Embedded beacon antenna structure design

Abstract

The utility model relates to the technical field of airborne equipment mechanism design, in particular to an embedded beacon antenna structure design, which comprises an aircraft skin and an antenna cover plate, a signal transmission assembly comprises an antenna radiation rod fixed on the inner bottom wall of an antenna shell, a feed head is fixedly arranged on the inner right wall of the antenna shell, and the feed head is fixedly arranged on the inner right wall of the antenna shell. The left end of the feed head is fixedly connected with a coupling ring, a capacitive load is fixedly installed on the inner left wall of the antenna shell, and an anti-interference assembly layer is arranged in the antenna shell. According to the embedded beacon antenna structure design, the antenna radiation rod, the feed head, the coupling ring and the capacitive load structure are all arranged in the antenna shell, and then the antenna shell is embedded into the aircraft through the aircraft skin, so that the antenna structure and the surface of the aircraft are conformal, and the influence on the overall aerodynamic performance of the aircraft is reduced; and the first shielding layer and the second shielding layer are additionally arranged in the antenna shell, so that the anti-interference capability of the beacon antenna during signal transmission can be further improved.

Description

Technical Field

[0001] The utility model relates to the technical field of airborne equipment mechanism design, in particular to a design of an embedded beacon antenna structure. Background Art

[0002] Beacon antennas are indispensable equipment in radio navigation systems. They mainly receive high-frequency horizontally polarized wave signals emitted by ground beacon transmitters, provide landing guidance information for aircraft, and thus ensure the safe landing of aircraft.

[0003] At present, beacon antennas basically use electrically small antennas as airborne beacon receivers, that is, the size of the antenna is very small relative to the wavelength of the antenna. At this time, the antenna can be regarded as an inductor, capacitor, or a combination of the two with very small radiation, and then the loading method is used to achieve the miniaturization of the antenna. Beacon antennas are usually composed of relatively protruding horizontal oscillators. This horizontal oscillator uses a loading load to shorten the length. When the antenna is installed on the lower part of the aircraft fuselage, it has a directional pattern with the maximum radiation direction vertically downward. Therefore, the current conventional beacon antennas are installed on the aircraft skin structure at the bottom of the aircraft skin and protrude from the outside of the fuselage.

[0004] However, the protruding antenna installation will affect the aircraft and destroy the overall streamlined structure of the aircraft surface, increase the frontal wind resistance of the aircraft, generate turbulence when the aircraft is flying at high speed, weaken the aircraft's maneuverability, and increase the aircraft's energy consumption. In addition, the protruding beacon antenna will be subjected to headwind loads, and in extreme cases the antenna cover may be damaged. Therefore, in order to solve the above-mentioned technical problems, an embedded beacon antenna structure design is proposed. Utility Model Content

[0005] In response to the shortcomings of the existing technology, the utility model provides an embedded beacon antenna structure design, which has the advantage of being able to reduce the impact of the antenna structure on the overall aerodynamic performance of the aircraft. It solves the problem in the above-mentioned background technology that the current conventional beacon antennas are installed on the aircraft skin with a structure protruding from the outside of the fuselage, which easily affects the aircraft and destroys the overall streamlined structure of the aircraft surface, resulting in increased frontal wind resistance of the aircraft and reduced maneuverability of the aircraft.

[0006] To achieve the above objectives, the present invention provides the following technical solutions: an embedded beacon antenna structure design, comprising an aircraft skin and an antenna cover fixed to the top of the aircraft skin, the top of the antenna cover being fixedly connected to an antenna housing, and a signal transmission component being disposed within the antenna housing;

[0007] The signal transmission component includes an antenna radiation rod fixed to the inner bottom wall of the antenna housing, a feed head is fixedly installed on the inner right wall of the antenna housing, a coupling ring is fixedly connected to the left end of the feed head, a capacitive load is fixedly installed on the inner left wall of the antenna housing, and an anti-interference component layer is provided inside the antenna housing.

[0008] Furthermore, a cover groove surface is provided on the top of the aircraft skin, and the bottom of the antenna cover is adaptively connected to the inner side of the cover groove surface.

[0009] Furthermore, the antenna cover and the antenna shell are both D-glass fiber structural layers, and the top of the antenna shell and the antenna cover are both curved structures.

[0010] Furthermore, the anti-interference component layer includes a first shielding layer located inside the antenna housing, and the first shielding layer is a metal shielding mesh structure.

[0011] Furthermore, an adhesive layer is laid on the outer side of the first shielding layer, and the adhesive layer is a conductive silver paste structure.

[0012] Furthermore, a second shielding layer is provided on a side of the adhesion layer away from the first shielding layer, and the second shielding layer is made of a ferrite material structure.

[0013] Beneficial effects

[0014] Compared with the existing technology, the technical solution of this application has the following beneficial effects:

[0015] The embedded beacon antenna structure is designed to place the more prominent antenna radiation rod, feed head, coupling loop and capacitive load structure in the antenna structure inside the antenna housing. The antenna housing is then embedded into the aircraft through the aircraft skin, making the antenna structure conformal to the aircraft surface, thereby reducing the impact on the overall aerodynamic performance of the aircraft. Then, a first shielding layer and a second shielding layer are added inside the antenna housing to further enhance the anti-interference capability of the beacon antenna during signal transmission. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is a three-dimensional schematic diagram of the beacon antenna structure of the utility model;

[0017] Figure 2 for Figure 1 Schematic diagram of the aircraft skin structure in perspective;

[0018] Figure 3 for Figure 1 perspective cutaway view;

[0019] Figure 4 for Figure 3 Schematic diagram of the anti-interference component layer structure in perspective;

[0020] Figure 5 This is a schematic diagram of the simulation results of the beacon antenna standing wave ratio;

[0021] Figure 6 Schematic diagram of the simulation results of the beacon antenna pattern (when phi = 0°);

[0022] Figure 7 Schematic diagram of the beacon antenna pattern simulation results (phi = 90°).

[0023] In the figure: 1. Aircraft skin; 2. Antenna cover; 3. Antenna housing; 4. Signal transmission component; 401. Antenna radiation rod; 402. Feed head; 403. Coupling ring; 404. Capacitive load; 405. Anti-interference component layer; 4051. First shielding layer; 4052. Adhesion layer; 4053. Second shielding layer. DETAILED DESCRIPTION

[0024] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0025] See also Figure 1-7 , an embedded beacon antenna structure design, including an aircraft skin 1 and an antenna cover 2 fixed to the top of the aircraft skin 1, the bottom of the antenna cover 2 is adaptively connected to the cover groove surface of the aircraft skin 1, and the top of the antenna cover 2 is fixedly connected to the antenna shell 3. The antenna cover 2 and the antenna shell 3 both adopt D glass fiber structure, and a signal transmission component 4 is arranged inside the antenna shell 3.

[0026] The signal transmission component 4 includes an antenna radiation rod 401 fixed to the inner bottom wall of the antenna housing 3, a feed head 402 is fixedly installed on the inner right wall of the antenna housing 3, a coupling ring 403 is fixedly connected to the left end of the feed head 402, and a capacitive load 404 is fixedly installed on the inner left wall of the antenna housing 3. The antenna radiation rod 401, feed head 402, coupling ring 403 and capacitive load 404 structures are all arranged inside the antenna housing 3, and an anti-interference component layer 405 is provided inside the antenna housing 3. The first shielding layer 4051 and the second shielding layer 4053 are bonded by an adhesive layer 4052.

[0027] During implementation, follow these steps:

[0028] 1) First, the antenna radiation rod 401, the feed head 402, the coupling loop 403 and the capacitive load 404 are all arranged inside the antenna housing 3;

[0029] 2) A cover groove is formed on the side of the aircraft skin 1 facing the aircraft, and the antenna cover 2 is connected to the inner side of the cover groove;

[0030] 3) The antenna housing 3 is then embedded into the aircraft structure so that the beacon antenna conforms to the aircraft surface;

[0031] 4) Finally, the first shielding layer 4051 and the second shielding layer 4053 are used to increase the anti-interference capability of the beacon antenna during signal transmission.

[0032] according to Figure 1 and Figure 3 As shown, the aircraft skin 1 is provided with a cover groove structure on the side facing the aircraft structure, and one side of the antenna cover 2 is connected and fixed to the inner side of the cover groove. The aircraft skin 1 is made of molybdenum-tungsten alloy material, which has excellent high temperature resistance and corrosion resistance, and can ensure the strength of the aircraft structure.

[0033] according to Figure 3 As shown, the antenna cover 2 and the antenna shell 3 are both made of D glass fiber material, which has the same structure as the aircraft radar cover. The D glass fiber material is a low-dielectric glass fiber structure with a low dielectric constant and tangent loss, which can meet the aircraft strength requirements and at the same time meet the beacon antenna's wave transmission performance requirements. The top of the antenna shell 3 and the antenna cover 2 can be designed with different curved surface structures to adapt to the aircraft's fluid form.

[0034] according to Figure 4 As shown, the first shielding layer 4051 is a metal shielding mesh structure, and the second shielding layer 4053 is a non-metallic ferrite material structure layer. The first shielding layer 4051 and the second shielding layer 4053 are bonded by an adhesive layer 4052. The adhesive layer 4052 is a conductive silver paste structure layer, which can play a vital role in electromagnetic interference shielding. The first shielding layer 4051 and the second shielding layer 4053 are both arranged in the inner layer structure of the antenna housing 3, which can increase the anti-interference ability of the beacon antenna during signal transmission.

[0035] according to Figure 1 As shown, compared with general beacon antennas, the embedded beacon antenna can achieve the performance of a normal external antenna, effectively reduce the wind resistance of the aircraft beacon antenna, and the air turbulence generated during high-speed flight. It can also be designed according to the skin digital model of different aircraft at different positions, and the antenna external cover surface and antenna shell can be changed. The internal structure of the antenna can remain consistent. The internal structure of the antenna is simple, does not require imported components and raw materials, can be 100% domestically produced, is easy to process, has low debugging difficulty, and can be mass-produced.

[0036] To summarize, the embedded beacon antenna structure is designed in such a way that the antenna radiation rod 401, feed head 402, coupling ring 403 and capacitive load 404 structures that are relatively prominent in the antenna structure are all arranged inside the antenna housing 3, and then the antenna housing 3 is embedded into the interior of the aircraft through the aircraft skin 1, so that the antenna structure and the aircraft surface are conformal, thereby reducing the impact on the overall aerodynamic performance of the aircraft. Then, a first shielding layer 4051 and a second shielding layer 4053 are added inside the antenna housing 3, which can further increase the anti-interference capability of the beacon antenna during signal transmission, and solves the problem in the above-mentioned background technology that the current conventional beacon antennas are all installed on the aircraft skin with a structure protruding from the outside of the fuselage, which easily affects the aircraft and destroys the overall streamlined structure of the aircraft surface, resulting in an increase in the frontal wind resistance of the aircraft and a decrease in the maneuverability of the aircraft.

[0037] It should be noted that, in this document, relational terms such as first and second, etc., are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply the existence of any such actual relationship or order between these entities or operations. Moreover, the terms "comprises," "comprising," or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article, or device comprising a series of elements includes not only those elements, but also other elements not explicitly listed, or elements inherent to such process, method, article, or device. In the absence of further limitations, an element defined by the phrase "comprising a ..." does not exclude the presence of other identical elements in the process, method, article, or device comprising the element.

[0038] Although the embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and variations may be made to these embodiments without departing from the principles and spirit of the present invention, and the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A design of an embedded beacon antenna structure, comprising an aircraft skin (1) and an antenna cover (2) fixed to the top of the aircraft skin (1), characterized in that: The top of the antenna cover (2) is fixedly connected to an antenna housing (3), and a signal transmission component (4) is provided inside the antenna housing (3); The signal transmission component (4) comprises an antenna radiation rod (401) fixed to the inner bottom wall of the antenna housing (3); a feed head (402) is fixedly mounted on the inner right wall of the antenna housing (3); a coupling ring (403) is fixedly connected to the left end of the feed head (402); a capacitive load (404) is fixedly mounted on the inner left wall of the antenna housing (3); and an anti-interference component layer (405) is provided inside the antenna housing (3).

2. The embedded beacon antenna structure design according to claim 1, characterized in that: The top of the aircraft skin (1) is provided with a cover groove surface, and the bottom of the antenna cover plate (2) is adaptively connected to the inner side of the cover groove surface.

3. The embedded beacon antenna structure design according to claim 1, characterized in that: The antenna cover plate (2) and the antenna housing (3) are both D-glass fiber structural layers, and the top of the antenna housing (3) and the antenna cover plate (2) are both curved surface structures.

4. The embedded beacon antenna structure design according to claim 1, characterized in that: The anti-interference component layer (405) comprises a first shielding layer (4051) located inside the antenna housing (3), and the first shielding layer (4051) is a metal shielding mesh structure.

5. The embedded beacon antenna structure design according to claim 4, characterized in that: An adhesive layer (4052) is laid on the outer side of the first shielding layer (4051), and the adhesive layer (4052) is a conductive silver paste structure.

6. The embedded beacon antenna structure design according to claim 5, characterized in that: The adhesion layer (4052) is provided with a second shielding layer (4053) on a side away from the first shielding layer (4051), and the second shielding layer (4053) is a ferrite material structure.

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