Receiving airborne equipment based on satellite communication

Abstract

The invention relates to the technical field of satellite communication, and discloses a receiving airborne device based on satellite communication. The receiving airborne equipment based on satellite communication comprises a machine body shell and a satellite communication antenna, a columnar shell extending to the upper portion of the machine body shell is embedded in the top of the machine body shell, and the receiving airborne equipment has the advantages that the airborne satellite communication antenna is fast to disassemble and assemble, and buffering protection is conducted on the airborne satellite communication antenna when the airborne satellite communication antenna is subjected to impact force during landing; the problems that in the prior art, an airborne satellite communication antenna is fixed to the top of a helicopter body through screws and a mounting frame, due to the fact that the helicopter body is high and the number of the screws is large, the airborne satellite communication antenna is inconvenient to disassemble and assemble, the descending rate of the helicopter is increased in the final stage of landing of the helicopter, and therefore certain impact force is generated, and the reliability of the helicopter is affected are solved. And as electronic components in the airborne satellite communication antenna are relatively precise, the impact force generated by landing may cause damage to the electronic components in the airborne satellite communication antenna.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite communication, and in particular to a receiving airborne device based on satellite communication. Background Art

[0002] An airborne satellite communication antenna is a device used to implement satellite communications on aircraft (such as helicopters). It can provide services such as long-distance data transmission, voice communication, and Internet access, ensuring that the aircraft maintains communication connection with the ground or other remote locations during flight.

[0003] In the prior art, the airborne satellite communication antenna is fixed to the top of the helicopter fuselage by screws and a mounting bracket. Since the fuselage is high and the number of screws is large, it is inconvenient to disassemble and assemble the airborne satellite communication antenna. In addition, in the final stage of landing of the helicopter, the pilot will gradually reduce the thrust of the rotor, which will increase the descent rate of the helicopter and generate a certain impact force. Since the electronic components inside the airborne satellite communication antenna are relatively sophisticated, the impact force generated by the landing may cause damage to the electronic components inside the airborne satellite communication antenna. Therefore, a receiving airborne device based on satellite communication is proposed to solve the above problems. Summary of the invention

[0004] 1. Technical issues to be solved

[0005] In view of the deficiencies in the prior art, the present invention provides a receiving airborne device based on satellite communication, which has the advantages of quick disassembly and assembly of the airborne satellite communication antenna, and buffering and protecting the airborne satellite communication antenna when it is subjected to impact force during landing. The present invention solves the problem in the prior art that the airborne satellite communication antenna is fixed to the top of the helicopter fuselage by screws and a mounting frame, and since the fuselage is relatively high and the number of screws is large, it is inconvenient to disassemble and assemble the airborne satellite communication antenna. In the final stage of landing of the helicopter, the pilot will gradually reduce the thrust of the rotor, which will cause the helicopter's descent rate to increase, thereby generating a certain impact force. Since the electronic components inside the airborne satellite communication antenna are relatively sophisticated, the impact force generated by the landing may cause damage to the electronic components inside the airborne satellite communication antenna.

[0006] (II) Technical solution

[0007] The technical solution of the present invention to solve the above technical problems is as follows: a receiving airborne device based on satellite communication, comprising a fuselage shell and a satellite communication antenna, the top of the fuselage shell is embedded with a columnar shell extending to the top thereof, the interior of the columnar shell is provided with buffer components distributed in an annular array, the outer side of the buffer component is provided with a movable circular plate located inside the columnar shell, the top of the movable circular plate is fixedly connected with a socket extending to the top of the columnar shell, the interior of the socket is provided with a self-locking component extending to the front side thereof, the bottom of the self-locking component is provided with driving rods distributed in an annular array, the inner cavity top wall of the socket is fixedly connected with support rods distributed in an annular array and adapted to the driving rods, the driving rod and the outer side of the corresponding support rod are both hinged with the same limiting component;

[0008] An inserting seat adapted to the socket is fixedly connected to the bottom of the satellite communication antenna, and limiting grooves distributed in a circular array and adapted to the limiting assembly are opened on the outer side of the inserting seat.

[0009] The beneficial effects of the present invention are:

[0010] 1) The receiving airborne device based on satellite communication can complete the installation of the satellite communication antenna by inserting the insertion seat at the bottom of the satellite communication antenna into the socket, rotating the self-locking component and then driving the driving rod to rotate, thereby driving the limit component to move so that it enters the limit groove outside the insertion seat. When the satellite communication antenna needs to be removed, the self-locking component is rotated in the opposite direction, and then the limit component is driven to reset through the driving rod, and then the limit component is separated from the limit groove, thereby releasing the limit on the insertion seat, and the satellite communication antenna can be removed, which has the advantage of quick disassembly and assembly of the airborne satellite communication antenna.

[0011] 2) For the satellite communication-based receiving airborne equipment, in the final stage of helicopter landing, the pilot will gradually reduce the thrust of the rotor, which will increase the helicopter's descent rate and generate a certain impact force. The impact force is transmitted to the device through the fuselage, causing the movable circular plate to swing up and down on the outside of the buffer component. During this process, the buffer component absorbs the impact force through elastic deformation, and then the swing of the movable circular plate gradually becomes stable, which has the advantage of buffering and protecting the airborne satellite communication antenna when it is subjected to impact force during landing.

[0012] Based on the above technical solution, the present invention can also be improved as follows.

[0013] Furthermore, the buffer assembly includes a sliding rod, a first spring and a second spring. The interior of the cylindrical shell is fixedly connected with sliding rods distributed in a circular array. The outer side of the sliding rod is slidably connected with the same movable circular plate located inside the cylindrical shell. The outer side of the sliding rod is sleeved with a first spring located between the bottom wall of the inner cavity of the cylindrical shell and the bottom of the movable circular plate. The outer side of the sliding rod is sleeved with a second spring located between the top wall of the inner cavity of the cylindrical shell and the top of the movable circular plate.

[0014] The beneficial effect of adopting the above-mentioned further scheme is that in the final stage of helicopter landing, the pilot will gradually reduce the thrust of the rotor, which will cause the helicopter's descent rate to increase, thereby generating a certain impact force. The impact force is transmitted to the device through the fuselage, causing the movable circular plate to swing up and down on the outside of the slide rod. During this process, the first spring and the second spring absorb the impact force through elastic deformation, and then the swing of the movable circular plate gradually becomes stable, thereby achieving buffering protection for the onboard satellite communication antenna when it is subjected to impact force during landing.

[0015] Further, the self-locking assembly includes a worm wheel and a bolt head worm, the socket is internally rotatably connected to the worm wheel, the socket is internally rotatably connected to the bolt head worm extending to the front side thereof and meshing with the worm wheel, and the bottom of the worm wheel is fixedly connected to driving rods distributed in a ring array;

[0016] Furthermore, the limiting assembly includes an arc-shaped connecting rod and a limiting plate. The outer side of the driving rod is hinged with an arc-shaped connecting rod, and the end of the arc-shaped connecting rod away from the driving rod is hinged with a limiting plate. The limiting plate is hinged with the corresponding support rod and adapted to the limiting groove.

[0017] The beneficial effect of adopting the above-mentioned further scheme is that the insertion seat at the bottom of the satellite communication antenna is inserted into the socket, and the bolt head worm is rotated. Since the bolt head worm is meshed with the worm wheel, the drive rod is driven to rotate, thereby driving the limit plate to rotate around the support rod to the opposite side through the arc connecting rod until the limit plates enter the limit groove on the outside of the insertion seat, so that the limit plate limits the insertion seat, and the installation of the satellite communication antenna is completed. When the satellite communication antenna needs to be removed, the bolt head worm is rotated in the opposite direction, and then the drive rod is driven to rotate in the opposite direction through the worm wheel, thereby driving the limit plate to rotate around the support rod to the opposite side through the arc connecting rod, so that the limit plate is separated from the limit groove, thereby releasing the limit on the insertion seat, and the satellite communication antenna can be removed, so as to achieve the effect of quick disassembly and assembly of the airborne satellite communication antenna.

[0018] Furthermore, the bottom of the insertion seat is provided with spherical protrusions distributed at four corners;

[0019] Furthermore, the bottom wall of the inner cavity of the socket is provided with positioning grooves distributed at four corners and adapted to the spherical protrusion, and the positioning grooves are adapted to the limiting grooves.

[0020] The beneficial effect of adopting the above further solution is that when the insertion seat at the bottom of the satellite communication antenna is inserted into the socket, the spherical protrusion and the positioning groove cooperate to facilitate the alignment of the limiting piece and the limiting groove. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a schematic diagram of the appearance structure of the present invention;

[0022] Figure 2 It is a cross-sectional view of the columnar housing structure of the present invention;

[0023] Figure 3 This is a bottom view of the limiting structure of the insert seat by the limiting assembly of the present invention;

[0024] Figure 4 It is a bottom view of the limiting assembly and the insert seat releasing limiting structure of the present invention;

[0025] Figure 5 This is an enlarged schematic diagram of the structure at a of the present invention;

[0026] Figure 6 It is an enlarged schematic diagram of the structure at point b of the present invention.

[0027] In the figure: 1. body shell; 2. satellite communication antenna; 3. cylindrical shell; 4. buffer assembly; 401. slide rod; 402. first spring; 403. second spring; 5. movable circular plate; 6. socket; 7. self-locking assembly; 701. worm gear; 702. bolt head worm; 8. driving rod; 9. support rod; 10. limit assembly; 101. arc connecting rod; 102. limit plate; 11. insertion seat; 12. limit groove; 13. spherical protrusion; 14. positioning groove. DETAILED DESCRIPTION

[0028] 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 described embodiments 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 creative work are within the scope of protection of the present invention.

[0029] Embodiment 1, by Figure 1-6A receiving airborne device based on satellite communication is provided. The present invention comprises a fuselage shell 1 and a satellite communication antenna 2. A columnar shell 3 extending to the top of the fuselage shell 1 is embedded on the top of the fuselage shell 1. A buffer assembly 4 distributed in an annular array is provided inside the columnar shell 3. The outer side of the buffer assembly 4 is provided with a movable circular plate 5 located inside the columnar shell 3. A socket 6 extending to the top of the columnar shell 3 is fixedly connected to the top of the movable circular plate 5. A self-locking assembly 7 extending to the front side of the socket 6 is provided inside the socket 6. A driving rod 8 distributed in an annular array is provided at the bottom of the self-locking assembly 7. A support rod 9 distributed in an annular array and adapted to the driving rod 8 is fixedly connected to the top wall of the inner cavity of the socket 6. The driving rod 8 and the outer side of the corresponding support rod 9 are both hinged with the same limiting assembly 10.

[0030] The bottom of the satellite communication antenna 2 is fixedly connected with an insertion seat 11 adapted to the socket 6, and the outer side of the insertion seat 11 is provided with a limiting groove 12 distributed in a circular array and adapted to the limiting component 10;

[0031] The self-locking assembly 7 includes a worm wheel 701 and a bolt head worm 702. The worm wheel 701 is rotatably connected inside the socket 6. The bolt head worm 702 extending to the front side of the socket 6 and meshing with the worm wheel 701 is rotatably connected inside the socket 6. The bottom of the worm wheel 701 is fixedly connected to the driving rods 8 distributed in a ring array.

[0032] The limiting assembly 10 includes an arc-shaped connecting rod 101 and a limiting plate 102. The outer side of the driving rod 8 is hinged with an arc-shaped connecting rod 101. The end of the arc-shaped connecting rod 101 away from the driving rod 8 is hinged with a limiting plate 102. The limiting plate 102 is hinged with the corresponding support rod 9 and is adapted to the limiting groove 12.

[0033] The insertion seat 11 at the bottom of the satellite communication antenna 2 is inserted into the socket 6, and the bolt head worm 702 is rotated. Since the bolt head worm 702 is meshed with the worm wheel 701, the driving rod 8 is driven to rotate, thereby driving the limiting piece 102 to rotate around the support rod 9 to the opposite side thereof through the arc connecting rod 101, until the limiting piece 102 enters the limiting groove 12 outside the insertion seat 11, so that the limiting piece 102 limits the insertion seat 11, and the installation of the satellite communication antenna 2 can be completed. When the satellite communication antenna 2 needs to be removed, the bolt head worm 702 is rotated in the opposite direction, and then the driving rod 8 is driven to rotate in the opposite direction through the worm wheel 701, thereby driving the limiting piece 102 to rotate around the support rod 9 to the opposite side thereof through the arc connecting rod 101, so that the limiting piece 102 is separated from the limiting groove 12, thereby releasing the limit on the insertion seat 11, and the satellite communication antenna 2 can be removed, so as to achieve the effect of quick disassembly and assembly of the airborne satellite communication antenna 2;

[0034] The bottom of the insertion seat 11 is provided with spherical protrusions 13 distributed in four corners;

[0035] The inner cavity bottom wall of the socket 6 is provided with positioning grooves 14 distributed at four corners and adapted to the spherical protrusion 13, and the positioning grooves 14 are adapted to the limiting grooves 12;

[0036] The insertion seat 11 at the bottom of the satellite communication antenna 2 is inserted into the socket 6 , and the spherical protrusion 13 cooperates with the positioning groove 14 , so that the limiting piece 102 and the limiting groove 12 are aligned.

[0037] Embodiment 2, on the basis of embodiment 1, the buffer assembly 4 comprises a slide bar 401, a first spring 402 and a second spring 403, the interior of the cylindrical shell 3 is fixedly connected with the slide bars 401 distributed in a ring array, the outer side of the slide bars 401 is slidably connected with the same movable circular plate 5 located inside the cylindrical shell 3, the outer side of the slide bars 401 is sleeved with the first spring 402 located between the bottom wall of the inner cavity of the cylindrical shell 3 and the bottom of the movable circular plate 5, and the outer side of the slide bars 401 is sleeved with the second spring 403 located between the top wall of the inner cavity of the cylindrical shell 3 and the top of the movable circular plate 5;

[0038] In the final stage of helicopter landing, the pilot will gradually reduce the thrust of the rotor, which will increase the helicopter's descent rate and generate a certain impact force. The impact force is transmitted to the device through the fuselage, causing the movable circular plate 5 to swing up and down on the outside of the slide bar 401. During this process, the first spring 402 and the second spring 403 absorb the impact force through elastic deformation, and then the swing of the movable circular plate 5 gradually becomes stable, so that the onboard satellite communication antenna 2 can be buffered and protected when the landing is subject to impact force.

[0039] Working principle:

[0040] The first step to implement the innovation point:

[0041] Step 1: Insert the insertion seat 11 at the bottom of the satellite communication antenna 2 into the socket 6, and make the spherical protrusion 13 enter the positioning groove 14, and then align the limiting piece 102 with the limiting groove 12;

[0042] Step 2: Rotate the bolt head worm 702. Since the bolt head worm 702 is meshed with the worm wheel 701, the driving rod 8 is driven to rotate, thereby driving the limiting piece 102 to rotate around the support rod 9 to the opposite side thereof through the arc connecting rod 101, until the limiting piece 102 enters the limiting groove 12 outside the insertion seat 11, so that the limiting piece 102 limits the insertion seat 11, and the installation of the satellite communication antenna 2 is completed;

[0043] Step 3: When the satellite communication antenna 2 needs to be removed, the bolt head worm 702 is rotated in the opposite direction, and then the driving rod 8 is driven to rotate in the opposite direction through the worm wheel 701, thereby driving the limiting plate 102 to rotate around the support rod 9 to the opposite side thereof through the arc connecting rod 101, so that the limiting plate 102 is separated from the limiting groove 12, thereby releasing the limit on the insertion seat 11 and removing the satellite communication antenna 2.

[0044] The second innovation point implementation steps:

[0045] Step 1: In the final stage of helicopter landing, the pilot will gradually reduce the thrust of the rotor, which will increase the helicopter's descent rate, thereby generating a certain impact force, which is transmitted to the device through the fuselage;

[0046] Step 2: The impact force causes the movable circular plate 5 to swing up and down on the outside of the sliding rod 401. During this process, the first spring 402 and the second spring 403 absorb the impact force through elastic deformation;

[0047] Step 3: The impact force is gradually weakened under the action of the first spring 402 and the second spring 403, so that the shaking of the movable circular plate 5 gradually tends to be stable, so that the airborne satellite communication antenna 2 can be buffered and protected when it is impacted during landing.

[0048] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the existence of other identical elements in the process, method, article or device including the elements.

[0049] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A satellite communication based receiving airborne device, comprising a body shell (1) and a satellite communication antenna (2), characterized in that: The top of the fuselage shell (1) is embedded with a columnar shell (3) extending above it, and the interior of the columnar shell (3) is provided with a buffer assembly (4) distributed in an annular array, and the outer side of the buffer assembly (4) is provided with a movable circular plate (5) located inside the columnar shell (3), and the top of the movable circular plate (5) is fixedly connected with a socket (6) extending above the columnar shell (3), and the interior of the socket (6) is provided with a self-locking assembly (7) extending to the front side thereof, and the bottom of the self-locking assembly (7) is provided with a driving rod (8) distributed in an annular array, and the inner cavity top wall of the socket (6) is fixedly connected with a support rod (9) distributed in an annular array and adapted to the driving rod (8), and the outer sides of the driving rod (8) and the corresponding support rod (9) are both hinged with a same limit assembly (10); The bottom of the satellite communication antenna (2) is fixedly connected to an insertion seat (11) adapted to the socket (6), and the outer side of the insertion seat (11) is provided with limiting grooves (12) distributed in a ring array and adapted to the limiting assembly (10).

2. The satellite communication-based receiving airborne device according to claim 1, characterized in that: The buffer assembly (4) comprises a slide bar (401), a first spring (402) and a second spring (403); the interior of the cylindrical shell (3) is fixedly connected with the slide bars (401) distributed in a ring array; the outer side of the slide bars (401) is slidably connected with the same movable circular plate (5) located inside the cylindrical shell (3); the outer side of the slide bars (401) is sleeved with the first spring (402) located between the bottom wall of the inner cavity of the cylindrical shell (3) and the bottom of the movable circular plate (5); the outer side of the slide bars (401) is sleeved with the second spring (403) located between the top wall of the inner cavity of the cylindrical shell (3) and the top of the movable circular plate (5).

3. The satellite communication-based receiving airborne device according to claim 1, characterized in that: The self-locking assembly (7) comprises a worm wheel (701) and a bolt head worm (702); the socket (6) is internally rotatably connected to the worm wheel (701); the socket (6) is internally rotatably connected to the bolt head worm (702) extending to the front side thereof and meshing with the worm wheel (701); the bottom of the worm wheel (701) is fixedly connected to drive rods (8) distributed in a ring array.

4. The satellite communication-based receiving airborne device according to claim 1, characterized in that: The limiting assembly (10) comprises an arc-shaped connecting rod (101) and a limiting plate (102); the outer side of the driving rod (8) is hinged with an arc-shaped connecting rod (101); one end of the arc-shaped connecting rod (101) away from the driving rod (8) is hinged with a limiting plate (102); the limiting plate (102) is hinged with the corresponding supporting rod (9) and is adapted to the limiting groove (12).

5. The satellite communication-based receiving airborne device according to claim 1, characterized in that: The bottom of the insertion seat (11) is provided with spherical protrusions (13) distributed at four corners.

6. A satellite communication based receiving airborne device according to claim 1 or 5, characterized in that: The inner cavity bottom wall of the socket (6) is provided with positioning grooves (14) distributed at four corners and adapted to the spherical protrusion (13), and the positioning grooves (14) are adapted to the limiting grooves (12).

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