upper surface 3 and the lower surface 4 is 10 °, the anti-collision sleeve is suitable for the skin with the edge thickness of 2 ± 0.5mm, the outer surface of the anti-collision sleeve is provided with a bright yellow warning layer, the material of the anti-collision sleeve is selected from silica gel, and the shore hardness of the anti-collision sleeve is 50HD.
Example 3:
as shown in fig. 3, the structural contour of the anti-collision sleeve in this embodiment corresponds to the skin edge contour of the front protection plate of the aircraft, wherein the opening width of the clamping groove 1 is 2mm, the groove bottom width is 2.5mm, the clamping groove tightly clamps the skin edge by friction, the ratio of the width of the upper inner side surface 5 or the lower inner side surface 6 to the opening width of the clamping groove 1 is 9.
Example 4:
as shown in fig. 4 and 5, an anti-collision sleeve for protecting the edge of an aircraft skin is characterized in that any one of the corner edges of the anti-collision sleeve is independently arranged and used and matched with the straight edge profile of the edge of the aircraft skin, a clamping groove 1 is formed in the inner side of the anti-collision sleeve, the anti-collision sleeve is clamped on the edge of the aircraft skin through the clamping groove 1, the clamping groove 1 is of a structure with the gradually reduced size from the bottom to the opening, the clamping groove 1 is installed by using friction force, the upper surface 3 and the lower surface 4 of the anti-collision sleeve incline inwards along with the clamping groove 1, the outer side of the anti-collision sleeve is provided with an arc surface 2, the anti-collision sleeve is integrally formed by adopting an elastomer material, the cross section of the corner sleeve is of a water-drop-like shape, and the larger end of the anti-collision sleeve can play a role of increasing the skin gap when the aircraft skin is stacked;
furthermore, the clamping groove 1 equally divides the inner side into an upper inner side surface 5 and a lower inner side surface 6, and the ratio of the width of the upper inner side surface 5 or the lower inner side surface 6 to the opening width of the clamping groove 1 is 9; the side wall of the clamping groove 1 is provided with a frosted surface; corresponding recesses or protrusions are arranged on the inner sides of the folded corner edges of the anti-collision sleeves according to the protrusions or the recessed parts of the edges of the skins; each right-angle side of the anti-collision sleeve is provided with a round angle; the angle alpha of the inward inclination of the upper surface 3 and the lower surface 4 is 10 degrees; the width of the opening of the clamping groove 1 is 1.5-2 mm, and the width of the groove bottom is 2-2.5 mm; the anti-collision sleeve is suitable for a skin with the edge thickness of 2 +/-0.5 mm; the outer surface of the anti-collision sleeve is provided with a warning layer, the anti-collision sleeve is made of silica gel, and the Shore hardness of the anti-collision sleeve is 40-60HD.
The anti-collision sleeve in this embodiment, but arbitrary dog-ear limit exclusive use, be a horizontal linear structure promptly, with the straight flange phase-match at aircraft skin edge, its length includes arbitrary required length, wherein set up centre gripping groove 1 lateral wall into frosting, the opening width of centre gripping groove 1 is 1.7mm, the tank bottom width is 2.4mm, the width of last medial surface 5 or lower medial surface 6 is 9 with the opening width ratio of centre gripping groove 1, it is 3.8mm (reservation 1 decimal place) to go up the width of medial surface 5 and lower medial surface 6 promptly, the angle alpha that upper surface 3 and lower surface 4 inboard slope is 10, the anti-collision sleeve is applicable to the skin that the edge thickness is 2 ± 0.5mm, the surface of anti-collision sleeve is provided with the warning layer, the material of anti-collision sleeve chooses for use silica gel, and its shao shi hardness is 45.
In practical operation, the anti-collision sleeves of the above embodiments 1 to 4 are slowly and carefully sleeved on the edges of the skins of the aircraft to be tightly clamped, a plurality of skins sleeved with the anti-collision sleeves are carefully stacked and stored, and gaps are left among the skins due to the anti-collision sleeves, so that the skins are prevented from being scratched due to close contact.
The above embodiments 1 to 4 only list the crash sleeves for the skin of partial specification, which do not represent the above, and for the edges of the skin of the airplane with different profiles, the corresponding crash sleeves are provided.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.
In the present disclosure, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may comprise direct contact between the first and second features, or may comprise contact between the first and second features not directly. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. The first feature being "under," "below," and "beneath" the second feature includes the first feature being directly under and obliquely below the second feature, or merely indicates that the first feature is at a lower level than the second feature.
The above is only a preferred embodiment of the present invention, and it should be noted that the above preferred embodiment should not be considered as limiting the present invention, and the protection scope of the present invention should be subject to the scope defined by the claims. It will be apparent to those skilled in the art that various modifications and enhancements can be made without departing from the spirit and scope of the invention, and such modifications and enhancements are intended to be within the scope of the invention.
Claims (10)
1. The utility model provides a protection aircraft skin is anticollision cover for edge, its characterized in that, anticollision cover is many dog-ear structures that many centre gripping limits constitute, and the profile phase-match at this anticollision cover's profile and aircraft skin edge, the inboard of anticollision cover is opened there is the centre gripping groove, the centre gripping groove is the structure that reduces gradually to the opening by the tank bottom, and the upper surface and the lower surface of anticollision cover incline to the inboard along with the centre gripping groove, the anticollision cover outside sets up to the arc surface, and the anticollision cover wholly adopts elastomer material integrated into one piece.
2. The anti-collision sleeve for protecting the edge of the skin of the airplane as claimed in claim 1, wherein the clamping groove divides the inner side equally into an upper inner side surface and a lower inner side surface, and the ratio of the width of the upper inner side surface or the lower inner side surface to the opening width of the clamping groove is 9.
3. The crash sleeve as defined in claim 1, wherein said sidewall of said grip groove is provided with a frosted surface.
4. The anti-collision sleeve for protecting the edge of the skin of the aircraft as claimed in claim 1, wherein corresponding recesses or protrusions are arranged on the inner side of the dog-ear edge of the anti-collision sleeve according to the protrusions or recesses of the edge of the skin.
5. The crash sleeve as defined in claim 1, wherein each right-angled edge of said crash sleeve is rounded.
6. A crash sleeve for protecting an edge of an aircraft skin as claimed in claim 1, wherein said upper and lower surfaces are inclined inwardly at an angle α of 10 °.
7. The crash sleeve as claimed in claim 1, wherein the width of the opening of the holding groove is 1.5-2 mm, the width of the groove bottom is 2-2.5 mm, and the crash sleeve is suitable for a skin with an edge thickness of 2 ± 0.5 mm.
8. The crash sleeve as claimed in claim 1, wherein any one of the clamping edges of the crash sleeve is used independently.
9. The impact sleeve of claim 1, wherein said elastomeric material has a shore hardness of 40-60HD.
10. The crash sleeve as claimed in claim 1, wherein a warning layer is provided on an outer surface of the crash sleeve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223254870.0U CN218751357U (en) | 2022-12-06 | 2022-12-06 | Anti-collision sleeve for protecting aircraft skin edge |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223254870.0U CN218751357U (en) | 2022-12-06 | 2022-12-06 | Anti-collision sleeve for protecting aircraft skin edge |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218751357U true CN218751357U (en) | 2023-03-28 |
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ID=85680422
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202223254870.0U Active CN218751357U (en) | 2022-12-06 | 2022-12-06 | Anti-collision sleeve for protecting aircraft skin edge |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218751357U (en) |
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2022
- 2022-12-06 CN CN202223254870.0U patent/CN218751357U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20230511 Address after: 310000 Room 706, Block B, No. 33, Yueming Road, Xixing Street, Binjiang District, Hangzhou, Zhejiang Patentee after: Jingxing Technology (Hangzhou) Co.,Ltd. Address before: 310000 Room 706, Block B, No. 33, Yueming Road, Xixing Street, Binjiang District, Hangzhou, Zhejiang Patentee before: Jingxing Technology (Hangzhou) Co.,Ltd. Patentee before: Cao Hu Patentee before: Jiang Hao |
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| TR01 | Transfer of patent right |