Wing structure with enhanced near-field scattering characteristic, manufacturing method and aircraft

Abstract

The invention provides a near-field scattering characteristic enhanced wing structure, a manufacturing method and an aircraft, the wing structure comprises a wing skeleton, a skin assembly, a scattering enhancement assembly and foaming foam, the wing skeleton comprises a spar and a rib, and the spar and the rib are both made of metal materials; the skin assembly comprises an upper skin and a lower skin which are both made of wave-transparent materials. The scattering enhancement assembly comprises a first metal plate, a plurality of second metal plates and a plurality of third metal plates, the first metal plate is laid in a separation cavity formed by the wing spar and the wing rib, and the second metal plates and the third metal plates are arranged on and / or under the first metal plate in a crossed combination mode; the foaming foam forms a whole with the first metal plate, the second metal plate and the third metal plate after being heated and expanded. According to the technical scheme, the technical problem that in the prior art, a small-size target aircraft with a conventional structure is small in aircraft body scattering characteristic under the near-field condition, and it is difficult to simulate the near-field characteristic of a large-size aircraft is solved.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to a wing structure with enhanced near-field scattering characteristics, a manufacturing method and an aircraft. Background Art

[0002] Target drones are military aircraft used as shooting training targets. They are often used to simulate enemy aircraft or incoming missiles during weapon tests and to provide imaginary targets for the shooting of various types of missiles and artillery.

[0003] Air defense weapons generally use laser or infrared optical fuses to track or attack enemy aircraft. Target aircraft equipped with Luneberg spheres, radiation sources and other payloads can be used to simulate large-scale, high-value enemy aircraft in the far field. However, in the near field, due to the small size of the target aircraft, simulation devices such as Luneberg spheres cannot play a role in scattering enhancement. Therefore, it is difficult for conventional small-sized target aircraft to simulate large-sized aircraft in the near field. In missile shooting training, when large-sized aircraft are required in near-field conditions, large-size or full-size methods are generally used. However, the production and manufacturing of large-size or full-size target aircraft is relatively costly and has a low cost-effectiveness ratio, which makes it difficult to meet the needs of weapons and equipment scientific research and training. Summary of the invention

[0004] The present invention provides a wing structure with enhanced near-field scattering characteristics, a manufacturing method and an aircraft, which can solve the technical problem in the prior art that the body scattering characteristics of a conventional small-sized target aircraft are relatively small in the near-field situation and it is difficult to meet the requirements of simulating the near-field characteristics of a large-sized aircraft.

[0005] According to one aspect of the present invention, there is provided a wing structure with enhanced near-field scattering characteristics, the wing structure comprising:

[0006] The wing frame includes a wing spar and a wing rib, and both the wing spar and the wing rib are made of metal materials;

[0007] The skin assembly includes an upper skin and a lower skin. The upper skin is laid on the upper surface of the wing frame, and the lower skin is laid on the lower surface of the wing frame. Both the upper skin and the lower skin are made of wave-transmitting materials.

[0008] A scattering enhancement component, the scattering enhancement component comprises a first metal plate, a plurality of second metal plates and a plurality of third metal plates, the first metal plate is laid in a compartment formed by a wing spar and a wing rib, and the plurality of second metal plates and the plurality of third metal plates are arranged on and / or below the first metal plate in a cross-combination manner to form an angle reflection structure, and the scattering characteristics are enhanced by the angle reflection structure;

[0009] The foaming foam is arranged in the compartment formed by the first metal plate, the second metal plate and the third metal plate to form a whole with the first metal plate, the second metal plate and the third metal plate after being expanded by heat. The foaming foam is used to fix and support the first metal plate, the second metal plate and the third metal plate and improve the strength of the wing structure.

[0010] Furthermore, the wing beam and the wing ribs are made of aluminum alloy, the first metal plate, the second metal plate and the third metal plate are all aluminum plates, and the wave-transmitting material is a glass fiber composite material.

[0011] Furthermore, mounting holes are provided on the wing beams and wing ribs, and the mounting holes are used to install and fix the scattering enhancement components.

[0012] Furthermore, the first metal plate, the second metal plate and the third metal plate are all provided with connecting holes, and the foamed foams in each compartment are connected into a whole through the connecting holes after being expanded by heat.

[0013] Furthermore, the thickness of the upper skin and the lower skin ranges from 0.6 mm to 1 mm, and the thickness of the aluminum plate ranges from 0.3 mm to 0.5 mm.

[0014] According to another aspect of the present invention, there is provided a method for manufacturing the wing structure proposed in the present invention, the manufacturing method comprising:

[0015] S1, placing the wave-transmitting material in a hot press pot for hot pressing to obtain an upper skin and a lower skin;

[0016] S2, using a machine tool to obtain a wing spar and a wing rib made of metal, and connecting and fixing the wing spar and the wing rib to obtain a wing skeleton;

[0017] S3, arranging the second metal plate and the third metal plate on and / or below the first metal plate in a cross combination form to form a corner reflection structure;

[0018] S4, placing the corner reflective structure in a foaming mold, cutting the foam into required sizes and placing them in the compartments formed by the first metal plate, the second metal plate and the third metal plate, respectively, and heating the foam so that the foam expands due to the heat and forms a whole with the corner reflective structure;

[0019] S5, connecting and fixing the corner reflection structure processed by S4 to the wing frame;

[0020] S6, the upper skin and the lower skin are respectively attached to the wing frame processed in S5 by adhesive films, and hot pressing is performed by hot pressing to make the upper skin, the lower skin, the wing frame and the corner reflection structure bonded and cured into an integral wing structure.

[0021] Furthermore, the wing beam and the wing ribs are made of aluminum alloy, the first metal plate, the second metal plate and the third metal plate are all aluminum plates, and the wave-transmitting material is a glass fiber composite material.

[0022] Furthermore, connecting holes are provided on the first metal plate, the second metal plate and the third metal plate, and heating the foamed foam so that it expands due to heat and forms a whole with the corner reflection structure includes: heating the foamed foam, and the foamed foam in each cavity expands due to heat and is connected into a whole through the connecting holes, and then forms a whole with the corner reflection structure.

[0023] According to yet another aspect of the present invention, an aircraft is provided. The aircraft includes the wing structure with enhanced near-field scattering characteristics as proposed above in the present invention.

[0024] By applying the technical solution of the present invention, a wing structure with enhanced near-field scattering characteristics, a manufacturing method and an aircraft are provided. The wing structure uses wing spars and wing ribs made of metal materials as the main load-bearing structure, uses wave-transparent materials as the upper and lower skins, and arranges an angle reflection structure composed of multiple metal plates in the compartment formed by the wing spars and the wing ribs. The angle reflection structure is fixedly supported by filling the compartment in the angle reflection structure with foamed foam. The scattering characteristics can be significantly improved without affecting the flight performance of the platform, while the weight of the wing structure is significantly reduced, and the strength and rigidity of the wing are improved. The near-field scattering characteristics of a high-value large-sized aircraft target can be simulated without changing the conventional configuration of a small-sized target aircraft, thereby saving the cost of weapon equipment training. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] The included drawings are used to provide a further understanding of the embodiments of the present invention, which constitute a part of the specification, are used to illustrate the embodiments of the present invention, and together with the text description, explain the principles of the present invention. Obviously, the drawings in the following description are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0026] Figure 1 A schematic diagram of a wing structure with enhanced near-field scattering characteristics provided according to a specific embodiment of the present invention is shown;

[0027] Figure 2 A schematic structural diagram of a scattering enhancement component provided according to a specific embodiment of the present invention is shown;

[0028] Figure 3 A schematic diagram showing the positional relationship between the scattering enhancement component and the foaming foam provided according to a specific embodiment of the present invention is shown. DETAILED DESCRIPTION

[0029] It should be noted that, in the absence of conflict, the embodiments in this application and the features in the embodiments can be combined with each other. The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. The following description of at least one exemplary embodiment is actually only illustrative and is by no means intended to limit the present invention and its application or use. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0030] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0031] Unless otherwise specifically stated, the relative arrangement of the parts and steps described in these embodiments, numerical expressions and numerical values ​​do not limit the scope of the present invention. At the same time, it should be understood that, for ease of description, the sizes of the various parts shown in the accompanying drawings are not drawn according to the actual proportional relationship. The technology, method and equipment known to ordinary technicians in the relevant field may not be discussed in detail, but in appropriate cases, the technology, method and equipment should be regarded as a part of the authorization specification. In all examples shown and discussed here, any specific value should be interpreted as being merely exemplary, rather than as a limitation. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters represent similar items in the following drawings, so once a certain item is defined in an accompanying drawing, it does not need to be further discussed in subsequent drawings.

[0032] like Figure 1 As shown, according to a specific embodiment of the present invention, a wing structure with enhanced near-field scattering characteristics is provided, the wing structure comprising:

[0033] The wing frame 10 includes a wing spar 11 and a wing rib 12, and the wing spar 11 and the wing rib 12 are both made of metal materials;

[0034] The skin assembly 20 includes an upper skin 21 and a lower skin 22. The upper skin 21 is laid on the upper surface of the wing frame 10, and the lower skin 22 is laid on the lower surface of the wing frame 10. Both the upper skin 21 and the lower skin 22 are made of wave-transmitting materials;

[0035] The scattering enhancement component 30 includes a first metal plate 31, a plurality of second metal plates 32 and a plurality of third metal plates 33. The first metal plate 31 is laid in a compartment formed by the spar 11 and the rib 12. The plurality of second metal plates 32 and the plurality of third metal plates 33 are arranged on and / or below the first metal plate 31 in a cross-combination manner to form an angle reflection structure, and the scattering characteristics are enhanced by the angle reflection structure.

[0036] Foaming foam, the foaming foam is arranged in the compartment formed by the first metal plate 31, the second metal plate 32 and the third metal plate 33 to form a whole with the first metal plate 31, the second metal plate 32 and the third metal plate 33 after thermal expansion, and the foaming foam is used to fix and support the first metal plate 31, the second metal plate 32 and the third metal plate 33 and improve the strength of the wing structure.

[0037] like Figure 2 and Figure 3 As shown, when multiple second metal plates 32 and multiple third metal plates 33 are only arranged on or below the first metal plate 31 in a cross-combination manner, a single-layer corner reflection structure is formed. When multiple second metal plates 32 and multiple third metal plates 33 are simultaneously arranged on and below the first metal plate 31 in a cross-combination manner, a double-layer corner reflection structure is formed. The double-layer corner reflection structure has a larger range of electromagnetic wave beam receiving angles than the single-layer corner reflection structure, and thus has a better scattering characteristic enhancement effect.

[0038] By applying this configuration, a wing structure with enhanced near-field scattering characteristics is provided. The wing structure uses metal spar and rib as the main load-bearing structure, uses wave-transparent material as the upper and lower skins, and arranges an angle reflection structure composed of multiple metal plates in the compartment formed by the spar and rib. The angle reflection structure is fixedly supported by filling the foamed foam in the compartment of the angle reflection structure. The scattering characteristics can be significantly improved without affecting the flight performance of the platform, and the weight of the wing structure can be significantly reduced. The strength and rigidity of the wing can be improved, and the near-field scattering characteristics of high-value large-sized aircraft targets can be simulated without changing the conventional configuration of the small-sized target aircraft, saving the training cost of weapons and equipment. Compared with the prior art, the technical solution of the present invention can solve the technical problem that the conventional configuration of the small-sized target aircraft in the prior art has a small body scattering characteristic in the near-field situation, and it is difficult to meet the requirements of simulating the near-field characteristics of large-sized aircraft.

[0039] As a specific embodiment of the present invention, the spar 11 and the rib 12 are all made of aluminum alloy, the first metal plate 31, the second metal plate 32 and the third metal plate 33 are all aluminum plates, and the wave-transmitting material is a glass fiber composite material. In order to reduce the weight of the entire structure, in the embodiment of the present invention, the thickness of the upper skin 21 and the lower skin 22 ranges from 0.6mm to 1mm, for example, the thickness can be selected as 0.8mm, and the thickness of the aluminum plate ranges from 0.3mm to 0.5mm, for example, 0.3mm. Through this configuration, the spar 11 and the rib 12 made of aluminum alloy are used as load-bearing structures, and the thickness of the upper and lower skins is relatively thin, which is only used to bear aerodynamic forces and maintain the structural shape. In addition, the upper and lower skins are made of glass fiber composite materials with good wave-transmitting properties, and the cross space between the spar 11 and the rib 12 is filled with an angular reflection structure composed of the first metal plate 31, the second metal plate 32 and the third metal plate 33 made of aluminum plates. The angular reflection structure cooperates with the beams and ribs made of aluminum alloy to enhance the scattering characteristics of the wing under near-field conditions.

[0040] Furthermore, in the embodiment of the present invention, mounting holes are provided on the spar 11 and the rib 12, and the mounting holes are used to install and fix the scattering enhancement component 30. As a specific embodiment of the present invention, the spar 11 and the rib 12 are used as the main load-bearing structure, and are machined from aluminum alloy materials, and mounting holes are processed on the spar 11 and the rib 12, and the scattering enhancement component 30 is fixedly connected to the spar 11 and the rib 12 by screwing.

[0041] In addition, if Figure 2 and Figure 3 As shown, the first metal plate 31, the second metal plate 32 and the third metal plate 33 are all provided with connecting holes, and the foamed foam in each cavity is connected as a whole through the connecting holes after being heated and expanded. In the present invention, the foamed foam has wave-transmitting properties, is a paper-like structure at room temperature, and can be cut at will. The foamed foam will expand and harden after being heated at high temperature, and fill in the cavity formed by the first metal plate 31, the second metal plate 32 and the third metal plate 33. At the same time, the foamed foam in each cavity is connected into an integral structure and forms a preform with the corner reflection structure. The expansion deformation of the foamed foam after heating is an irreversible reaction. After the foam is cooled, the structural shape when expanded will be maintained. In this way, the foamed foam can provide fixed support for the corner reflection structure, maintain the structural stability of the corner reflection structure, and improve the structural strength of the wing.

[0042] According to another aspect of the present invention, there is provided a method for manufacturing the wing structure proposed in the present invention, the manufacturing method comprising:

[0043] S1, placing the wave-transmitting material in a hot press pot for hot pressing to obtain an upper skin and a lower skin;

[0044] S2, using a machine tool to obtain a wing spar and a wing rib made of metal, and connecting and fixing the wing spar and the wing rib to obtain a wing skeleton;

[0045] S3, arranging the second metal plate and the third metal plate on and / or below the first metal plate in a cross combination form to form a corner reflection structure;

[0046] S4, placing the corner reflective structure in a foaming mold, cutting the foam into required sizes and placing them in the compartments formed by the first metal plate, the second metal plate and the third metal plate, respectively, and heating the foam so that the foam expands due to the heat and forms a whole with the corner reflective structure;

[0047] S5, connecting and fixing the corner reflection structure processed by S4 to the wing frame;

[0048] S6, the upper skin and the lower skin are respectively attached to the wing frame processed in S5 by adhesive films, and hot pressing is performed by hot pressing to make the upper skin, the lower skin, the wing frame and the corner reflection structure bonded and cured into an integral wing structure.

[0049] In this way, a method for manufacturing a wing structure with enhanced near-field scattering characteristics is provided. The method uses wave-transparent materials to manufacture preforms of upper and lower skins, uses machined metal materials to manufacture wing beams and ribs as main load-bearing structures, and forms an angle reflection structure by cross-arranging a second metal plate and a third metal plate on and / or below a first metal plate. The angle reflection structure is filled with foamed foam to achieve fixed support for the angle reflection structure, and then the various components are bonded into an integral structure through secondary bonding and curing. The wing structure manufactured by the method can significantly improve the scattering characteristics without affecting the flight performance of the platform, while significantly reducing the weight of the wing structure, and improving the strength and stiffness of the wing. It can simulate the near-field scattering characteristics of high-value large-size aircraft targets without changing the conventional configuration of the small-size target aircraft, thereby saving the cost of weapon equipment training.

[0050] Furthermore, in the embodiment of the present invention, the wing spar and the wing rib are all made of aluminum alloy, the first metal plate, the second metal plate and the third metal plate are all aluminum plates, and the wave-transmitting material is a glass fiber composite material. Through this configuration, the wing spar and the wing rib made of aluminum alloy are used as load-bearing structures, and the upper and lower skins are relatively thin, which are only used to bear aerodynamic forces and maintain the structural appearance. In addition, the upper and lower skins are made of glass fiber composite materials with good wave-transmitting properties, and at the same time, the cross space between the wing spar and the wing rib is filled with an angular reflection structure composed of the first metal plate, the second metal plate and the third metal plate made of aluminum plate. The angular reflection structure cooperates with the beams and ribs made of aluminum alloy to enhance the scattering characteristics of the wing under near-field conditions.

[0051] In addition, in the embodiment of the present invention, the first metal plate, the second metal plate and the third metal plate are all provided with connecting holes, and heating the foamed foam so that it expands by heat and forms a whole with the corner reflection structure includes: heating the foamed foam, and the foamed foam in each cavity is connected as a whole through the connecting holes after it expands by heat, and then forms a whole with the corner reflection structure. In the present invention, the foamed foam has wave-transmitting properties, is a paper-like structure at room temperature, and can be cut at will. The foamed foam will expand and harden after being heated at high temperature, and fill in the cavity formed by the first metal plate, the second metal plate and the third metal plate. At the same time, the foamed foam in each cavity is connected into an integral structure and forms a preform with the corner reflection structure. The expansion deformation of the foamed foam after heating is an irreversible reaction. After the foam cools, the structural shape when expanded will be maintained. In this way, the foamed foam can provide fixed support for the corner reflection structure, maintain the structural stability of the corner reflection structure, and improve the structural strength of the wing.

[0052] According to another aspect of the present invention, an aircraft is provided, the aircraft comprising the near-field scattering characteristic enhanced wing structure proposed in the present invention. Since the near-field scattering characteristic enhanced wing structure proposed in the present invention can significantly improve the scattering characteristics without affecting the flight performance of the platform, while significantly reducing the weight of the wing structure and improving the strength and rigidity of the wing, therefore, applying it to the aircraft can achieve the near-field scattering characteristic simulation of a high-value large-sized aircraft target without changing the conventional configuration of the small-sized target aircraft, thereby saving the cost of weapon equipment training.

[0053] In order to further understand the present invention, the following Figure 1 , Figure 2 and Figure 3 The wing structure and the manufacturing process of the present invention are described in detail.

[0054] like Figure 1 As shown, the wing has a half span of 2800 mm, and the entire structure includes an upper skin 21, a lower skin 22, a spar 11, a rib 12, a scattering enhancement component 30, and foaming foam. The upper and lower skins of the wing are made of wave-transmitting materials, and the spar 11, rib 12, and scattering enhancement component 30 inside the wing are all made of metal materials. The scattering enhancement component 30 is embedded inside the skin, which can enhance the near-field scattering characteristics in all directions. The foaming foam provides fixed support for the scattering enhancement component 30 and improves the structural strength of the wing. The manufacturing process of the wing structure is as follows:

[0055] In the first step, the parts are prefabricated and the wave-transmitting glass fiber composite material is hot-pressed in a hot press to form an upper skin 21 and a lower skin 22, and the thickness of the upper and lower skins is 0.8 mm; the wing spar 11 and the wing rib 12 are machined and formed, and the material is aluminum alloy. The wing spar 11 and the wing rib 12 are connected by screws; the aluminum plates with holes are cross-assembled to form a molded part, and the thickness of the selected aluminum plates is 0.3 mm. The molded part is divided into an upper and lower layer, and the upper and lower layers are arranged cross-wise. An aluminum plate is set in the middle to separate the two layers to form a double-layer corner reflection structure, such as Figure 2 and Figure 3 As shown, the second metal plate 32 and the third metal plate 33 are arranged on the upper and lower sides of the first metal plate 31 in a cross manner, thereby ensuring that the wing has a good scattering characteristic enhancement effect in all directions.

[0056] In the second step, the foaming foam is subjected to a foaming reaction, the paper-like foaming foam is cut into the required size, the corner reflective structure molded part is placed in the foaming mold, the paper-like foam is placed in the compartment of the corner reflector respectively, the mold is placed in an oven for heating and heat preservation, the foam undergoes a chemical reaction, and after expansion, it is connected to the surrounding foam through the connecting holes to form a whole, forming a corner reflective structure prefabricated part, the corner reflective structure is embedded in the formed foam, becomes the skeleton of the foam, and supports each other, the corner reflective structure prefabricated part is as follows Figure 2 As shown, the number of corner reflective structure prefabricated parts required for the wing is determined according to the number of cavities surrounded by beams and ribs and the required size of scattering characteristics, and the molding temperature and molding time are set according to the thickness of the wing.

[0057] In the third step, the corner reflection structure prefabricated parts are combined with the beams and ribs of the wing to form a combination, and mounting holes are set on the wing beams 11 and the wing ribs 12. The corner reflection structure prefabricated parts are fixed to the mounting holes of the beams and ribs by screwing, so as to form the skeleton structure of the wing as a whole.

[0058] The fourth step is to bond and solidify the wing skeleton structure and the upper and lower skins for the second time. The adhesive film is pasted on the upper and lower surfaces of the corner reflector structure to bond the wing skin to the wing skeleton. The adhesive film is melted under the hot pressing in the hot pressing process to bond the wing skin to the beam, rib and corner reflector structure prefabricated body into an integral structure. The schematic diagram of the overall wing structure is shown in the figure. Figure 1 shown.

[0059] The scattering characteristics of the wing with this structural design and the conventional wing in the near field were simulated and tested. The near-field scattering characteristics of a single wing in the conventional configuration are about 0.1m 2 After the wing structure of the present invention is enhanced by scattering characteristics, the near-field scattering characteristics reach 0.5m 2 ~0.6m 2The enhanced scattering structure proposed in the present invention can be applied to the design of target drone structural parts such as tail fins and fuselages, and the scattering characteristics of small-sized target drones under near-field conditions will be significantly enhanced.

[0060] In summary, the present invention provides a wing structure with enhanced near-field scattering characteristics, a manufacturing method and an aircraft. The wing structure uses a wing spar and a wing rib of a metal material as the main load-bearing structure, uses a wave-transparent material as the upper and lower skins, and arranges an angle reflection structure composed of a plurality of metal plates in the compartment formed by the wing spar and the wing rib. The angle reflection structure is fixedly supported by filling the foamed foam in the compartment of the angle reflection structure. The scattering characteristics can be significantly improved without affecting the flight performance of the platform, and the weight of the wing structure can be significantly reduced. The strength and rigidity of the wing are improved, and the near-field scattering characteristics of a high-value large-sized aircraft target can be simulated without changing the conventional configuration of the small-sized target aircraft, saving the cost of weapon equipment training. Compared with the prior art, the technical solution of the present invention can solve the technical problem that the conventional configuration of the small-sized target aircraft in the prior art has a small body scattering characteristic in the near-field situation, and it is difficult to meet the requirements of simulating the near-field characteristics of a large-sized aircraft.

[0061] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0062] In addition, it should be noted that the use of terms such as "first" and "second" to limit components is only for the convenience of distinguishing the corresponding components. If not otherwise stated, the above terms have no special meaning and therefore cannot be understood as limiting the scope of protection of the present invention.

[0063] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A wing structure with enhanced near-field scattering characteristics, characterized in that: The wing structure comprises: A wing frame (10), the wing frame (10) comprising a wing spar (11) and a wing rib (12), the wing spar (11) and the wing rib (12) both being made of metal material; A skin assembly (20), the skin assembly (20) comprising an upper skin (21) and a lower skin (22), the upper skin (21) being laid on the upper surface of the wing frame (10), the lower skin (22) being laid on the lower surface of the wing frame (10), and the upper skin (21) and the lower skin (22) both being made of wave-transmitting material; A scattering enhancement component (30), the scattering enhancement component (30) comprising a first metal plate (31), a plurality of second metal plates (32) and a plurality of third metal plates (33), the first metal plate (31) being laid in a compartment formed by the wing beam (11) and the wing rib (12), the plurality of second metal plates (32) and the plurality of third metal plates (33) being arranged on and / or below the first metal plate (31) in a cross-combination manner to form an angle reflection structure, and the scattering characteristics are enhanced by the angle reflection structure; The foaming foam is arranged in a compartment formed by the first metal plate (31), the second metal plate (32) and the third metal plate (33) so as to form a whole with the first metal plate (31), the second metal plate (32) and the third metal plate (33) after thermal expansion, and the foaming foam is used to fix and support the first metal plate (31), the second metal plate (32) and the third metal plate (33) and to improve the strength of the wing structure.

2. The wing structure according to claim 1, characterized in that: The wing beam (11) and the wing rib (12) are both made of aluminum alloy, the first metal plate (31), the second metal plate (32) and the third metal plate (33) are all aluminum plates, and the wave-transmitting material is a glass fiber composite material.

3. The wing structure according to claim 2, characterized in that: The wing beam (11) and the wing rib (12) are provided with mounting holes, and the mounting holes are used to mount and fix the scattering enhancement component (30).

4. The wing structure according to claim 3, characterized in that: The first metal plate (31), the second metal plate (32) and the third metal plate (33) are all provided with connecting holes, and the foamed foam in each compartment is connected into a whole through the connecting holes after being expanded by heat.

5. The wing structure according to claim 4, characterized in that: The thickness of the upper skin (21) and the lower skin (22) ranges from 0.6 mm to 1 mm, and the thickness of the aluminum plate ranges from 0.3 mm to 0.5 mm.

6. A method for manufacturing a wing structure according to any one of claims 1 to 5, characterized in that: The manufacturing method comprises: S1, placing the wave-transmitting material in a hot press pot for hot pressing to obtain an upper skin and a lower skin; S2, using a machine tool to obtain a wing spar and a wing rib made of metal, and connecting and fixing the wing spar and the wing rib to obtain a wing skeleton; S3, arranging the second metal plate and the third metal plate on and / or below the first metal plate in a cross combination form to form a corner reflection structure; S4, placing the corner reflective structure in a foaming mold, cutting the foam into required sizes and placing them in the compartments formed by the first metal plate, the second metal plate and the third metal plate, respectively, and heating the foam so that the foam expands due to the heat and forms a whole with the corner reflective structure; S5, connecting and fixing the corner reflection structure processed by S4 to the wing frame; S6, the upper skin and the lower skin are respectively attached to the wing frame processed in S5 by adhesive films, and hot pressing is performed by hot pressing to make the upper skin, the lower skin, the wing frame and the corner reflection structure bonded and cured into an integral wing structure.

7. The manufacturing method according to claim 6, characterized in that: The wing beam and the wing rib are both made of aluminum alloy, the first metal plate, the second metal plate and the third metal plate are all aluminum plates, and the wave-transmitting material is a glass fiber composite material.

8. The manufacturing method according to claim 7, characterized in that: The first metal plate, the second metal plate and the third metal plate are all provided with connecting holes, and heating the foamed foam so that it expands due to heat to form a whole with the corner reflection structure includes: heating the foamed foam, and the foamed foam in each cavity expands due to heat to be connected into a whole through the connecting holes, and then forms a whole with the corner reflection structure.

9. An aircraft, characterized in that: The aircraft comprises the near-field scattering property enhanced wing structure according to any one of claims 1 to 5.

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