Skin antenna, manufacturing method and airplane

Abstract

The invention discloses a skin antenna, a manufacturing method and an airplane, the skin antenna comprises a skin and an antenna assembly fixed with the skin, the skin and the antenna assembly are arc-shaped structures with the same radian, an opening penetrating through the skin is formed in the skin, the antenna assembly is fixed on the inner surface of the skin, and a radiating surface of the antenna assembly is exposed from the opening. The radiating surface of the antenna assembly is conformal and flush with the outer surface of the skin. The opening is formed in the skin, so that the radiating surface of the antenna assembly is exposed from the opening, and the skin is prevented from influencing the performance of the antenna; moreover, the radiating surface of the antenna assembly is conformal and flush with the outer surface of the skin, and the space occupied by the antenna assembly in the thickness direction of the skin is small, thereby preventing the antenna assembly from affecting the aerodynamic efficiency of the skin. The skin antenna not only can be used as a skin structure of an airplane, but also has good antenna performance.

Description

Technical Field

[0001] The present invention relates to the technical field of airborne antennas, and particularly to a skin antenna, a manufacturing method thereof, and an aircraft. Background Art

[0002] In recent years, airborne antennas have played an important role in application fields such as communication, navigation and positioning, electronic reconnaissance, countermeasure, and identification of friend or foe for fire control radar. And airborne antennas have different structural forms and installation methods due to different applications. In communication applications, traditional airborne communication systems usually adopt rod-shaped antennas to achieve long-distance signal transmission. Due to their long size, rod-shaped antennas need to occupy a large space when installed in the wings or fuselage of an aircraft. Moreover, due to the rigid structure characteristics of rod-shaped antennas, they cannot be conformal with the aircraft structure, and the part extending outside the aircraft aerodynamic surface affects the aerodynamic efficiency of the whole machine, thus increasing the aircraft energy consumption.

[0003] In order to avoid affecting the aerodynamic efficiency of the whole machine, existing airborne antennas are usually arranged inside the aircraft wing to achieve the integrated design of the wing and the antenna. Although arranging the antenna inside the aircraft wing in the prior art can increase the aerodynamic efficiency, the antenna in the prior art is not truly conformal with the wing. Only the antenna is arranged inside the wing, and the skin of the wing will affect the performance of the antenna. Summary of the Invention

[0004] In order to overcome the disadvantages and deficiencies existing in the prior art, the purpose of the present invention is to provide a skin antenna, a manufacturing method thereof, and an aircraft to solve the problem that the airborne antenna in the prior art cannot take into account better aerodynamic efficiency and better antenna performance.

[0005] The purpose of the present invention is achieved by the following technical solutions:

[0006] The present invention provides a skin antenna, including a skin and an antenna assembly fixed to the skin. The skin and the antenna assembly are arc-shaped structures with the same radian. An opening penetrating the skin is provided on the skin. The antenna assembly is fixed to the inner surface of the skin, and the radiation surface of the antenna assembly exposes from the opening. The radiation surface of the antenna assembly is conformal and flush with the outer surface of the skin.

[0007] Furthermore, the antenna assembly includes a wave-transparent protective cover, a connecting frame beam, and an antenna. The connecting frame beam is located at the opening, the periphery of the connecting frame beam is fixed to the inner surface of the skin, the wave-transparent protective cover is located inside the opening and fixed to the connecting frame beam, and the antenna is fixed to the connecting frame beam and corresponds to the wave-transparent protective cover.

[0008] Further, the antenna includes a radiation layer, a dielectric layer, and a ground layer. The connection frame beam has a plurality of accommodation cells distributed in an array. The connection frame beam is disposed between the ground layer and the wave-transmitting protective cover. The radiation layer and the dielectric layer are both disposed within the accommodation cells. The dielectric layer is located between the radiation layer and the ground layer and separates the radiation layer and the ground layer from each other.

[0009] Further, it at least includes one of the following:

[0010] The thickness of the connection frame beam is greater than or equal to the sum of the thicknesses of the radiation layer and the dielectric layer;

[0011] Both the radiation layer and the ground layer are made of copper-clad flexible PI film;

[0012] The outer surface of the radiation layer is closely attached to and conformal with the inner surface of the wave-transmitting protective cover.

[0013] Further, the connection frame beam includes a plurality of transverse beams and longitudinal beams with arc-shaped structures. The transverse beams and the longitudinal beams are arranged crosswise to form a plurality of the accommodation cells distributed in an array. The transverse beams are provided with first engaging grooves, and the longitudinal beams are provided with second engaging grooves that cooperate with the first engaging grooves.

[0014] Further, the wave-transmitting protective cover and the skin are made of different materials. The wave-transmitting protective cover and the connection frame beam are both made of glass fiber composite material, and the skin is made of carbon fiber composite material.

[0015] This application also provides a manufacturing method for a skin antenna for manufacturing the skin antenna as described above. The manufacturing method includes:

[0016] Providing a skin, and opening an opening penetrating the skin;

[0017] Providing an antenna assembly. The skin and the antenna assembly are arc-shaped structures with the same radian. Fixing the antenna assembly to the inner surface of the skin. The radiation surface of the antenna assembly exposes from the opening, and the radiation surface of the antenna assembly is conformal and flush with the outer surface of the skin.

[0018] Further, the manufacturing method includes manufacturing the antenna assembly:

[0019] Providing a connection frame beam. The connection frame beam has a plurality of accommodation cells distributed in an array, and bending and shaping the connection frame beam;

[0020] Providing a wave-transmitting protective cover, and pressing and conforming the wave-transmitting protective cover and the connection frame beam together;

[0021] An antenna is provided. The antenna is formed by laminating a radiation layer, a dielectric layer, and a ground layer. The radiation layer and the ground layer overlap each other and are arranged in an array on the ground layer. The dielectric layer is located between the radiation layer and the ground layer and separates the radiation layer and the ground layer. The antenna is connected to the connection frame beam and conformal, and the radiation layer and the dielectric layer are respectively disposed in the accommodation cells.

[0022] Further, the manufacturing method includes manufacturing the connection frame beam:

[0023] A plurality of transverse beams and longitudinal beams with arc-shaped structures are provided. A first engaging groove is machined on the transverse beam, and a second engaging groove matching the first engaging groove is machined on the longitudinal beam;

[0024] Adhesive is respectively coated in the first engaging groove of the transverse beam and the second engaging groove of the longitudinal beam, and the plurality of transverse beams and the plurality of longitudinal beams are engaged with each other and subjected to vacuum heat curing treatment.

[0025] The present application also provides an aircraft, including the skin antenna as described above, and the skin antenna serves as the outer shell of the aircraft.

[0026] The beneficial effects of the present invention are as follows: By providing an opening in the skin, the radiation surface of the antenna assembly is exposed from the opening, thereby avoiding the influence of the skin on the performance of the antenna; moreover, the radiation surface of the antenna assembly is conformal and flush with the outer surface of the skin, avoiding the influence of the antenna assembly on the aerodynamic efficiency of the skin, and the antenna assembly occupies a small space in the thickness of the skin, reducing the load weight, and is more suitable for the aircraft platform. The skin antenna of the present application can not only be used as the skin structure of the aircraft, but also has good antenna performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 is a schematic structural diagram of the inner surface of the skin antenna in the present invention;

[0028] Figure 2 is a schematic exploded structural diagram of the skin antenna in the present invention;

[0029] Figure 3 is a schematic exploded structural diagram of the transverse beam and the longitudinal beam in the present invention.

[0030] In the figure: skin 10, opening 101; antenna assembly 20, wave-transparent protective cover 21, connection frame beam 22, accommodation cell 22a, transverse beam 221, first engaging groove 221a, longitudinal beam 222, second engaging groove 222a, antenna 23, radiation layer 231, dielectric layer 232, ground layer 233. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0031] To further elaborate on the technical means and effects adopted by the present invention to achieve the intended invention purpose, the following, in conjunction with the accompanying drawings and preferred embodiments, details the specific implementation manners, structures, features, and effects of the skin antenna and its manufacturing method, and the aircraft according to the present invention as follows:

[0032] Figure 1 It is a schematic structural diagram of the inner surface of the skin antenna in the present invention. Figure 2 It is a schematic exploded structural diagram of the skin antenna in the present invention. Figure 3 It is a schematic exploded structural diagram of the transverse beam and the longitudinal beam in the present invention.

[0033] As Figures 1 to 3 shown, a skin antenna provided in Embodiment 1 of the present invention includes a skin 10 and an antenna assembly 20 fixed to the skin 10. The skin 10 and the antenna assembly 20 are arc-shaped structures with the same radian. An opening 101 penetrating the skin 10 is provided on the skin 10. The antenna assembly 20 is fixed to the inner surface of the skin 10, and the radiation surface of the antenna assembly 20 is exposed from the opening 101. The radiation surface of the antenna assembly 20 is conformal and flush with the outer surface of the skin 10.

[0034] By providing the opening 101 on the skin 10, the radiation surface of the antenna assembly 20 is exposed from the opening 101, thereby avoiding the skin 10 from affecting the performance of the antenna; moreover, the radiation surface of the antenna assembly 20 is conformal and flush with the outer surface of the skin 10, avoiding the antenna assembly 20 from affecting the aerodynamic efficiency of the skin 10, and the antenna assembly 20 occupies a small space in the thickness of the skin 10, reducing the load weight, and is more suitable for the aircraft platform. The skin antenna of the present application can be used as the skin structure of the aircraft and has good antenna performance.

[0035] In this embodiment, the antenna assembly 20 includes a wave-transparent protective cover 21, a connecting frame beam 22, and an antenna 23. The connecting frame beam 22 is located at the opening 101, and the periphery of the connecting frame beam 22 is fixed to the inner surface of the skin 10. The wave-transparent protective cover 21 is located within the opening 101 and is fixed to the connecting frame beam 22. The size of the wave-transparent protective cover 21 is the same as the size of the radiation surface of the antenna assembly 20. The outer surface of the wave-transparent protective cover 21 is conformal and flush with the outer surface of the skin 10, that is, the outer surface of the wave-transparent protective cover 21 is the radiation surface of the antenna assembly 20. The antenna 23 is fixed to the connecting frame beam 22 and corresponds to the wave-transparent protective cover 21. That is, the entire antenna assembly 20 is fixed to the skin 10 through the connecting frame beam 22, and the wave-transparent protective cover 21 and the antenna 23 are connected to the connecting frame beam 22. Among them, the wave-transparent protective cover 21, the connecting frame beam 22, and the antenna 23 are all arc-shaped structures with the same radian, so as to ensure that the entire antenna assembly 20 is an arc-shaped structure with the same radian as the antenna assembly 20.

[0036] Further, the opening 101 has a square structure, and the size of the radiation surface of the antenna assembly 20 is the same as that of the opening 101, that is, the size of the wave - transmitting protective cover 21 is the same as that of the opening 101, so as to ensure that the wave - transmitting protective cover 21 can be well embedded in the opening 101, to better ensure that the antenna assembly 20 has a larger radiation surface, while avoiding affecting the aerodynamic efficiency of the skin 10.

[0037] Further, the antenna 23 includes a radiation layer 231, a dielectric layer 232, and a ground layer 233. The connecting frame beam 22 has a plurality of accommodation cells 22a distributed in an array. The connecting frame beam 22 is arranged between the ground layer 233 and the wave - transmitting protective cover 21. The connecting frame beam 22 divides the gap between the ground layer 233 and the wave - transmitting protective cover 21 into a plurality of chambers distributed in an array. Both the radiation layer 231 and the dielectric layer 232 are arranged in the accommodation cells 22a. The dielectric layer 232 is located between the radiation layer 231 and the ground layer 233 and separates the radiation layer 231 and the ground layer 233. The number of the radiation layer 231 and the dielectric layer 232 is the same as the number of the accommodation cells 22a. The size of each radiation layer 231 and dielectric layer 232 is the same as the size of the accommodation cells 22a. The radiation layer 231 and the dielectric layer 232 are overlapped with each other and embedded in the accommodation cells 22a. The radiation layer 231 and the dielectric layer 232 of the antenna 23 adopt a block structure, making the antenna 23 easier to bend and deform, and facilitating conformal shaping with the skin 10.

[0038] In this embodiment, the wave - transmitting protective cover 21 and the skin 10 are made of different materials. Among them, both the wave - transmitting protective cover 21 and the connecting frame beam 22 are made of fiberglass composite materials, so as to avoid the wave - transmitting protective cover 21 and the connecting frame beam 22 from affecting the antenna performance. The skin 10 is made of carbon fiber composite materials, so as to reduce the weight of the skin 10 and make the skin 10 have better strength, which is more suitable for use in the aircraft outer shell.

[0039] Further, both the radiation layer 231 and the ground layer 233 are made of copper - clad flexible PI films, and the dielectric layer 232 adopts a honeycomb structure. Thus, after the radiation layer 231, the dielectric layer 232, and the ground layer 233 are pressed together, it is ensured that the antenna 23 has a certain flexibility, so as to be better conformal with the skin 10. Preferably, the copper - clad flexible PI (Polyimide Film) film can be made of two layers of flexible PI films with a copper film sandwiched in the middle, so as to avoid short - circuiting of the radiation layer 231 and the ground layer 233 with other conductive materials, and to avoid affecting the electrical performance of the antenna 23.

[0040] Further, the thickness of the connecting frame beam 22 is greater than or equal to the sum of the thicknesses of the radiation layer 231 and the dielectric layer 232. The outer surface of the radiation layer 231 is closely attached to and conformal with the inner surface of the wave-transmitting protective cover 21, so that the antenna 23 has better radiation performance. Preferably, the thickness of the connecting frame beam 22 is equal to the sum of the thicknesses of the radiation layer 231 and the dielectric layer 232, so as to ensure that the radiation layer 231 and the dielectric layer 232 are just embedded in the accommodation grid 22a, and the outer surface of the radiation layer 231 is closely attached to the inner surface of the wave-transmitting protective cover 21. Thus, it can not only protect the shape of the antenna assembly 20 unchanged during flight, but also customize the thickness of the connecting frame beam 22 according to the sectional height of different antenna assemblies 20, so as to meet the installation of antennas of different sizes.

[0041] Further, the connecting frame beam 22 includes a plurality of transverse beams 221 and longitudinal beams 222 with arc-shaped structures. The transverse beams 221 and the longitudinal beams 222 are arranged crosswise and form a plurality of accommodation grids 22a distributed in an array. The transverse beam 221 is provided with a first engaging groove 221a, and the longitudinal beam 222 is provided with a second engaging groove 222a that cooperates with the first engaging groove 221a, so as to ensure the flatness of the surface of the connecting frame beam 22.

[0042] Further, the thickness of the skin 10 is 1-1.5 mm, the thickness of the connecting frame beam 22 is 2-5 mm, the thickness of the wave-transmitting protective cover 21 is 1-1.5 mm, and the thicknesses of the skin 10 and the wave-transmitting protective cover 21 are the same. The thicknesses of the radiation layer 231 and the ground layer 233 are 0.05-0.1 mm, the thickness of the dielectric layer 232 is 2 mm, and the thickness of the entire antenna 23 is 2.1-5.1 mm to form a low-profile antenna. The connecting frame beam 22 is formed by the intersection of 5 transverse beams 221 with arc-shaped structures and 5 longitudinal beams 222 with arc-shaped structures, forming 16 accommodation grids 22a distributed in a 4x4 array. The accommodation grid 22a is a square structure, and the size of each accommodation grid 22a is 62-67 mm. For example, the thicknesses of both the skin 10 and the wave-transmitting protective cover 21 are 1.5 mm. The thicknesses of both the radiation layer 231 and the ground layer 233 are 0.05 mm, and the thickness of the entire antenna 23 is 2.1 mm. The thickness of the connecting frame beam 22 is 3 mm, the size of each accommodation grid 22a is 62 mm, and the depths of the first engaging groove 221a and the second engaging groove 222a are 1.5 mm, that is, the depths of the first engaging groove 221a and the second engaging groove 222a are both half of the thickness of the connecting frame beam 22. Of course, the size of the accommodation grid 22a can be set according to the sizes of the radiation layer 231 and the dielectric layer 232, and the number of accommodation grids 22a can be customized according to the antenna design index.

[0043] This application also provides a manufacturing method for a skin antenna for manufacturing the skin antenna as described above. The manufacturing method includes:

[0044] Provide a skin 10, the skin 10 is an arc structure, for example, the skin 10 is an arc structure of a gradient surface. An opening 101 penetrating the skin 10 is formed on the skin 10, and the opening 101 is, for example, a square structure. The skin 10 is made of carbon fiber composite material, so that the weight of the skin 10 can be reduced, and the skin 10 has better strength, and is more suitable for use in the aircraft shell. The thickness of the skin 10 is 1-1.5 mm, for example, 1.5 mm.

[0045] Provide an antenna assembly 20, the skin 10 and the antenna assembly 20 are arc structures with the same radian. The antenna assembly 20 is fixed to the inner surface of the skin 10, and the radiation surface of the antenna assembly 20 is exposed from the opening 101, and the radiation surface of the antenna assembly 20 is conformal and flush with the outer surface of the skin 10. Among them, the skin 10 and the antenna assembly 20 can be bonded by glue.

[0046] Furthermore, the manufacturing method includes manufacturing the antenna assembly 20:

[0047] Provide a connection frame beam 22, the connection frame beam 22 has a plurality of accommodation cells 22a distributed in an array, and the connection frame beam 22 is bent and shaped. The connection frame beam 22 is made of glass fiber composite material, so as to avoid the wave-transparent protective cover 21 and the connection frame beam 22 from affecting the antenna performance. The thickness of the connection frame beam 22 is 2-5 mm, for example, 3 mm.

[0048] Provide a wave-transparent protective cover 21, press the wave-transparent protective cover 21 and the connection frame beam 22 together and make them conformal. For example, an adhesive (such as epoxy glue) is coated between the wave-transparent protective cover 21 and the connection frame beam 22, and the wave-transparent protective cover 21 and the connection frame beam 22 are pressed and cured under vacuum and high temperature, so that the wave-transparent protective cover 21 and the connection frame beam 22 are pressed together. Among them, the wave-transparent protective cover 21 is made of glass fiber composite material, so as to avoid the wave-transparent protective cover 21 and the connection frame beam 22 from affecting the antenna performance. The thickness of the wave-transparent protective cover 21 is 1-1.5 mm, for example, 1.5 mm. The thickness of the skin 10 is the same as that of the wave-transparent protective cover 21, so as to better ensure that the outer surface of the wave-transparent protective cover 21 is conformal and flush with the outer surface of the skin 10.

[0049] An antenna 23 is provided. The antenna 23 is formed by laminating a radiation layer 231, a dielectric layer 232, and a ground layer 233, for example, by high-temperature hot pressing. The radiation layer 231 and the ground layer 233 overlap each other and are arranged in an array on the ground layer 233. The dielectric layer 232 is located between the radiation layer 231 and the ground layer 233 and separates the radiation layer 231 and the ground layer 233. The antenna 23 is connected to and conformal with the connecting frame beam 22. The radiation layer 231 and the dielectric layer 232 are both correspondingly arranged in the accommodation cell 22a. The antenna 23 and the connecting frame beam 22 can be fastened with screws or sealant. Among them, the number of the radiation layer 231 and the ground layer 233 is the same as the number of the accommodation cells 22a. The size of each radiation layer 231 and dielectric layer 232 is the same as the size of the accommodation cell 22a. The radiation layer 231 and the dielectric layer 232 are arranged to overlap each other and are embedded in the accommodation cell 22a.

[0050] Furthermore, both the radiation layer 231 and the ground layer 233 are made of copper-clad flexible PI films, and the dielectric layer 232 adopts a honeycomb structure. Thus, after the radiation layer 231, the dielectric layer 232, and the ground layer 233 are laminated together, it is ensured that the antenna 23 has a certain flexibility to be better conformal with the skin 10. Therefore, during processing and manufacturing, only the connecting frame beam 22 needs to be bent and shaped. After the wave-transparent protective cover 21 and the antenna 23 are laminated with the connecting frame beam 22, they are automatically conformal with the connecting frame beam 22 to reduce the bending and shaping process. Preferably, the copper-clad flexible PI (Polyimide Film) film can be made of two layers of flexible PI films with a copper film sandwiched in the middle, so as to avoid short circuits between the radiation layer 231 and the ground layer 233 and other conductive materials, and to avoid affecting the electrical performance of the antenna 23. The thickness of the radiation layer 231 and the ground layer 233 is 0.05 - 0.1 mm, the thickness of the dielectric layer 232 is 2 mm, and the thickness of the entire antenna 23 is 2.1 - 5.1 mm. For example, the thickness of both the radiation layer 231 and the ground layer 233 is 0.05 mm, and the thickness of the entire antenna 23 is 2.1 mm.

[0051] Furthermore, the manufacturing method includes manufacturing the connecting frame beam 22:

[0052] A plurality of transverse beams 221 and longitudinal beams 222 with arc-shaped structures are provided. A first engaging groove 221a is machined on the transverse beam 221, and a second engaging groove 222a matching with the first engaging groove 221a is machined on the longitudinal beam 222. The depth of the first engaging groove 221a and the second engaging groove 222a is 1.5 mm, that is, the depths of the first engaging groove 221a and the second engaging groove 222a are both half of the thickness of the connecting frame beam 22.

[0053] Apply adhesive (such as epoxy glue) to the first engaging groove 221a of the horizontal beam 221 and the second engaging groove 222a of the vertical beam 222 respectively, engage multiple horizontal beams 221 and multiple vertical beams 222 with each other, and perform vacuum heat curing treatment. After cooling, a complete connecting frame beam 22 is formed. Among them, the number of both the horizontal beam 221 and the vertical beam 222 is 5, and they intersect to form 4x4 = 16 accommodating cells 22a distributed in an array. The accommodating cell 22a is a square structure, and the size of each accommodating cell 22a is 62 - 67 mm. For example, the size of each accommodating cell 22a is 62 mm.

[0054] This application provides an aircraft, including the skin antenna as described above. The skin antenna serves as the outer shell of the aircraft. For example, the skin antenna is used for the wings, fuselage, tail wings, etc. of the aircraft, and has strong adaptability.

[0055] In this article, the orientation words such as up, down, left, right, front, and back are defined based on the positions of the structures in the drawings and the positions relative to each other, only for the sake of clarity and convenience in expressing the technical solution. It should be understood that the use of the orientation words should not limit the scope of protection claimed in this application. It should also be understood that the terms "first" and "second" used in this article are only for distinction in name and do not limit the quantity and order.

[0056] The above are only the preferred embodiments of the present invention, and do not impose any formal limitations on the present invention. Although the present invention has been disclosed above with the preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make some changes or modifications by using the disclosed technical content within the scope of the technical solution of the present invention, which are equivalent embodiments of equivalent changes. However, as long as it does not depart from the content of the technical solution of the present invention, any simple modification, equivalent change, and modification made to the above embodiments based on the technical essence of the present invention still fall within the protection scope of the technical solution of the present invention.

Claims

1. A skin antenna, characterized in that: The invention comprises a skin (10) and an antenna assembly (20) fixed to the skin (10); the skin (10) and the antenna assembly (20) are arc-shaped structures with the same curvature; the skin (10) is provided with an opening (101) penetrating the skin (10); the antenna assembly (20) is fixed to the inner surface of the skin (10); the radiation surface of the antenna assembly (20) is exposed from the opening (101); and the radiation surface of the antenna assembly (20) is conformal and flush with the outer surface of the skin (10).

2. The skin antenna according to claim 1, characterized in that: The antenna assembly (20) comprises a wave-transmitting protective cover (21), a connecting frame beam (22) and an antenna (23); the connecting frame beam (22) is located at the opening (101); the periphery of the connecting frame beam (22) is fixed to the inner surface of the skin (10); the wave-transmitting protective cover (21) is located in the opening (101) and is fixed to the connecting frame beam (22); the antenna (23) is fixed to the connecting frame beam (22) and corresponds to the wave-transmitting protective cover (21).

3. The skin antenna according to claim 2, characterized in that: The antenna (23) comprises a radiation layer (231), a dielectric layer (232) and a stratum (233); the connecting frame beam (22) has a plurality of accommodating grids (22a) distributed in an array; the connecting frame beam (22) is arranged between the stratum (233) and the wave-transmitting protective cover (21); the radiation layer (231) and the dielectric layer (232) are both arranged in the accommodating grid (22a); the dielectric layer (232) is located between the radiation layer (231) and the stratum (233) and separates the radiation layer (231) and the stratum (233).

4. The skin antenna according to claim 3, characterized in that: At least one of the following: The thickness of the connecting frame beam (22) is greater than or equal to the sum of the thicknesses of the radiation layer (231) and the dielectric layer (232); The radiation layer (231) and the ground layer (233) are both made of copper-clad flexible PI film; The outer surface of the radiation layer (231) is tightly fitted and conformal to the inner surface of the wave-transmitting protective cover (21).

5. The skin antenna according to claim 2, characterized in that: The connecting frame beam (22) comprises a plurality of arc-shaped transverse beams (221) and longitudinal beams (222); the transverse beams (221) and the longitudinal beams (222) are arranged crosswise to form a plurality of the containing grids (22a) distributed in an array; the transverse beam (221) is provided with a first wedging groove (221a); ​​and the longitudinal beam (222) is provided with a second wedging groove (222a) matched with the first wedging groove (221a).

6. The skin antenna according to claim 2, characterized in that: The wave-transmitting protective cover (21) and the skin (10) are made of different materials; the wave-transmitting protective cover (21) and the connecting frame beam (22) are both made of glass fiber composite materials, and the skin (10) is made of carbon fiber composite materials.

7. A method for manufacturing a skin antenna, characterized in that: Used to manufacture the skin antenna according to any one of claims 1 to 6, the manufacturing method comprising: Providing a skin (10), and opening (101) penetrating the skin (10) is provided on the skin (10); An antenna assembly (20) is provided, wherein the skin (10) and the antenna assembly (20) are arc-shaped structures with the same curvature, the antenna assembly (20) is fixed to the inner surface of the skin (10), the radiation surface of the antenna assembly (20) is exposed from the opening (101), and the radiation surface of the antenna assembly (20) is conformal and flush with the outer surface of the skin (10).

8. The method for manufacturing the skin antenna according to claim 7, characterized in that: The manufacturing method comprises manufacturing the antenna assembly (20): Providing a connecting frame beam (22), the connecting frame beam (22) having a plurality of accommodating grids (22a) distributed in an array, and bending the connecting frame beam (22) into a fixed shape; Providing a wave-transmitting protective cover (21), and pressing the wave-transmitting protective cover (21) and the connecting frame beam (22) together to conform to each other; An antenna (23) is provided. The antenna (23) is formed by pressing together a radiation layer (231), a dielectric layer (232) and a ground layer (233). The radiation layer (231) and the ground layer (233) overlap each other and are distributed in an array on the ground layer (233). The dielectric layer (232) is located between the radiation layer (231) and the ground layer (233) and separates the radiation layer (231) and the ground layer (233). The antenna (23) is connected to the connecting frame beam (22) and conforms to the shape. The radiation layer (231) and the dielectric layer (232) are correspondingly arranged in the containing grid (22a).

9. The method for manufacturing the skin antenna according to claim 8, characterized in that: The manufacturing method comprises manufacturing the connecting frame beam (22): Providing a plurality of arc-shaped transverse beams (221) and longitudinal beams (222), processing a first wedging groove (221a) on the transverse beam (221), and processing a second wedging groove (222a) matching the first wedging groove (221a) on the longitudinal beam (222); Adhesive is applied to the first wedging groove (221a) of the transverse beam (221) and the second wedging groove (222a) of the longitudinal beam (222) respectively, and a plurality of the transverse beams (221) and a plurality of the longitudinal beams (222) are wedged together, and then subjected to vacuum heat curing treatment.

10. An aircraft, characterized in that: It comprises the skin antenna as described in any one of claims 1 to 6, and the skin antenna serves as the outer shell of the aircraft.

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