CN215399301U - Airfoil surface structure, wing and aircraft - Google Patents
Airfoil surface structure, wing and aircraft Download PDFInfo
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- CN215399301U CN215399301U CN202120928804.3U CN202120928804U CN215399301U CN 215399301 U CN215399301 U CN 215399301U CN 202120928804 U CN202120928804 U CN 202120928804U CN 215399301 U CN215399301 U CN 215399301U
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- sandwich layer
- airfoil
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Abstract
The utility model discloses an airfoil structure, an airfoil and an aircraft, wherein the aircraft comprises the airfoil structure, the airfoil structure comprises a sandwich layer arranged in a coating space of a skin, the skin comprises a forming structure, a cavity is formed between the forming structure and the tip of the skin, the sandwich layer comprises a first sandwich layer and a second sandwich layer which are positioned at two sides of the forming structure, the second sandwich layer is arranged in the cavity, and the core material of the second sandwich layer is a foam filling molding structure. According to the airfoil structure, the cavity is formed in the tip end area of the skin through the shaping structure, and the second sandwich layer is formed in the cavity in a foaming and filling mode, so that the risk of cracking of the sandwich layer in the tip end area is effectively reduced, the structural reliability of the airfoil structure is improved, and the reliability of an airfoil and an aircraft is improved.
Description
Technical Field
The utility model relates to the technical field of aerospace, in particular to an airfoil structure, a wing and an aircraft.
Background
The composite material sandwich structure airfoil has the structural characteristics of light weight and high strength, and is widely applied to the field of aviation.
As shown in fig. 1, the airfoil structure 100 made of the conventional composite material is a glued structure of an upper skin 121, a lower skin 122, a tail end skin 123 and a sandwich layer 110, the upper skin 121, the lower skin 122 and the tail end skin 123 sandwich the sandwich layer 110, and the upper skin 121, the lower skin 122 and the tail end skin 123 are glued together, wherein, as shown in fig. 2, the edge local thickness at a tip 111 (corresponding to the edge position of the wing) of the sandwich layer 110 is smaller (less than 3 mm), but the sandwich layer 110 in a honeycomb structure is prone to collapse and crack at the edge local position of the tip 111, which seriously affects the appearance and the gluing strength of the airfoil.
SUMMERY OF THE UTILITY MODEL
In view of the above problems, the present invention provides an airfoil, so as to change the tip characteristics of a sandwich layer in a skin, reduce the risk of tip collapse cracking, improve the connection reliability between the skin and the sandwich layer of a tip part of an airfoil structure, and guarantee the structural characteristics of the airfoil structure.
According to an aspect of the utility model, there is provided an airfoil structure comprising:
a skin comprising a shaped structure with a cavity formed between the shaped structure and a tip of the skin;
a sandwich layer arranged in the coating space of the skin and comprising a first sandwich layer and a second sandwich layer which are positioned at two sides of the forming structure, wherein,
the second sandwich layer is located in the cavity, and a core material of the second sandwich layer is of a foam filling forming structure.
Optionally, the skin is an integrally molded structure, and the tip of the skin is structurally continuous.
Optionally, the skin is a carbon fiber skin, the sandwich layer is an aramid honeycomb core material, and the second sandwich layer is an epoxy foam rubber foam structure.
Optionally, the skin is a cyanate ester quartz fiber prepreg, the sandwich layer is a polymethacrylimide foam core material, and the structure of the second sandwich layer is a cyanate ester foam rubber foam structure.
Optionally, the shape of the cross-section of the shaping structure is curved with the convex outer surface facing the tip of the airfoil structure.
Optionally, the shape of the cross-section of the shaping structure is V-shaped with the V-shaped tip facing the tip of the airfoil structure.
Optionally, the cavity is a metal mold forming structure.
Optionally, the tip of the airfoil structure is an acute angle structure.
According to another aspect of the utility model, there is provided an airfoil comprising an airfoil structure provided according to the utility model.
According to a further aspect of the utility model, there is provided an aircraft comprising a wing provided according to the utility model.
The airfoil structure provided by the utility model comprises a sandwich layer arranged in a coating space of a skin, wherein the skin comprises a forming structure, a cavity is formed between the forming structure and the tip of the skin, the sandwich layer comprises a first sandwich layer and a second sandwich layer which are positioned at two sides of the forming structure, the second sandwich layer is arranged in the cavity, and the core material of the second sandwich layer is a foam filling molding structure. According to the airfoil structure, the cavity is formed in the tip end area of the skin through the shaping structure, and the second sandwich layer is formed in the cavity in a foaming and filling mode, so that the risk of cracking of the sandwich layer in the tip end area is effectively reduced, the structural reliability of the airfoil structure is improved, and the reliability of an airfoil and an aircraft is improved.
The wing provided by the utility model comprises the wing surface structure provided by the utility model, the structural stability is high, and the reliability of the wing is improved.
The aircraft provided by the utility model comprises the wing, the structural characteristics of the wing are guaranteed, and the navigation safety of the aircraft is improved.
Drawings
The above and other objects, features and advantages of the present invention will become more apparent from the following description of the embodiments of the present invention with reference to the accompanying drawings, in which:
FIG. 1 shows a schematic structural view of an airfoil configuration according to the prior art;
FIG. 2 illustrates a partial cross-sectional structural schematic of an airfoil structure according to the prior art;
FIG. 3 illustrates a partial cross-sectional structural view of an airfoil structure according to an embodiment of the utility model;
FIGS. 4-6 illustrate various structural schematics in a process flow for preparing the airfoil structure shown in FIG. 3.
Detailed Description
Various embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. Like elements in the various figures are denoted by the same or similar reference numerals. For purposes of clarity, the various features in the drawings are not necessarily drawn to scale.
The following detailed description of embodiments of the present invention is provided in connection with the accompanying drawings and examples.
FIG. 3 illustrates a partial cross-sectional structural view of an airfoil structure according to an embodiment of the utility model.
As shown in fig. 3, the airfoil structure 200 according to the embodiment of the present invention includes a first sandwich layer 210 and a second sandwich layer 211 disposed inside a skin 220, and the first sandwich layer 210 and the second sandwich layer 211 are spaced by a forming structure 221 and fixed in two cavities formed by the skin 220 and the forming structure 221, respectively, so as to be integrally fixed.
In this embodiment, the shape of the cross section of the forming structure 221 is a V-shape, the V-shape tip faces the tip of the airfoil structure 200 and is consistent with the tip of the airfoil structure 200, the outer surface of the V-shape corresponds to the tail end of the second sandwich layer 211, the inner surface of the V-shape forming structure 221 corresponds to the tip of the first sandwich layer 210, and the forming structure 221 and the skin 220 are an integrated molding structure, which can ensure the structural stability of the forming structure 221, and the structure of the tip facing the tip of the airfoil structure 200 can improve the bearing continuity and the structural strength. In an alternative embodiment, the shape of the cross-section of the shaping structure 221 is arcuate, with the convex outer surface of the arc facing in line with the tip of the airfoil structure 200. In an alternative embodiment, the shape of the cross-section of the shaping structure 221 is a straight structure, oriented perpendicular to the tip of the airfoil structure 200. In an alternative embodiment, the cross-sectional shape of the shaping structure 221 is a kidney shape, with the outer surface of the kidney protruding towards the first core layer 210.
The forming structure 221 simultaneously provides load bearing for the tip of the first sandwich layer 210 and the tail of the second sandwich layer 211, ensures the continuity of the first sandwich layer 210 and the second sandwich layer 211, and ensures the continuous load bearing capability of the airfoil structure 200.
The first sandwich layer 210 corresponds to a main body part of a sandwich layer of the airfoil structure 200, the second sandwich layer 211 corresponds to an edge tip of the sandwich layer of the airfoil structure 200, the first sandwich layer 210 and the second sandwich layer 211 are separated through the forming structure 221, load of the airfoil structure 200 can be dispersed, cracking risk of the tip sandwich layer of the airfoil structure 200 is effectively reduced, structural characteristics of the airfoil structure 200 are guaranteed, and reliability and service life of the airfoil structure 200 are improved. Wherein the first sandwich layer 210 is a honeycomb core, and the second sandwich layer 211 is a foam core.
In this embodiment, the skin 220 of the airfoil structure 200 is an integrally formed structure, the integral structure of the skin 220 has no glue joint surface, the fiber structure at the tip of the skin 220 is continuous, the integrity of the fiber structure is high, and the skin structure has better adaptability in the use occasions of higher vibration fatigue loads, thereby effectively reducing the layering risk of the skin and further improving the reliability of the airfoil structure 200.
In optional embodiment 1, the skin 220 is a carbon fiber skin, the first sandwich layer 210 and the second sandwich layer 211 are both aramid honeycomb core materials, the structure of the second sandwich layer 211 is a foamed structure of the aramid honeycomb core materials, the aramid honeycomb and the carbon fiber are good in compounding performance, the integrity of the carbon fiber skin is high, and the carbon fiber skin is good in adaptation to use occasions with high vibration fatigue loads.
In an alternative embodiment 2, the skin 220 is a cyanate ester quartz fiber prepreg, and both the first sandwich layer 210 and the second sandwich layer 211 are Polymethacrylimide (PMI) foam core materials, so that an airfoil structure with good wave-transmitting performance can be obtained, and the airfoil structure can be used for a stealth wing.
FIGS. 4-6 illustrate various structural schematics in a process flow for preparing the airfoil structure shown in FIG. 3.
As shown in fig. 4, the airfoil structure 200 according to the embodiment of the present invention completes the formation of the integrated skin 220 and the first sandwich layer 210 by using the mold 31, wherein the tip of the mold 31 is a male mold, and the tail end of the mold 31 is a female mold, and the tip of the skin 220 and the protruding outer surface of the forming structure 221 are respectively formed in the solidification formation. In this embodiment, mold 31 is a metal mold, and has poor compatibility with skin 220, thereby facilitating demolding.
After the skin 220, the forming structure 221 and the first sandwich layer 210 are integrally cured and molded, the mold 31 is removed, and the cavity 203 is formed at the position of the second sandwich layer 211, so that the structure shown in fig. 5 is formed.
Then, as shown in fig. 6, the cavity 203 is partially filled with the foam rubber 32, an external female die (not shown in the figure) is used to constrain the shape of the skin 220, so as to maintain the shape of the cavity 203, and the foam rubber 32 is foamed inside the cavity 203 to fill the cavity 203 entirely, so as to obtain the second sandwich layer 211 of the foam-filled molding structure, and obtain the airfoil structure 200 shown in fig. 3. In optional embodiment 1, the foam adhesive 32 is an epoxy foam adhesive, and in optional embodiment 2, the foam adhesive 32 is a cyanate ester foam adhesive.
The airfoil structure comprises the sandwich layer arranged in the coating space of the skin, the skin comprises the forming structure, a cavity is formed between the forming structure and the tip of the skin, the sandwich layer comprises the first sandwich layer and the second sandwich layer which are positioned on two sides of the forming structure, the second sandwich layer is arranged in the cavity, and the core material of the second sandwich layer is a foam filling forming structure, so that the fracture risk of the sandwich layer in the tip area is effectively reduced, and the structural reliability of the airfoil structure is improved.
The utility model also provides a wing and an aircraft, wherein the aircraft comprises the wing, the wing comprises the airfoil structure provided by the utility model, the structural reliability of the wing is improved, and the navigation safety and the functional structure reliability of the aircraft are improved.
In accordance with the embodiments of the present invention as set forth above, these embodiments are not exhaustive and do not limit the utility model to the precise embodiments described. Obviously, many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the utility model and the practical application, to thereby enable others skilled in the art to best utilize the utility model and various embodiments with various modifications as are suited to the particular use contemplated. The utility model is limited only by the claims and their full scope and equivalents.
Claims (10)
1. An airfoil structure, comprising:
a skin comprising a shaped structure with a cavity formed between the shaped structure and a tip of the skin;
a sandwich layer arranged in the coating space of the skin and comprising a first sandwich layer and a second sandwich layer which are positioned at two sides of the forming structure, wherein,
the second sandwich layer is located in the cavity, and a core material of the second sandwich layer is of a foam filling forming structure.
2. The airfoil structure according to claim 1,
the skin is an integrally formed structure, and the tip end of the skin is continuous in structure.
3. The airfoil structure according to claim 1,
the skin is carbon fiber skin, the sandwich layer is aramid fiber honeycomb core, the second sandwich layer is epoxy foaming glue foam structure.
4. The airfoil structure according to claim 1,
the skin is cyanate ester quartz fiber prepreg, the sandwich layer is polymethacrylimide foam core material, and the structure of the second sandwich layer is cyanate ester foam rubber foam structure.
5. The airfoil structure according to claim 1,
the shape of the cross-section of the shaping structure is curved and the convex outer surface faces the tip of the airfoil structure.
6. The airfoil structure according to claim 1,
the cross-sectional shape of the shaping structure is V-shaped, and the V-shaped tip is towards the tip of the airfoil structure.
7. The airfoil structure according to claim 1,
the cavity is of a metal mold forming structure.
8. The airfoil structure according to claim 1,
the tip of the airfoil structure is an acute angle structure.
9. An airfoil comprising the airfoil structure of any one of claims 1 to 8.
10. An aircraft comprising a wing according to claim 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120928804.3U CN215399301U (en) | 2021-04-30 | 2021-04-30 | Airfoil surface structure, wing and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120928804.3U CN215399301U (en) | 2021-04-30 | 2021-04-30 | Airfoil surface structure, wing and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215399301U true CN215399301U (en) | 2022-01-04 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120928804.3U Active CN215399301U (en) | 2021-04-30 | 2021-04-30 | Airfoil surface structure, wing and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215399301U (en) |
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2021
- 2021-04-30 CN CN202120928804.3U patent/CN215399301U/en active Active
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