A wing embedded satellite communication antenna cover body

Abstract

The utility model discloses a wing embedded satellite communication antenna cover body, including wing, cover body main frame and communication part, cover body main frame sets up at the front end of wing, and communication part sets up at the top of wing, the front end of cover body main frame is provided with the partition end, and the back of cover body main frame is provided with the installation clamping groove that is hinged with wing, and the upper and lower sides of cover body main frame all are provided with a row of through groove, and the left and right ends of cover body main frame all are provided with the fixed side frame that is fixed with wing, communication part includes communication cylinder and fin antenna, and communication cylinder sets up in the inside of cover body main frame, and fin antenna is fixedly installed at the top of cover body main frame, and fin antenna covers the top surface of communication cylinder, and the inside of fin antenna is provided with the receiving column that is hinged with communication cylinder. The utility model discloses three mounting pegs in the inside of communication cylinder and is fixed with cover body main frame inner chamber, and fin antenna is hinged with communication cylinder through fixed bolt and receiving column, realizes the independent disassembly and replacement of communication part.

Description

Technical Field

[0001] This utility model relates to the field of aerospace communication antenna technology, specifically a wing-embedded satellite communication antenna cover. Background Technology

[0002] With the rapid development of aerospace technology, hypersonic vehicles, drone swarms, and new-generation military and civilian aircraft have placed higher demands on the performance of satellite communication systems.

[0003] Traditional airborne satellite communication antennas typically employ external or protruding designs. External antennas disrupt the streamlined structure of the aircraft surface, increasing drag, reducing fuel efficiency, and easily causing aerodynamic noise and vibration, especially at high speeds. Furthermore, some existing antennas have complex connection methods to the wing, insufficient structural integration, and difficulty in achieving rapid disassembly and replacement, resulting in low maintenance efficiency. Therefore, a wing-embedded satellite communication antenna radome is proposed. Utility Model Content

[0004] This invention provides a wing-embedded satellite communication antenna radome, which aims to improve the problems of limited aerodynamic performance and inconvenient modular rapid maintenance.

[0005] This utility model is implemented as follows: a wing-embedded satellite communication antenna radome, including a wing, a radome main frame and a communication component, wherein the radome main frame is located at the front end of the wing and the communication component is located at the top of the wing;

[0006] The front end of the main frame of the cover is provided with a partition end, the back side of the main frame of the cover is provided with an installation clamping groove that engages with the wing, the upper and lower sides of the main frame of the cover are provided with a row of flow grooves, and the left and right ends of the main frame of the cover are provided with fixed side frames that are fixed to the wing.

[0007] The communication components include a communication column and a fin antenna. The communication column is located inside the main frame of the enclosure, and the fin antenna is fixedly installed on the top of the main frame of the enclosure. The fin antenna covers the top surface of the communication column, and a receiving column that engages with the communication column is located inside the fin antenna.

[0008] Preferably, one end of each of the two fixed side frames is provided with a transition plate that is connected to the main frame of the cover. The fixed side frames are snapped onto the front end of the wing, and the inner threads of the fixed side frames are fitted with threaded bolts that are fixed to the outer surface of the wing.

[0009] Preferably, the dividing end divides the main frame of the enclosure into two symmetrical parts, upper and lower. The outer surface of the dividing end is coated with a high-temperature resistant coating, and the dividing end is tangent to the two sides of the main frame of the enclosure.

[0010] Preferably, an arc-shaped layer is provided on the back side of the main frame of the canopy, the bottom of the arc-shaped layer is in contact with the top surface of the wing, and a flow groove is provided on the front side of the top of the main frame of the canopy that runs through the arc-shaped layer, with the inner surface of the flow groove being parallel to the top surface of the wing.

[0011] Preferably, the outer wall of the mounting slot is provided with a weather-resistant pressure layer that fits against the wing, and the back side of the arc-shaped layer is provided with a positioning screw groove that communicates with the wing. The inner side of the positioning screw groove is provided with a headless screw that is fixed to the wing.

[0012] Preferably, an electrostatic brush located outside the arc-shaped layer can be threadedly installed on the inner side of the positioning screw groove. The electrostatic brush is in contact with the headless screw and is lower than the opening of the flow groove.

[0013] Preferably, the top surface of the communication column is provided with a pressure plate that is coplanar with the top of the main frame of the radome. The pressure plate is in contact with the bottom surface of the fin antenna. The inner wall of the communication column is provided with three mounting bolts that are fixed to the inner cavity of the main frame of the radome. The inner cavity of the communication column is provided with six transmission columns arranged in a circular array. A common connecting ring is provided between the six transmission columns. The mounting bolts are fixed to the transmission columns.

[0014] Preferably, the top inner side of the fin antenna is provided with a fixing bolt that is fixed to the inner cavity of the main frame of the fin antenna, and the bottom of the fin antenna is fixedly installed with a receiving column that engages with the communication column. The bottom end of the receiving column adopts a spring probe structure. The receiving column is snapped into the inner side of the transmission column. The inner cavity of the fin antenna is provided with a communication module that is electrically connected to the receiving column.

[0015] Compared with the prior art, the beneficial effects of this utility model are:

[0016] 1. This utility model is provided with a main frame of the cover and a mounting slot. By embedding the wing into the inner wall groove of the mounting slot, the wing is completely fitted with a uniform radius of curvature, eliminating the protruding structure of traditional external antennas. At the same time, flow channels are opened on the upper and lower sides of the main frame of the cover to form airflow channels, which accelerates airflow during flight and reduces the surface temperature of the cover.

[0017] 2. This utility model is equipped with a fixed side frame, which is stably connected to the front end of the wing by threaded bolts, and fixed to the top of the wing by positioning screw grooves and headless screws, so as to achieve quick snap-fit ​​and disassembly. At the same time, three mounting bolts are set inside the communication column to fix it to the inner cavity of the main frame of the cover. The fin antenna is snapped to the communication column by fixing bolts and receiving column, so as to achieve independent disassembly and replacement of communication components. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the structure of this utility model;

[0019] Figure 2 This is a schematic diagram of the fixed side frame structure of this utility model;

[0020] Figure 3 This is a schematic diagram of the structure at the connection between the main frame of the cover and the wing of this utility model;

[0021] Figure 4 This is a side view cross-sectional structural diagram of the present invention;

[0022] Figure 5 This is a schematic diagram of the internal structure of the communication column and fin antenna of this utility model.

[0023] In the diagram: 1. Wing; 2. Main frame of the enclosure; 21. Mounting slot; 22. Arc-shaped layer; 23. Positioning screw slot; 24. Electrostatic brush; 25. Weather-resistant pressure layer; 3. Separator end; 4. Fixed side frame; 41. Threaded bolt; 42. Transition plate; 5. Communication column; 51. Pressure plate; 52. Transfer column; 53. Connecting ring; 54. Mounting bolt; 6. Fin antenna; 61. Fixing bolt; 62. Receiving column; 63. Communication module; 7. Flow channel. Detailed Implementation

[0024] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0025] In the description of this utility model, it should be understood that the terms "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0026] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0027] Example 1

[0028] Please see Figure 1-4A wing-embedded satellite communication antenna radome includes a wing 1, a radome main frame 2, and communication components. The radome main frame 2 is located at the front end of the wing 1, and the communication components are located at the top of the wing 1. A mounting groove 21 is formed on the back side of the radome main frame 2 to engage with the wing 1. The radius of curvature of the groove is consistent with the surface of the wing 1, achieving seamless conformal embedding. The outer wall of the mounting groove 21 is provided with a weather-resistant pressure-resistant layer 25 made of rubber or silicone material, which adheres tightly to the surface of the wing 1 to prevent moisture intrusion.

[0029] The front end of the main frame 2 of the cover is provided with a dividing end 3, which divides the main frame 2 of the cover into two symmetrical parts, upper and lower. The outer surface of the dividing end 3 is coated with a high temperature resistant coating, which can withstand high temperature. The dividing end 3 is tangent to the two sides of the main frame 2 of the cover, which can release the impacted airflow from both sides and ensure a smooth transition of the aerodynamic shape.

[0030] The main frame 2 of the cover is equipped with fixed side frames 4 at both ends, which are fixed to the wings 1. One end of each fixed side frame 4 is equipped with a transition plate 42 connected to the main frame 2 of the cover to ensure the curvature of the connection and avoid the occurrence of angles that would increase the flight drag of the wings 1. The fixed side frame 4 is snapped into the front end of the wings 1. The inner thread of the fixed side frame 4 is fitted with a threaded bolt 41 that is fixed to the outer surface of the wings 1. One end of the bolt is located on the inner side of the fixed side frame 4 and the other end is located on the inner front end of the wings 1 to ensure the stability of the two when they are engaged and embedded.

[0031] A row of flow grooves 7 is opened on both the upper and lower sides of the main frame 2 of the cover. An arc-shaped layer 22 is provided on the back side of the main frame 2 of the cover. The bottom of the arc-shaped layer 22 is in contact with the top surface of the wing 1. A flow groove 7 that runs through the arc-shaped layer 22 is opened on the front side of the top of the main frame 2 of the cover. The inner surface of the flow groove 7 is parallel to the top surface of the wing 1, forming an airflow channel to reduce the surface temperature of the main frame 2 of the cover.

[0032] A hydrophobic coating can be applied to the inner wall of the flow channel 7 to prevent ice and rainwater accumulation.

[0033] like Figure 4 As shown, the back side of the arc-shaped layer 22 is provided with a positioning screw groove 23 that communicates with the wing 1, and the inner side of the positioning screw groove 23 is provided with a headless screw that is fixed to the wing 1.

[0034] The inner side of the positioning screw groove 23 can be threaded with an electrostatic brush 24 located on the outer side of the arc-shaped layer 22. The electrostatic brush 24 is in contact with the headless screw, which can guide the static electricity of the cover and the wing 1 into the atmosphere to prevent the accumulation of static electricity from causing electromagnetic interference. At the same time, the electrostatic brush 24 is lower than the opening of the flow groove 7 to avoid affecting the aerodynamic performance.

[0035] It should be noted that the main frame 2 of the cover adopts a modular design, and the fixed side frame 4 and positioning screw groove 23 can be quickly disassembled, greatly reducing maintenance time.

[0036] Example 2

[0037] Please see Figure 1 , 3 4, 5. The communication component includes a communication column 5 and a fin antenna 6. The communication column 5 is located inside the main frame 2 of the enclosure. The fin antenna 6 is fixedly installed on the top of the main frame 2 of the enclosure. The fin antenna 6 covers the top surface of the communication column 5. A receiving column 62 that is engaged with the communication column 5 is provided inside the fin antenna 6.

[0038] The top surface of the communication column 5 is provided with a pressure plate 51 that is coplanar with the top of the main frame 2 of the radome. The pressure plate 51 is in contact with the bottom surface of the fin antenna 6 to ensure mechanical stability. The inner wall of the communication column 5 is provided with three mounting bolts 54 that are fixed to the inner cavity of the main frame 2 of the radome. The mounting bolts 54 can be made of high-strength carbon fiber composite material to reduce weight.

[0039] like Figure 5 As shown, the inner cavity of the communication column 5 is provided with six transmission columns 52 arranged in a circular array. The six transmission columns 52 are connected by a common connecting ring 53 to realize the interconnection of electrical signals and avoid individual damage that would affect the overall communication effect. The mounting bolts 54 are fixed to the transmission columns 52, which can realize the quick installation and removal of the whole.

[0040] The top inner side of the fin antenna 6 is provided with a fixing bolt 61 that is fixed to the inner cavity of the main frame 2 of the fin antenna. The bottom of the fin antenna 6 is fixedly installed with a receiving post 62 that engages with the communication post 5. The receiving post 62 is snapped into the inner side of the transmission post 52. The receiving post 62 adopts a spring probe structure to ensure reliable contact with the transmission post 52, adapt to vibration during flight, and realize stable transmission of electrical signals. The inner cavity of the fin antenna 6 is provided with a communication module 63 that is electrically connected to the receiving post 62.

[0041] It should be noted that the satellite signal is received by the internal communication module 63 of the fin antenna 6, transmitted through the receiving column 62 to the transmission column 52 inside the communication column 5, and then collected by the connecting ring 53 before being transmitted to the airborne communication equipment through the internal cable of the wing 1.

[0042] The transmitted signal can be transmitted in reverse, enabling bidirectional communication.

[0043] Although 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 alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A wing-embedded satellite communication antenna radome, comprising a wing (1), a radome main frame (2), and communication components, wherein the radome main frame (2) is disposed at the front end of the wing (1), and the communication components are disposed at the top of the wing (1); characterized in that The front end of the main frame (2) of the cover is provided with a partition end (3), the back side of the main frame (2) of the cover is provided with an installation clamping groove (21) that engages with the wing (1), the upper and lower sides of the main frame (2) of the cover are provided with a row of flow grooves (7), and the left and right ends of the main frame (2) of the cover are provided with fixed side frames (4) that are fixed to the wing (1). The communication component includes a communication column (5) and a fin antenna (6). The communication column (5) is located inside the main frame (2) of the enclosure. The fin antenna (6) is fixedly installed on the top of the main frame (2) of the enclosure. The fin antenna (6) covers the top surface of the communication column (5). A receiving column (62) that is engaged with the communication column (5) is provided inside the fin antenna (6).

2. A radome for a wing-mounted satellite communication antenna according to claim 1, characterized in that: One end of each of the two fixed side frames (4) is provided with a transition plate (42) connected to the main frame (2) of the cover. The fixed side frame (4) is snapped onto the front end of the wing (1). The inner thread of the fixed side frame (4) is fitted with a threaded bolt (41) that is fixed to the outer surface of the wing (1).

3. A conformal satellite communication antenna radome for an aircraft wing according to claim 1, wherein: The dividing end (3) divides the main frame (2) of the cover into two symmetrical parts, the outer surface of the dividing end (3) is coated with a high temperature resistant coating, and the dividing end (3) is tangent to the two sides of the main frame (2).

4. A conformal satellite communication antenna radome for an aircraft wing according to claim 3, wherein: An arc-shaped layer (22) is provided on the back side of the main frame (2) of the cover. The bottom of the arc-shaped layer (22) is in contact with the top surface of the wing (1). A flow groove (7) is provided on the front side of the top of the main frame (2) of the cover, which passes through the arc-shaped layer (22). The inner groove surface of the flow groove (7) is parallel to the top surface of the wing (1).

5. A conformal satellite communication antenna radome for an aircraft wing according to claim 4, wherein: The outer wall of the mounting groove (21) is provided with a weather-resistant pressure layer (25) that fits against the wing (1). The back side of the arc-shaped layer (22) is provided with a positioning screw groove (23) that communicates with the wing (1). The inner side of the positioning screw groove (23) is provided with a headless screw that is fixed to the wing (1).

6. A conformal satellite communication antenna radome for an aircraft wing according to claim 5, wherein: An electrostatic brush (24) located outside the arc-shaped layer (22) can be threaded onto the inner side of the positioning screw groove (23). The electrostatic brush (24) is in contact with the headless screw and is lower than the opening of the flow groove (7).

7. The embedded wing satellite communication antenna radome of claim 1, wherein: The top surface of the communication column (5) is provided with a pressure plate (51) that is coplanar with the top of the main frame (2) of the hood. The pressure plate (51) is in contact with the bottom surface of the fin antenna (6). The inner wall of the communication column (5) is provided with three mounting bolts (54) that are fixed to the inner cavity of the main frame (2). The inner cavity of the communication column (5) is provided with six transmission columns (52) arranged in a circular array. A common connecting ring (53) is provided between the six transmission columns (52). The mounting bolts (54) are fixed to the transmission columns (52).

8. A conformal satellite communication antenna radome for an aircraft wing according to claim 7, wherein: The top inner side of the fin antenna (6) is provided with a fixing bolt (61) that is fixed to the inner cavity of the main frame (2) of the fin antenna (6). The bottom of the fin antenna (6) is fixedly installed with a receiving column (62) that engages with the communication column (5). The bottom end of the receiving column (62) adopts a spring probe structure. The receiving column (62) is snapped into the inner side of the transmission column (52). The inner cavity of the fin antenna (6) is provided with a communication module (63) that is electrically connected to the receiving column (62).

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