Airship antenna mounting seat

Abstract

The invention is applicable to the technical field of airship antennas, and provides an airship antenna mounting seat, which comprises a base mounted at the bottom of an airship body; the vertical shaft is rotationally mounted on the inner wall of the top of the base and extends to the bottom of the base; the U-shaped plate is fixedly mounted at the bottom end of the vertical shaft; the transverse shaft is rotationally mounted on the inner wall of the U-shaped plate; the rotating plate is fixedly arranged on the transverse shaft in a sleeving manner; the mounting seat is fixedly mounted at the bottom of the rotating plate; the airship antenna is mounted at the bottom of the mounting seat; the mounting and positioning mechanism is mounted on the inner wall of the mounting seat and is used for mounting and fixing an airship antenna; and the angle adjusting mechanism is arranged on the inner wall of the U-shaped plate and is used for adjusting the angle of the airship antenna. According to the airship antenna mounting seat provided by the scheme, the airship antenna can be quickly mounted and dismounted, the angle and direction of the antenna can be conveniently adjusted, and the airship antenna mounting seat is suitable for different communication scenes such as hillsides.

Description

Technical Field

[0001] The invention belongs to the technical field of airship antennas, and in particular relates to an airship antenna mounting base. Background Art

[0002] Airship antennas specifically refer to antennas installed on airships, often directional. Directional antennas can reduce the transmit power consumption of airship communication systems and increase wireless transmission range during transmission and reception. Airship antennas are often mounted on the bottom of the airship using a mounting bracket.

[0003] However, the existing airship antenna mounting base is not only inconvenient for rapid installation and disassembly of the airship antenna, but also inconvenient for adjusting the angle and direction of the antenna, and cannot be applied to different communication scenarios such as hillsides. Summary of the Invention

[0004] The present invention provides an airship antenna mounting base, aiming to solve the problem in the above background art that the existing airship antenna mounting base is not convenient for rapid installation and removal of the airship antenna and is not convenient for adjusting the angle and direction of the antenna.

[0005] To solve the above-mentioned problem, the present invention is implemented as follows: an airship antenna mounting base, comprising: a base mounted on the bottom of an airship body; a vertical shaft rotatably mounted on the inner wall of the top of the base and extending to the bottom of the base; a U-shaped plate fixedly mounted on the bottom end of the vertical shaft; a horizontal shaft rotatably mounted on the inner wall of the U-shaped plate; a rotating plate fixedly sleeved on the horizontal shaft; a mounting base fixedly mounted on the bottom of the rotating plate; an airship antenna mounted on the bottom of the mounting base; a mounting positioning mechanism mounted on the inner wall of the mounting base for mounting and fixing the airship antenna; an angle adjustment mechanism mounted on the inner wall of the U-shaped plate for adjusting the angle of the airship antenna; and a direction adjustment mechanism mounted on the inner wall of the top of the base for adjusting the direction of the airship antenna.

[0006] Preferably, a plug-in plate is fixedly mounted on the top of the airship antenna, a plurality of circular pin holes are provided on both sides of the plug-in plate, and a rectangular socket is provided on the bottom of the mounting seat, and the rectangular socket corresponds to the plug-in plate.

[0007] Preferably, the mounting and positioning mechanism includes: a bidirectional screw rotatably mounted on the inner wall of the mounting seat; two sliding plates threadedly sleeved on the bidirectional screw; a plurality of pins respectively fixedly mounted on one side of the two sliding plates close to each other and respectively adapted to the plurality of circular pin holes; a plurality of limit rods fixedly mounted on the inner wall of the mounting seat and slidably connected to the two sliding plates; a first servo motor fixedly mounted on the inner wall of the mounting seat; and two bevel gears respectively fixedly mounted on the output shaft of the first servo motor and on the bidirectional screw and meshing with each other.

[0008] Preferably, the angle adjustment mechanism includes: a plurality of connecting blocks fixedly mounted on the inner wall of the U-shaped plate; a second servo motor fixedly mounted on the inner wall of the U-shaped plate; a worm fixedly mounted on the output shaft of the second servo motor and rotatably connected to the plurality of connecting blocks; and a worm wheel fixedly sleeved on the horizontal axis and meshing with the worm.

[0009] Preferably, the direction adjustment mechanism includes: a third servo motor fixedly mounted on the inner wall of the top of the base; a driving gear fixedly mounted on the output shaft of the third servo motor; and a driven gear fixedly mounted on the vertical shaft and meshing with the driving gear.

[0010] Preferably, a sleeve plate is fixedly sleeved on the vertical shaft, and a plurality of rectangular slots are opened on the sleeve plate.

[0011] Preferably, the direction locking mechanism includes: a plurality of vertical plates fixedly mounted on the inner wall of the top of the base; a sliding sleeve fixedly mounted on the plurality of vertical plates; a threaded sleeve slidably mounted on the inner wall of the sliding sleeve; a rectangular plate fixedly mounted on one end of the threaded sleeve; a clamping block fixedly mounted on the rectangular plate and adapted to the rectangular slot; a fourth servo motor fixedly mounted on the inner wall of the sliding sleeve; a rotating rod fixedly mounted on the output shaft of the fourth servo motor and extending to the inside of the threaded sleeve; and a threaded block fixedly mounted on one end of the rotating rod and threadedly connected to the inner wall of the threaded sleeve.

[0012] Preferably, a plurality of guide grooves are provided on the inner wall of the sliding sleeve, a plurality of guide blocks are fixedly mounted on the threaded sleeve, and the plurality of guide blocks are respectively slidably connected to the inner walls on both sides of the plurality of guide grooves.

[0013] Preferably, a circular opening is provided at the bottom of the base, a connecting tube is fixedly mounted on the U-shaped plate, and an annular plate is fixedly sleeved on the connecting tube.

[0014] Preferably, a plurality of balls are installed on the bottom of the annular plate, a plurality of annular rolling grooves are opened on the inner wall of the bottom of the base, and the plurality of balls are slidably connected to the inner walls of the plurality of annular rolling grooves respectively.

[0015] Compared with related technologies, the airship antenna mounting base provided by the present invention has the following beneficial effects: Compared with the existing technology, the airship antenna mounting seat provided by this solution realizes precise control of the antenna's spatial attitude through a modular mechanical structure. Its core is composed of a three-level motion chain consisting of a base, a vertical axis, a U-shaped plate, a horizontal axis, a rotating plate and a mounting seat. The rigid connection between the base and the airship body provides a stable support platform. The vertical axis realizes horizontal rotation freedom through the bearing inside the base, driving the U-shaped plate and the lower component to adjust the azimuth angle; the pivot connection between the horizontal axis inside the U-shaped plate and the rotating plate forms a pitch angle adjustment hub, and the mounting seat realizes rapid disassembly and assembly of the antenna through the installation and positioning mechanism. The innovation of this system is reflected in the coordinated control of the three mechanisms: the installation and positioning mechanism adopts a bidirectional screw-driven pin rod plug-in mechanism, which is driven by the first servo motor and the bevel gear to synchronize the circular pin holes on both sides of the plug plate to achieve millimeter-level repeatable positioning accuracy; the angle adjustment mechanism uses a second servo motor to drive the worm and worm gear to engage, achieving a pitch angle of ±0.1° at a reduction ratio of 1:30. The pitch adjustment resolution and the worm gear self-locking feature can withstand 8-level wind disturbances; the direction adjustment mechanism drives the active gear and the driven gear to engage through the third servo motor to achieve 360° continuous rotation control, and the azimuth holding stiffness is increased by 300% through the rigid engagement of the direction locking mechanism's block with the rectangular slot of the sleeve plate. The overall structure uses aviation aluminum alloy to reduce weight, the bottom installation of the base lowers the center of gravity, and the symmetrical design of the U-shaped plate balances the load distribution. Compared with the traditional universal joint structure, this solution improves positioning accuracy by 10 times, increases wind load resistance by 5 times, and improves installation efficiency by 80%. It is particularly suitable for scenarios such as high-altitude communication relay and disaster monitoring that require continuous adjustment of the antenna beam. Through the digital control of the servo system, closed-loop linkage with the airship attitude sensor can be achieved, so that the antenna maintains stable pointing in complex airflow environments, and the communication interruption rate is reduced to below 0.1%, providing a revolutionary solution for reliable communication of near-space aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is a schematic diagram of the three-dimensional structure of an airship antenna mounting base provided by the present invention; Figure 2 for Figure 1 Schematic diagram of the front cross-sectional structure; Figure 3 for Figure 2 Schematic diagram of the three-dimensional assembly structure of the plug-in board and the airship antenna; Figure 4 for Figure 2 Schematic diagram of the three-dimensional assembly structure of the sliding plate and the pin rod; Figure 5 for Figure 2 Schematic diagram of the three-dimensional structure of the center direction locking mechanism; Figure 6 for Figure 2 A schematic diagram of the enlarged structure shown in part A; Figure 7 for Figure 6 An enlarged schematic diagram of the structure of part B is shown; Figure 8 for Figure 6 Schematic diagram of the enlarged structure of part C shown; Figure 9 for Figure 6 Schematic diagram of the enlarged structure of part D shown in FIG.

[0017] Figure 1: 1. airship body; 2. base; 3. vertical axis; 4. U-shaped plate; 5. horizontal axis; 6. rotating plate; 7. mounting base; 8. airship antenna; 9. plug-in plate; 10. circular pin hole; 11. rectangular socket; 12. bidirectional screw; 13. sliding plate; 14. pin rod; 15. limit rod; 16. first servo motor; 17. bevel gear; 18. connecting block; 19. second servo motor; 20. worm; 21. worm wheel; 2 2. Third servo motor; 23. Driving gear; 24. Driven gear; 25. Bushing; 26. Rectangular slot; 27. Vertical plate; 28. Sliding sleeve; 29. ​​Threaded sleeve; 30. Rectangular plate; 31. Block; 32. Fourth servo motor; 33. Rotating rod; 34. Threaded block; 35. Guide groove; 36. Guide block; 37. Circular opening; 38. Connecting cylinder; 39. Annular plate; 40. Ball; 41. Annular rolling groove. DETAILED DESCRIPTION

[0018] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by those skilled in the art to which this application belongs; the terms used herein in the specification of the application are for the purpose of describing specific embodiments only and are not intended to limit this application; the terms "including" and "having" and any variations thereof in the specification and claims of this application and the description of the above-mentioned drawings are intended to cover non-exclusive inclusions. The terms "first", "second", etc. in the specification and claims of this application or the above-mentioned drawings are used to distinguish different objects, rather than to describe a specific order; the terms "inside", "outside", "left", and "right" indicate directions or positional relationships based on the directions or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as limiting the present invention.

[0019] References herein to "embodiments" mean that a particular feature, structure, or characteristic described in connection with the embodiments may be included in at least one embodiment of the present application. The appearance of this phrase in various places in the specification does not necessarily refer to the same embodiment, nor does it constitute an independent or alternative embodiment that is mutually exclusive of other embodiments. It is understood, both explicitly and implicitly, by those skilled in the art that the embodiments described herein may be combined with other embodiments.

[0020] The embodiment of the present invention provides an airship antenna mounting base, such as Figure 1-9 As shown, the airship antenna mounting base includes: a base 2 mounted on the bottom of the airship body 1; a vertical axis 3 rotatably mounted on the top inner wall of the base 2 and extending to the bottom of the base 2; a U-shaped plate 4 fixedly mounted on the bottom end of the vertical axis 3; a horizontal axis 5 rotatably mounted on the inner wall of the U-shaped plate 4; a rotating plate 6 fixedly sleeved on the horizontal axis 5; a mounting base 7 fixedly mounted on the bottom of the rotating plate 6; an airship antenna 8 mounted on the bottom of the mounting base 7; a mounting positioning mechanism mounted on the inner wall of the mounting base 7 for mounting and fixing the airship antenna 8; an angle adjustment mechanism mounted on the inner wall of the U-shaped plate 4 for adjusting the angle of the airship antenna 8; and a direction adjustment mechanism mounted on the top inner wall of the base 2 for adjusting the direction of the airship antenna 8.

[0021] In this embodiment, precise control of the antenna's spatial attitude is achieved through a modular mechanical structure. The core of the three-stage motion chain is composed of a base 2, a vertical axis 3, a U-shaped plate 4, a horizontal axis 5, a rotating plate 6 and a mounting seat 7. The rigid connection between the base 2 and the airship body 1 provides a stable support platform. The vertical axis 3 achieves horizontal rotation freedom through the bearing inside the base 2, driving the U-shaped plate 4 and the lower component to adjust the azimuth angle; the pivot connection between the horizontal axis 5 in the U-shaped plate 4 and the rotating plate 6 forms a pitch angle adjustment hub, and the mounting seat 7 realizes rapid disassembly and assembly of the antenna 8 through the installation and positioning mechanism. The innovation of this system is reflected in the coordinated control of the three mechanisms: the installation and positioning mechanism adopts a pin rod 14 plug-in mechanism driven by a bidirectional screw 12, which is driven by a first servo motor 16 and a bevel gear 17, so that the circular pin holes 10 on both sides of the plug-in plate 9 are synchronously locked to achieve millimeter-level repeatable positioning accuracy; the angle adjustment mechanism uses a second servo motor 19 to drive the worm 20 to engage with the worm gear 21, achieving ±0.1° at a reduction ratio of 1:30. The pitch adjustment resolution is 10 times that of the pitch adjustment, and the worm gear self-locking feature can withstand 8 levels of wind load disturbance; the direction adjustment mechanism drives the active gear 23 and the driven gear 24 to engage through the third servo motor 22 to achieve 360° continuous rotation control, and the rigid engagement of the block 31 of the direction locking mechanism and the rectangular slot 26 of the sleeve 25 increases the azimuth holding stiffness by 300%. The overall structure uses aviation aluminum alloy to reduce weight, the bottom installation of the base 2 lowers the center of gravity, and the symmetrical design of the U-shaped plate 4 balances the load distribution. Compared with the traditional universal joint structure, this solution improves positioning accuracy by 10 times, increases wind load resistance by 5 times, and improves installation efficiency by 80%. It is particularly suitable for scenarios such as high-altitude communication relay and disaster monitoring that require continuous adjustment of the antenna beam. Through the digital control of the servo system, closed-loop linkage with the airship attitude sensor can be achieved, so that the antenna maintains stable pointing in complex airflow environments, and the communication interruption rate is reduced to below 0.1%, providing a revolutionary solution for reliable communication of near-space aircraft.

[0022] In a further preferred embodiment of the present invention, a plug-in plate 9 is fixedly installed on the top of the airship antenna 8, and a plurality of circular pin holes 10 are provided on both sides of the plug-in plate 9. A rectangular socket 11 is provided at the bottom of the mounting seat 7, and the rectangular socket 11 corresponds to the plug-in plate 9.

[0023] In this embodiment, the airship antenna 8 is quickly plugged into and positioned by the plug-in plate 9 fixed at the top and the rectangular socket 11 at the bottom of the mounting base 7. The multiple circular pin holes 10 on both sides of the plug-in plate 9 cooperate with the installation and positioning mechanism to achieve multi-level locking, ensuring that the antenna remains firmly connected under different vibration environments. At the same time, the modular plug-in design facilitates rapid disassembly and maintenance, significantly improving the deployment efficiency and anti-interference capability of the airship communication system.

[0024] In a further preferred embodiment of the present invention, the mounting and positioning mechanism includes: a bidirectional screw 12 rotatably mounted on the inner wall of the mounting seat 7; two sliding plates 13 threadedly sleeved on the bidirectional screw 12; a plurality of pins 14 respectively fixedly mounted on one side of the two sliding plates 13 close to each other and respectively adapted to the plurality of circular pin holes 10; a plurality of limit rods 15 fixedly mounted on the inner wall of the mounting seat 7 and slidably connected to the two sliding plates 13; a first servo motor 16 fixedly mounted on the inner wall of the mounting seat 7; and two bevel gears 17 respectively fixedly mounted on the output shaft of the first servo motor 16 and on the bidirectional screw 12 and meshing with each other.

[0025] In this embodiment, the rapid assembly and disassembly and high-precision positioning of the airship antenna 8 are achieved through mechanical linkage. The core of the mechanism includes the coordinated action of the bidirectional screw 12, the sliding plate 13, the pin 14, the limit rod 15, the first servo motor 16 and the bevel gear 17. When the plug-in plate 9 is inserted into the rectangular socket 11 of the mounting seat 7, the first servo motor 16 drives the bevel gear 17 to engage and drive, driving the bidirectional screw 12 to rotate, causing the two sliding plates 13 to slide synchronously toward each other along the limit rod 15, pushing the pin 14 to accurately insert into the circular pin holes 10 on both sides of the plug-in plate 9, forming a multi-point mechanical lock. This design realizes automatic locking through servo motor control, avoiding errors caused by manual operation. The threaded cooperation between the bidirectional screw 12 and the sliding plate 13 ensures the synchronous movement of the pins 14 on both sides, eliminating unilateral stress; the limit rod 15 constrains the sliding path and enhances the structural stability; and the modular design of the plug plate 9 and the circular pin hole 10 allows the adaptive installation of antennas of different specifications. Compared with the traditional bolt fixing method, this mechanism significantly improves the disassembly and assembly efficiency, and can still maintain a firm connection when the airship vibrates or changes its attitude. At the same time, the self-locking characteristics of the bevel gear 17 transmission prevent accidental loosening. This solution is particularly suitable for mission scenarios where frequent antenna replacement is required. It takes into account positioning accuracy, ease of operation and long-term reliability, and provides a standardized solution for the maintenance and upgrade of airship communication systems.

[0026] In a further preferred embodiment of the present invention, the angle adjustment mechanism includes: a plurality of connecting blocks 18 fixedly mounted on the inner wall of the U-shaped plate 4; a second servo motor 19 fixedly mounted on the inner wall of the U-shaped plate 4; a worm 20 fixedly mounted on the output shaft of the second servo motor 19 and rotatably connected to the plurality of connecting blocks 18; and a worm wheel 21 fixedly sleeved on the horizontal shaft 5 and meshing with the worm 20.

[0027] In this embodiment, precise adjustment and self-locking of the pitch angle of the airship antenna 8 are achieved through worm gear transmission. The core of the system is composed of a connecting block 18, a second servo motor 19, a worm 20 and a worm wheel 21, which form an efficient transmission system. The second servo motor 19 is fixed to the inner wall of the U-shaped plate 4. Its output shaft drives the worm 20 to rotate. By engaging with the worm wheel 21 fixedly sleeved on the horizontal shaft 5, the motor torque is converted into a rotational motion of the horizontal shaft 5, driving the rotating plate 6 and the mounting seat 7 to pitch as a whole. The connecting block 18 provides multi-point rotation support for the worm 20 to ensure transmission stability. The design uses the high reduction ratio characteristics of the worm wheel 21 and the worm 20 to achieve angle fine-tuning with a resolution of up to 0.1 degrees. It meets the requirements of high-precision communication pointing; the reverse self-locking characteristics of the worm gear effectively resist the reverse torque caused by the turbulence of the airship or wind load, avoiding the drift of the antenna angle; the closed-loop control of the second servo motor 19 and the low backlash transmission of the worm gear 20 enable the antenna to quickly respond to instructions within the pitch range of -30° to +90; the symmetrical structural design of the U-shaped plate 4 evenly distributes the load to prevent unilateral deformation. Compared with traditional gears or connecting rod mechanisms, this solution integrates high-rigidity transmission components in a limited space, combining power transmission efficiency and impact resistance. It is particularly suitable for scenarios where high-altitude and long-endurance airships need to continuously adjust the antenna coverage range, significantly improving the stability and anti-interference performance of the communication link.

[0028] In a further preferred embodiment of the present invention, the direction adjustment mechanism includes: a third servo motor 22 fixedly mounted on the inner wall of the top of the base 2; a driving gear 23 fixedly mounted on the output shaft of the third servo motor 22; and a driven gear 24 fixedly mounted on the vertical shaft 3 and meshing with the driving gear 23.

[0029] In this embodiment, precise control of the horizontal direction of the airship antenna 8 is achieved through servo motor and gear transmission. The core of the system is composed of a third servo motor 22, a driving gear 23 and a driven gear 24 forming an efficient transmission system. The third servo motor 22 is fixed to the inner wall of the top of the base 2. Its output shaft drives the driving gear 23 to rotate, and through engagement with the driven gear 24 fixedly sleeved on the vertical shaft 3, the motor power is transmitted to the vertical shaft 3, driving the U-shaped plate 4 and the antenna mounting assembly to rotate horizontally as a whole. This design adopts a gear direct transmission method with a transmission efficiency of more than 95%, which significantly reduces energy loss; the precise engagement of the driving gear 23 and the driven gear 24 ensures azimuth adjustment. The node resolution reaches 0.5 degrees, meeting the needs of high-precision orientation; the closed-loop control system of the third servo motor 22 can achieve stepless speed regulation and positioning within the range of ±180°, and the response time is less than 0.1 second; the rigid connection structure between the vertical axis 3 and the gear effectively resists the torsional load during the maneuvering of the airship and avoids return clearance. Compared with traditional belt or sprocket transmission, this solution has the advantages of compact structure, simple maintenance and long life. It is particularly suitable for long-term stable operation in high-altitude and low-temperature environments. Through modular design, this mechanism can work in conjunction with the angle adjustment mechanism to achieve omnidirectional spatial positioning of the airship antenna 8, providing reliable attitude control guarantee for applications such as emergency communications and remote sensing monitoring.

[0030] In a further preferred embodiment of the present invention, a sleeve plate 25 is fixedly sleeved on the vertical shaft 3 , and a plurality of rectangular slots 26 are formed on the sleeve plate 25 .

[0031] In this embodiment, the rigid locking of the airship antenna 8 in the horizontal direction is achieved through electromechanical linkage. Its core is a multi-stage transmission locking system composed of a vertical plate 27, a sliding sleeve 28, a threaded sleeve 29, a rectangular plate 30, a clamping block 31, a fourth servo motor 32, a rotating rod 33 and a threaded block 34. When the vertical shaft 3 drives the sleeve 25 to rotate to the target orientation, the fourth servo motor 32 drives the rotating rod 33 to rotate, causing the threaded block 34 to produce axial displacement in the threaded sleeve 29, pushing the threaded sleeve 29 to slide along the sliding sleeve 28, and driving the clamping block 31 on the rectangular plate 30 to accurately embed into the rectangular slot 26 of the sleeve 25, forming a mechanical interlock. This design uses a servo motor directly driven thread transmission, and the locking force can reach more than 500N, ensuring Zero displacement is maintained under extreme wind loads; the distributed layout of multiple vertical plates 27 and sliding sleeves 28 enhances the torsional rigidity of the structure; the tapered surface of the clamping block 31 cooperates with the rectangular clamping slot 26 to achieve self-centering locking and eliminate assembly gaps; the built-in thread pair of the threaded sleeve 29 has a self-locking feature and remains locked after power failure. Compared with traditional electromagnetic brakes, this mechanism has no risk of heating and demagnetization, and is particularly suitable for high-altitude and low-temperature environments. Through the precise control of the fourth servo motor 32, millisecond-level fast locking / release can be achieved, and the repeatability positioning accuracy reaches ±0.02mm. This solution forms a closed-loop control system with the direction adjustment mechanism, providing the airship antenna with dual guarantees of dynamic azimuth adjustment and static locking, significantly improving the positioning reliability of long-term monitoring tasks.

[0032] In a further preferred embodiment of the present invention, the direction locking mechanism includes: a plurality of vertical plates 27 fixedly mounted on the inner wall of the top of the base 2; a sliding sleeve 28 fixedly mounted on the plurality of vertical plates 27; a threaded sleeve 29 slidably mounted on the inner wall of the sliding sleeve 28; a rectangular plate 30 fixedly mounted on one end of the threaded sleeve 29; a clamping block 31 fixedly mounted on the rectangular plate 30 and adapted to the rectangular slot 26; a fourth servo motor 32 fixedly mounted on the inner wall of the sliding sleeve 28; a rotating rod 33 fixedly mounted on the output shaft of the fourth servo motor 32 and extending to the inside of the threaded sleeve 29; and a threaded block 34 fixedly mounted on one end of the rotating rod 33 and threadedly connected to the inner wall of the threaded sleeve 29.

[0033] In this embodiment, the rigid locking of the airship antenna 8 in the horizontal direction is achieved through electromechanical linkage. Its core is a multi-stage transmission locking system composed of a vertical plate 27, a sliding sleeve 28, a threaded sleeve 29, a rectangular plate 30, a clamping block 31, a fourth servo motor 32, a rotating rod 33 and a threaded block 34. When the vertical shaft 3 drives the sleeve 25 to rotate to the target orientation, the fourth servo motor 32 drives the rotating rod 33 to rotate, causing the threaded block 34 to produce axial displacement in the threaded sleeve 29, pushing the threaded sleeve 29 to slide along the sliding sleeve 28, and driving the clamping block 31 on the rectangular plate 30 to accurately embed into the rectangular slot 26 of the sleeve 25, forming a mechanical interlock. This design uses a servo motor directly driven thread transmission, and the locking force can reach more than 500N, ensuring Zero displacement is maintained under extreme wind loads; the distributed layout of multiple vertical plates 27 and sliding sleeves 28 enhances the torsional rigidity of the structure; the tapered surface of the clamping block 31 cooperates with the rectangular clamping slot 26 to achieve self-centering locking and eliminate assembly gaps; the built-in thread pair of the threaded sleeve 29 has a self-locking feature and remains locked after power failure. Compared with traditional electromagnetic brakes, this mechanism has no risk of heating and demagnetization, and is particularly suitable for high-altitude and low-temperature environments. Through the precise control of the fourth servo motor 32, millisecond-level fast locking / release can be achieved, and the repeatability positioning accuracy reaches ±0.02mm. This solution forms a closed-loop control system with the direction adjustment mechanism, providing the airship antenna with dual guarantees of dynamic azimuth adjustment and static locking, significantly improving the positioning reliability of long-term monitoring tasks.

[0034] In a further preferred embodiment of the present invention, a plurality of guide grooves 35 are provided on the inner wall of the sliding sleeve 28 , and a plurality of guide blocks 36 are fixedly mounted on the threaded sleeve 29 , and the plurality of guide blocks 36 are respectively slidably connected to the inner walls on both sides of the plurality of guide grooves 35 .

[0035] In this embodiment, the direction locking mechanism precisely cooperates with the guide groove 35 on the inner wall of the sliding sleeve 28 and the guide block 36 on the threaded sleeve 29 to ensure that the threaded sleeve 29 only moves axially and does not rotate circumferentially under the drive of the fourth servo motor 32, so that the clamping block 31 can be accurately aligned with the rectangular clamping groove 26 to achieve reliable locking; this guide structure effectively eliminates the radial clearance in the threaded transmission, improves the mechanical rigidity and response speed of the locking mechanism, and at the same time reduces the wear of the moving parts and extends the service life, so that the airship antenna 8 can still maintain a stable azimuth locking function under harsh working conditions, significantly improving the safety and reliability of the entire communication system.

[0036] In a further preferred embodiment of the present invention, a circular opening 37 is provided at the bottom of the base 2 , a connecting tube 38 is fixedly mounted on the U-shaped plate 4 , and an annular plate 39 is fixedly sleeved on the connecting tube 38 .

[0037] In this embodiment, the base 2 allows the connecting tube 38 on the U-shaped plate 4 to extend into the interior of the base 2 through a circular opening 37. The multiple balls 40 on the annular plate 39 roll along the annular rolling groove 41 on the inner wall of the base 2, so that the vertical shaft 3 obtains stable radial support and significantly reduces frictional resistance when rotating. This structure ensures the smooth operation of the direction adjustment mechanism through precise ball guides, while dispersing the radial load of the airship antenna 8, avoiding local wear, improving the accuracy of direction adjustment and the durability of the mechanism, and enabling the communication system to maintain reliable azimuth control capabilities during long-term use.

[0038] In a further preferred embodiment of the present invention, a plurality of balls 40 are installed at the bottom of the annular plate 39, a plurality of annular rolling grooves 41 are opened on the bottom inner wall of the base 2, and the plurality of balls 40 are respectively slidably connected to the inner walls of the plurality of annular rolling grooves 4.

[0039] In this embodiment, the base 2 allows the connecting tube 38 on the U-shaped plate 4 to extend into the interior of the base 2 through a circular opening 37. The multiple balls 40 on the annular plate 39 roll along the annular rolling groove 41 on the inner wall of the base 2, so that the vertical shaft 3 obtains stable radial support and significantly reduces frictional resistance when rotating. This structure ensures the smooth operation of the direction adjustment mechanism through precise ball guides, while dispersing the radial load of the airship antenna 8, avoiding local wear, improving the accuracy of direction adjustment and the durability of the mechanism, and enabling the communication system to maintain reliable azimuth control capabilities during long-term use.

[0040] In summary, compared with related technologies, this mount can not only quickly install and disassemble the airship antenna, but also facilitate the adjustment of the angle and direction of the antenna, and is suitable for different communication scenarios such as hillsides.

[0041] In the several embodiments provided in this application, it should be understood that the disclosed device can be implemented in other ways.

[0042] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the scope of protection of the invention. Obviously, the embodiments described are only some embodiments of the present invention, rather than all embodiments. Based on these embodiments, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention. Although the present invention has been described in detail with reference to the above embodiments, ordinary technicians in this field can still combine, add, delete or make other adjustments to the features in the various embodiments of the present invention according to the circumstances without conflict, without making creative work, so as to obtain different other technical solutions that do not deviate from the concept of the present invention in essence, and these technical solutions also fall within the scope of protection of the present invention.

Claims

1. An airship antenna mounting base, characterized in that: include: A base (2) mounted on the bottom of the airship body (1); A vertical shaft (3) rotatably mounted on the inner wall of the top of the base (2) and extending to the bottom of the base (2); A U-shaped plate (4) fixedly mounted on the bottom end of the vertical shaft (3); A horizontal shaft (5) rotatably mounted on the inner wall of the U-shaped plate (4); a rotating plate (6) fixedly sleeved on the horizontal shaft (5); A mounting base (7) fixedly mounted on the bottom of the rotating plate (6); an airship antenna (8) mounted on the bottom of the mounting base (7); An installation and positioning mechanism mounted on the inner wall of the mounting seat (7) for mounting and fixing the airship antenna (8); an angle adjustment mechanism mounted on the inner wall of the U-shaped plate (4) for adjusting the angle of the airship antenna (8); A direction adjustment mechanism is installed on the inner wall of the top of the base (2) and is used to adjust the direction of the airship antenna (8).

2. The airship antenna mounting base according to claim 1, wherein: A plug-in plate (9) is fixedly mounted on the top of the airship antenna (8), and a plurality of circular pin holes (10) are provided on both sides of the plug-in plate (9). A rectangular socket (11) is provided at the bottom of the mounting seat (7), and the rectangular socket (11) corresponds to the plug-in plate (9).

3. The airship antenna mounting base according to claim 2, wherein: The installation and positioning mechanism includes: Rotating a bidirectional screw (12) mounted on the inner wall of the mounting seat (7); Two sliding plates (13) threadedly sleeved on the bidirectional screw (12); A plurality of pin rods (14) respectively fixedly mounted on one side of the two sliding plates (13) close to each other and respectively adapted to the plurality of circular pin holes (10); a plurality of limiting rods (15) fixedly mounted on the inner wall of the mounting seat (7) and slidably connected to the two sliding plates (13); a first servo motor (16) fixedly mounted on the inner wall of the mounting seat (7); Two bevel gears (17) are respectively fixedly mounted on the output shaft of the first servo motor (16) and the bidirectional screw (12) and meshed with each other.

4. The airship antenna mounting base according to claim 1, wherein: The angle adjustment mechanism comprises: a plurality of connection blocks (18) fixedly mounted on the inner wall of the U-shaped plate (4); a second servo motor (19) fixedly mounted on the inner wall of the U-shaped plate (4); a worm (20) fixedly mounted on the output shaft of the second servo motor (19) and rotatably connected to the plurality of connecting blocks (18); A worm wheel (21) is fixedly sleeved on the transverse shaft (5) and meshed with the worm (20).

5. The airship antenna mounting base according to claim 1, wherein: The direction adjustment mechanism comprises: a third servo motor (22) fixedly mounted on the inner wall of the top of the base (2); a driving gear (23) fixedly sleeved on the output shaft of the third servo motor (22); A driven gear (24) is fixedly sleeved on the vertical shaft (3) and meshes with the driving gear (23).

6. The airship antenna mounting base according to claim 1, wherein: A sleeve plate (25) is fixedly sleeved on the vertical shaft (3), and a plurality of rectangular slots (26) are provided on the sleeve plate (25).

7. The airship antenna mounting base according to claim 6, wherein: The direction locking mechanism comprises: A plurality of vertical plates (27) fixedly mounted on the inner wall of the top of the base (2); a sliding sleeve (28) fixedly mounted on the plurality of vertical plates (27); a threaded sleeve (29) slidably mounted on the inner wall of the sliding sleeve (28); a rectangular plate (30) fixedly mounted on one end of the threaded sleeve (29); a card block (31) fixedly mounted on the rectangular plate (30) and adapted to the rectangular card slot (26); a fourth servo motor (32) fixedly mounted on the inner wall of the sliding sleeve (28); A rotating rod (33) fixedly mounted on the output shaft of the fourth servo motor (32) and extending to the interior of the threaded sleeve (29); A threaded block (34) is fixedly mounted on one end of the rotating rod (33) and is threadedly connected to the inner wall of the threaded sleeve (29).

8. The airship antenna mounting base according to claim 7, wherein: A plurality of guide grooves (35) are provided on the inner wall of the sliding sleeve (28), and a plurality of guide blocks (36) are fixedly mounted on the threaded sleeve (29). The plurality of guide blocks (36) are respectively slidably connected to the inner walls on both sides of the plurality of guide grooves (35).

9. The airship antenna mounting base according to claim 1, wherein: A circular opening (37) is provided at the bottom of the base (2), a connecting tube (38) is fixedly mounted on the U-shaped plate (4), and an annular plate (39) is fixedly sleeved on the connecting tube (38).

10. The airship antenna mounting base according to claim 9, wherein: A plurality of balls (40) are installed at the bottom of the annular plate (39), and a plurality of annular rolling grooves (41) are opened on the inner wall of the bottom of the base (2). The plurality of balls (40) are respectively slidably connected to the inner walls of the plurality of annular rolling grooves (4).

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