Satellite terminal structure

Abstract

The utility model provides a satellite terminal structure which comprises an antenna cover, a middle frame and a rear shell, the antenna cover and the rear shell are connected to two opposite sides of the middle frame in a sealed mode, a sealed cavity is formed by the antenna cover and the rear shell, and an antenna assembly is located in the sealed cavity and fixed to the middle frame. The outer edge of the middle frame is exposed out of the sealing cavity to form a heat dissipation part. The satellite terminal structure is of a three-layer structure, the middle frame serves as a main body, the two sides of the middle frame are connected with the antenna cover and the rear shell in a sealed mode respectively to surround the middle frame to form a sealed cavity, and the antenna assembly is arranged in the sealed cavity. The edge part of the middle frame is exposed out of the antenna cover and the rear shell and forms a heat dissipation part, so that heat of the antenna assembly in the sealing cavity can be conducted to the outer side of the sealing cavity through the middle frame and dissipated through the heat dissipation part. Compared with the prior art, the LED lamp has the advantages of higher waterproofness and higher environmental adaptability, can be used in outdoor complex environments such as a humid environment, is higher in heat dissipation efficiency, and can meet the requirements of markets and users.

Description

TECHNICAL FIELD

[0001] The utility model relates to satellite communication field, especially a kind of satellite terminal structure. BACKGROUND

[0002] With the continuous progress of global communication technology, low-orbit satellite communication has become an important means to realize global coverage and high data transmission. As a key component of low-orbit satellite communication, the development and application of low-orbit phased array satellite terminal are crucial. As a carrier, the structure of low-orbit phased array satellite terminal not only relates to the overall performance and reliability of the communication system, but also directly affects the user experience. The existing terminal structure has large thickness size, heavy weight, is not convenient to carry, and has poor environmental adaptability, single terminal application scenario and limited use. SUMMARY

[0003] The technical problem to be solved by the utility model is to overcome the defects of the terminal structure of the prior art, such as large thickness size, heavy weight, inconvenience to carry, poor environmental adaptability, single terminal application scenario and limited use, and to provide a satellite terminal structure.

[0004] The utility model solves the above technical problems by the following technical scheme:

[0005] A satellite terminal structure, characterized in that it comprises: a radome, a middle frame and a rear shell, the radome and the rear shell are sealingly connected to the opposite sides of the middle frame, the radome and the rear shell form a sealed cavity, and the antenna assembly is located in the sealed cavity and fixed to the middle frame.

[0006] The outer edge of the middle frame is exposed to the sealed cavity to form a heat dissipation part.

[0007] In the present scheme, the satellite terminal structure is a three-layer structure with the middle frame as the main body. The radome and the rear shell are sealingly connected to the two sides of the middle frame to form a sealed cavity around the middle frame. The antenna assembly is arranged in the sealed cavity. The edge part of the middle frame is exposed to the radome and the rear shell and forms a heat dissipation part, so that the heat of the antenna assembly in the sealed cavity can be conducted to the outside of the sealed cavity through the middle frame and dissipated through the heat dissipation part. It has high waterproofness, stronger environmental adaptability, can be used in complex outdoor environments such as humid environments, and has higher heat dissipation efficiency, which can meet the market and user demand.

[0008] Preferably, the antenna assembly comprises a phased array antenna board and a chip board group.

[0009] The sealed cavity is divided into an upper cavity and a lower cavity by the middle frame, and the shape and size of the middle frame are comparable to those of the phased array antenna board.

[0010] The phased array antenna board is located in the upper cavity and is mounted on one side of the middle frame, and the chip board group is located in the lower cavity and is mounted on the other side of the middle frame.

[0011] In the scheme, the satellite terminal structure is three-layer structure, the middle frame forms upper and lower cavities with the radome and the rear shell respectively, the upper cavity is used to place the phased array antenna board to make its signal receiving capacity best. The transverse size of the middle frame is equivalent to the phased array antenna board, so that the transverse size of the whole satellite terminal structure can just place the antenna board, the lower cavity is used to place other chip board groups, other chip board groups are placed directly below the phased array antenna board, and the longitudinal space is utilized without additional transverse space, so that the satellite terminal occupies less space while ensuring the antenna area and has better portability. In addition, the chips in the upper and lower cavities are fixed through the middle frame, so that the heat of the chips in the upper and lower cavities can be conducted out through the middle frame, and the heat dissipation efficiency is also higher.

[0012] Preferably, the antenna assembly further comprises a GPS antenna and / or a WIFI antenna, and a corresponding mounting groove is formed in the middle frame, and the GPS antenna and / or the WIFI antenna are arranged in the mounting groove when the antenna assembly is mounted on the middle frame.

[0013] In the scheme, the GPS antenna and the WIFI antenna are placed in the corresponding mounting groove formed in the middle frame, so that the heat dissipation effect is better and the integration is higher.

[0014] Preferably, the radome and the rear shell are respectively bonded to two sides of the middle frame.

[0015] In the scheme, the satellite terminal structure is assembled without using screws, and is bonded by using structural adhesive, so that the sealing performance is good and the structure is simple.

[0016] Preferably, a groove is arranged on one side of the heat dissipation part facing the radome and / or one side of the heat dissipation part facing the rear shell, a protruding part facing the heat dissipation part is arranged on the radome and / or the rear shell in correspondence, and structural adhesive is arranged in the groove, and the protruding part extends into the groove to bond the middle frame and the radome and / or the rear shell.

[0017] In the scheme, the radome, the rear shell and the middle frame have matching embedded structures. When assembled, the protruding parts on the radome and the rear shell are embedded into the groove of the heat dissipation part of the middle frame, and structural adhesive is arranged in the groove, so that the embedded parts can be bonded after embedding, the connection strength is ensured, the embedded structure with the groove containing structural adhesive also has excellent sealing performance, and the environmental adaptability is also stronger.

[0018] Preferably, the heat dissipation part surrounds the sealing cavity in a closed ring shape.

[0019] In the scheme, the above structure is adopted, so that the heat can be uniformly conducted and dissipated, and the heat dissipation effect is better.

[0020] Preferably, the heat dissipation part comprises a plurality of heat dissipation teeth with gaps.

[0021] In the scheme, the above structure is adopted, and the heat dissipation tooth structure is adopted. The plurality of heat dissipation teeth with gaps can increase the heat exchange area and improve the heat dissipation effect.

[0022] Preferably, the heat dissipation part comprises a hydrophobic coating.

[0023] In the scheme, the above structure is adopted. The heat dissipation part of the middle frame exposed to air is sprayed for protection, the salt mist resistance and other performances are good, and the environmental adaptability is further improved.

[0024] Preferably, the middle frame is made of aluminum alloy material.

[0025] In the scheme, the above structure is adopted. The aluminum alloy material has high thermal conductivity, stronger heat dissipation effect, and lighter weight, and is more portable.

[0026] Preferably, a heat conduction boss is arranged on the middle frame, a heat conduction gasket is arranged on the heat conduction boss, and the antenna assembly is fixed to the middle frame through the heat conduction boss.

[0027] In the scheme, the above structure is adopted. The heat conduction boss is designed at the corresponding position of the middle frame. The heat conduction gasket is filled between the heat conduction boss and the chip. The heat generated by the chip can be conducted to the middle frame in time, and the heat dissipation effect is better.

[0028] Preferably, the phased array antenna board of the antenna assembly is a tile type phased array antenna, and an FPC flat cable is connected.

[0029] In the scheme, the above structure is adopted. The tile type phased array antenna can greatly reduce the height of the device, and further improve the portability of the terminal.

[0030] Preferably, a screw hole is arranged on the bottom of the rear shell, and the satellite terminal structure further comprises a seat screw, which is threadedly connected to the screw hole.

[0031] In the scheme, the above structure is adopted. The seat screw can be used as a simple base support. The satellite terminal can be directly placed on a plane. In addition, the seat screw can be removed. After being removed, the screw hole can also extend a variety of support accessories and other accessories, and the environmental adaptability is stronger.

[0032] Preferably, the rear shell is further provided with a breathable hole, and a breathable waterproof film is arranged on the inner side of the breathable hole.

[0033] In the scheme, the above structure is adopted, the water-tightness is ensured through the water-proof film, the air permeability hole does not affect the sealing property of the terminal, and the environmental adaptability is not sacrificed.

[0034] The positive progress effect of the utility model lies in: a satellite terminal structure, comprising: a radome, a middle frame and a rear shell, the radome and the rear shell are sealingly connected on the opposite sides of the middle frame, the radome and the rear shell form a sealed cavity, and the antenna assembly is located in the sealed cavity and fixed to the middle frame; the outer edge of the middle frame is exposed to the sealed cavity to form a heat dissipation part. The satellite terminal structure is a three-layer structure, taking the middle frame as the main body, the two sides of the middle frame are sealingly connected with the radome and the rear shell to form a sealed cavity around the middle frame, and the antenna assembly is arranged in the sealed cavity. The edge part of the middle frame is exposed to the radome and the rear shell and forms a heat dissipation part, so that the heat of the antenna assembly in the sealed cavity can be conducted to the outside of the sealed cavity through the middle frame and dissipated through the heat dissipation part. It has higher waterproofness, stronger environmental adaptability, can be used in complex environments such as wet environments, and has higher heat dissipation efficiency, which can ensure that it meets the needs of the market and users. BRIEF DESCRIPTION OF DRAWINGS

[0035] Figure 1 It is an explosion schematic view of the satellite terminal structure of the utility model embodiment.

[0036] Figure 2 It is a cross-sectional schematic view of the satellite terminal structure of the utility model embodiment.

[0037] Figure 3 It is a heat dissipation state schematic view of the middle frame of the utility model embodiment.

[0038] Figure 4 It is a structure schematic view of the middle frame of the utility model embodiment.

[0039] Figure 5 It is a schematic view of the phased array antenna of the utility model embodiment.

[0040] Figure 6 It is a structure schematic view of the satellite terminal structure and the support of the utility model embodiment.

[0041] BRIEF DESCRIPTION OF DRAWINGS:

[0042] Radome 1

[0043] GPS antenna 2

[0044] WIFI antenna 3

[0045] Phased array antenna board 4

[0046] Middle frame 5

[0047] Interface board 6

[0048] Baseband plate 7

[0049] FPC flexible flat cable 8

[0050] Connecting cable 9

[0051] Breathable and waterproof membrane 10

[0052] Back cover 11

[0053] Seat Cushion Screw 12

[0054] Heat dissipation section 13

[0055] Vent hole 14

[0056] Protrusion 15

[0057] Groove 16

[0058] Thermal boss 17

[0059] Thermal pad 18

[0060] Chip 19

[0061] PCB board 20

[0062] 21 heat dissipation teeth

[0063] Through hole 22

[0064] Mounting slot 23

[0065] Terminal 24

[0066] Bracket 25

[0067] Upper cavity 26

[0068] Lower cavity 27 Detailed Implementation

[0069] The present invention will be described more clearly and completely below with reference to the accompanying drawings, using a preferred embodiment.

[0070] This embodiment provides a satellite terminal 24 structure, such as Figure 1 As shown, the terminal 24 consists of an antenna cover 1, a GPS antenna 2, a WIFI antenna 3, a phased array antenna board 4, a middle frame 5, an interface board 6, a baseband board 7, an FPC flexible flat cable 8, a connecting cable 9, a breathable and waterproof membrane 10, a rear shell 11, and seat screws 12. The antenna cover 1 and the rear shell 11 are sealed together on opposite sides of the middle frame 5, forming a sealed cavity. The antenna assembly is located within the sealed cavity and fixed to the middle frame 5. The outer edge of the middle frame 5 is exposed outside the sealed cavity, forming a heat dissipation section 13.

[0071] The satellite terminal 24 is a three-layer structure, taking the middle frame 5 as the main body, the middle frame 5 is sealed and connected with the radome 1 and the back shell 11 on both sides to form a sealed cavity around the middle frame 5, wherein the radome 1 faces up and forms an upper cavity 26 with the upper side of the middle frame 5; the back shell 11 faces down and forms a lower cavity 27 with the middle frame 5. The antenna assembly is arranged in the sealed cavity. The radome 1 and the back shell 11 are located at the upper end and the lower end of the middle frame 5 in the vertical direction, respectively, and are connected with the top surface and the bottom surface of the middle frame 5, respectively. The size of the middle frame 5 in the horizontal direction is larger than that of the radome 1 and the back shell 11, and when connected, the edge part of the middle frame 5 will protrude out of the radome 1 and the back shell 11. The protruding part forms a heat dissipation part 13, so that the heat of the antenna assembly in the sealed cavity can be conducted to the outside of the sealed cavity through the middle frame 5 and dissipated through the heat dissipation part 13.

[0072] This structure has high waterproofness and stronger environmental adaptability, and can be used in complex outdoor environments such as humid environments, and has higher heat dissipation efficiency, which can ensure that it meets the needs of the market and users.

[0073] As shown in Figure 1 , 2 , the antenna assembly includes a phased array antenna board 4 and a chip board group. The sealed cavity is divided into an upper cavity 26 and a lower cavity 27 by the middle frame 5, and the shape and size of the middle frame 5 are comparable to those of the phased array antenna board 4. The phased array antenna board 4 is located in the upper cavity 26 and is installed on one side of the middle frame 5, and the chip board group is located in the lower cavity 27 and is installed on the other side of the middle frame 5.

[0074] Specifically, the chip board group includes an interface board 6 and a baseband board 7. The phased array antenna board 4, the interface board 6 and the baseband board 7 are all PCB boards 20 with chips, and are all fixed on the upper and lower sides of the middle frame 5 and located in the upper cavity 26 and the lower cavity 27, respectively. The upper cavity 26 is used to place the phased array antenna board 4 to make its signal receiving capacity best. The transverse size of the middle frame 5 is comparable to that of the phased array antenna board 4, so that the transverse size of the entire satellite terminal 24 structure can just place the antenna board, and the lower cavity 27 is used to place other chip board groups, which are placed directly below the phased array antenna board 4, using longitudinal space without additional transverse space, so that the satellite terminal 24 occupies less space while ensuring the antenna area, and has better portability. In addition, the chips in the upper cavity 26 and the lower cavity 27 are fixed through the middle frame 5, so that the heat of the chips in the upper and lower cavities 27 can be conducted away through the middle frame 5, and the heat dissipation efficiency is also higher.

[0075] In addition, as shown in Figure 1 , 4As shown, the antenna assembly further comprises a GPS antenna 2 and a WIFI antenna 3, and the middle frame 5 is provided with corresponding installation grooves 23, and when the antenna assembly is installed on the middle frame 5, the GPS antenna 2 and the WIFI antenna 3 are arranged in the installation grooves 23. Placing the GPS antenna 2 and the WIFI antenna 3 in the corresponding installation grooves 23 on the middle frame 5 has better heat dissipation effect and higher integration. The middle frame 5 is provided with a through port, which can communicate between the upper and lower sides, so that the chip assemblies in the upper cavity 26 and the lower cavity 27 can be connected to each other.

[0076] As shown in Figure 1 , 4 , the circumferential direction of the middle frame 5 in the horizontal direction is greater than that of the radome 1 and the back cover, so that the heat dissipation part 13 is formed in the circumferential direction, and the heat dissipation part 13 surrounds the sealed cavity to form a closed ring. The heat can be uniformly conducted and dissipated, and the heat dissipation effect is better. In other embodiments, the heat dissipation part 13 can also be formed only in a local part to adapt to other structural requirements.

[0077] The specific connection mode of the satellite terminal 24 structure in the embodiment is shown in the figure, and the specific heat dissipation effect of the middle frame 5 is shown in Figure 3 . The middle frame 5 is made of aluminum alloy. The aluminum alloy has high thermal conductivity, strong heat dissipation effect, light weight and portability. In other embodiments, other conventional high-thermal-conductivity high-strength materials can also be used.

[0078] The heat dissipation part 13 comprises a plurality of heat dissipation teeth 21 with gaps. The heat dissipation teeth 21 are concave-convex structures formed on the outer surface of the heat dissipation part 13. Through the concave-convex structures, the plurality of heat dissipation teeth 21 with gaps can increase the heat exchange area and improve the heat dissipation effect.

[0079] As shown in Figure 3 , the middle frame 5 is provided with a heat-conducting boss 17, and the heat-conducting boss 17 is provided with a heat-conducting gasket. The antenna assembly is fixed to the middle frame 5 through the heat-conducting boss 17. The heat-conducting boss 17 is designed at the corresponding position of the middle frame 5, and the heat-conducting gasket is filled between the heat-conducting boss 17 and the chip 19. The heat generated by the chip 19 can be conducted to the middle frame 5 in time, and the heat dissipation effect is better.

[0080] In addition, the heat dissipation part 13 in the embodiment comprises a hydrophobic coating. The heat dissipation part 13 of the middle frame 5 exposed to the air is sprayed with a protective coating, which has good salt mist resistance and other properties, and further improves environmental adaptability. The layer can be 10% titanium dioxide and a hydrophobic coating. In other embodiments, other common coatings can also be used according to other requirements.

[0081] In the embodiment, the specific connection mode of the satellite terminal 24 structure is shown in Figure 2 . The radome 1 and the back shell 11 are respectively bonded to the two sides of the middle frame 5. The satellite terminal 24 structure does not use screws for assembly, but uses structural adhesive for bonding, which has good sealing performance and simple structure.

[0082] Specifically, as shown in Figure 2 The heat dissipation part 13 is provided with a groove 16 on the side facing the radome 1 and the side facing the back shell 11, and the radome 1 and the back shell 11 are correspondingly provided with a protrusion 15 facing the heat dissipation part 13, and the groove 16 is provided with structural adhesive, and the protrusion 15 extends into the groove 16 to bond the middle frame 5 and the radome 1 and / or the back shell 11. The radome 1, the back shell 11 and the middle frame 5 have a matching fitting structure. When assembled, the protrusion 15 on the radome 1 and the back shell 11 is embedded in the groove 16 of the heat dissipation part 13 of the middle frame 5, and the groove 16 is provided with structural adhesive, so that it can be bonded after embedding, ensuring the connection strength, and the groove 16 containing the structural adhesive also has the effect of a sealing ring, and the fitting structure also has excellent sealing performance and stronger environmental adaptability.

[0083] The phased array antenna can be divided into a tile type structure and a brick type structure according to the TR component and antenna integration mode. The brick type phased array antenna has a large volume, high loss and high cost, and is produced by using a micro assembly process, and the yield of good products is low.

[0084] The phased array antenna board 4 of the embodiment is a tile type phased array antenna, and is connected by using an FPC flat cable. The tile type phased array antenna can greatly reduce the equipment height and further improve the portability of the terminal 24. The tile type phased array antenna architecture is shown in Figure 5 Specifically, the antenna array, the TR component and the feed network are integrated on a microwave multilayer PCB board 20. The tile type phased array antenna reduces the connector interconnection between the antenna and the TR, and replaces the entire micro-assembled TR module with a TR chip, and integrates multiple components into a PCB board 20, which can greatly reduce the equipment height, that is, the low profile.

[0085] As shown in Figure 1 The back shell 11 is also provided with a breathable hole 14, and the inner side of the breathable hole 14 is provided with a breathable waterproof membrane 10. The breathability is ensured, the heat dissipation effect is stronger, the waterproofness is ensured by the waterproof membrane, the breathable hole 14 does not affect the sealing performance of the terminal 24, and the environmental adaptability is not sacrificed.

[0086] As shown in Figure 1 The back shell 11 is provided with a threaded hole at the bottom, and the satellite terminal 24 structure further includes a cushion screw 12 which is threadedly connected to the threaded hole. The cushion screw 12 is usually used to fill the threaded hole, and can also be used as a simple base support, so that the satellite terminal 24 can be directly placed on a plane. In addition, the cushion screw 12 can be removed, and after being removed, the threaded hole can also be expanded to a support 25 and other accessories of multiple use scenarios, and the environmental adaptability is stronger, as shown in Figure 6 .

[0087] Although the specific embodiments of the present application are described above, those skilled in the art should understand that this is only an example, the protection scope of the present application is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principles and essence of the present application, but these changes and modifications all fall within the protection scope of the present application.

Claims

1. A satellite terminal structure, characterized by, It includes: The radome, the middle frame, the back shell and the antenna assembly, the radome and the back shell are sealed and connected on the opposite sides of the middle frame, the radome and the back shell form a sealed cavity, and the antenna assembly is located in the sealed cavity and fixed to the middle frame; The outer edge of the middle frame is exposed to the sealed cavity to form a heat dissipation part.

2. The satellite terminal structure of claim 1, wherein, The antenna assembly includes a phased array antenna board and a chip board group; The sealed cavity is divided into an upper cavity and a lower cavity by the middle frame, and the shape and size of the middle frame are equivalent to the phased array antenna board; The phased array antenna board is located in the upper cavity and is installed on one side of the middle frame, and the chip board group is located in the lower cavity and is installed on the other side of the middle frame.

3. The satellite terminal structure of claim 1, wherein, The antenna assembly also includes a GPS antenna and / or a WIFI antenna, and the middle frame is provided with a corresponding installation slot, and when the antenna assembly is installed on the middle frame, the GPS antenna and / or the WIFI antenna are arranged in the installation slot.

4. The satellite terminal structure of claim 1, wherein, The radome and the back shell are respectively bonded to the two sides of the middle frame.

5. The satellite terminal structure of claim 4, wherein, The heat dissipation part is provided with a groove on the side facing the radome and / or the back shell, and the radome and / or the back shell are correspondingly provided with a protrusion facing the heat dissipation part, and the groove is provided with a structural adhesive, and the protrusion extends into the groove to bond the middle frame and the radome and / or the back shell.

6. The satellite terminal structure of claim 1, wherein, The heat dissipation part surrounds the sealed cavity in a closed ring shape.

7. The satellite terminal structure of claim 1, wherein, The heat dissipation part includes a plurality of heat dissipation teeth with gaps.

8. The satellite terminal structure of claim 1, wherein, The heat dissipation part includes a hydrophobic coating.

9. The satellite terminal structure of claim 1, wherein, The middle frame is made of aluminum alloy material.

10. The satellite terminal structure of claim 1, wherein, The middle frame is provided with a heat conduction boss, and the heat conduction boss is provided with a heat conduction gasket, and the antenna assembly is fixed to the middle frame through the heat conduction boss.

11. The satellite terminal structure of claim 1, wherein, The phased array antenna board of the antenna assembly is a tile type phased array antenna, and is connected by FPC wiring.

12. The satellite terminal structure of claim 1, wherein, The back shell is provided with a screw hole at the bottom, and the satellite terminal structure further includes a cushion screw, which is threadedly connected to the screw hole.

13. The satellite terminal structure of claim 1, wherein, The back shell is also provided with a breathable hole, and the inside of the breathable hole is provided with a breathable waterproof film.

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