TWM648832U - Composite mechanism type Starlink satellite receiving antenna - Google Patents

Abstract

This new model relates to a composite mechanism starlink satellite receiving antenna, which includes a horizontal axis adjustment device on a base; a set of dish antennas, which are reversely symmetrically installed on the left and right sides of the horizontal axis adjustment device. They are driven by a first arm and a second arm respectively; a Starlink satellite orbit adjustment device can drive the first arm and the second arm to cross and swing in opposite directions on a support, so that the left and right dish antennas can Handover tracking of Starlink satellites; and an elevation adjustment device and a set of polarization adjustment devices can simultaneously adjust the elevation angle and polarization direction of the dish antenna, thereby utilizing two dish antennas on a single receiving device Cross-swing in opposite directions to form a "composite mechanism" receiving antenna that can be quickly switched to a new target satellite, which can replace the two independent antennas currently used in traditional small satellite ground terminal equipment (Very Small Aperture Terminal, VSAT), and The "phased array" electronic antenna of the Starlink system has improved efficiency with reduced cost and low failure rate.

Description

Composite mechanism starlink satellite receiving antenna

The present invention relates to a Starlink satellite receiving antenna, especially a single composite mechanism receiving antenna, which can replace the traditional Very Small Aperture Terminal (VSAT) using two independent antennas and the phase of the Starlink system. Controlled array electronic antenna device.

With the advancement of low earth orbit (LEO) satellite technology, the use of low earth orbit satellites to provide communication services has become more and more widespread. However, low-orbit satellites (LEO) are different from traditional artificial satellites. Most artificial satellites are synchronous satellites and work in GSO (Geosynchronous Orbit). This is because the rotation angular velocity of satellites in this orbit is synchronous with the earth, so it is called synchronous track. In synchronous orbit, the satellite is stationary relative to the earth, so it is relatively easy to adjust the ephemeris and align the ground communication stations. The disadvantage is that the distance is long and the power required for communication is high. Therefore, a heavy-duty antenna with large transmitting and receiving power and volume is required. equipment.

、虛線

所示)，當第二顆衛星S2快到A點時，於是第二接收天線80b就先回到a點追蹤第二顆衛星S2(如圖中實線

所示)，又當第二顆衛星S2來到b點位置時，除了第二接收天線80b繼續追蹤外(如圖中實虛線

所示)，第接收天線80a此時也回到B點位置(如圖中實虛線

所示)，依此類推，二個接收天線80a、80b不斷的換手。是以，INTELLIAN的VSAT必須使用二個獨立的接收天線80a、80b，因此不僅成本增加，且二個獨立的接收天線不斷換手在操作上較複雜，為其缺失。此類型專利另揭露於US20210399416A1、US20190157765A1等專利案中。 Figure 1A shows a conventional low-orbit satellite receiving antenna 80 disclosed by INTELLIAN TECHNOLGIES, Inc., which belongs to a Very Small Aperture Terminal (VSAT). This type of patent is disclosed in US 2021/ 0066778A1 patent, the receiving antenna 80 includes an elevation angle (Elevation angle) adjustment device 81, an oblique angle (Oblique angle) adjustment device 82, and an azimuth angle (Azimuth angle) adjustment device 83; as shown in Figure 1B, since the low-orbit satellite is in orbit The operation speed is very fast. Therefore, the User Equipment (UE) on the surface needs to frequently change hands to a new target satellite (target satellite). That is to say, at least two receiving antennas 80a and 80a are required. 80b, when the first receiving antenna 80a and the second receiving antenna 80b track the first satellite S1 counterclockwise from point B to point c (solid line in the figure)

, dashed line

as shown), when the second satellite S2 is approaching point A, the second receiving antenna 80b first returns to point a to track the second satellite S2 (solid line in the figure)

as shown), and when the second satellite S2 comes to the position of point b, in addition to the second receiving antenna 80b continuing to track (the solid dotted line in the figure

as shown), the receiving antenna 80a also returns to the position of point B at this time (the solid and dotted line in the figure

shown), and so on, the two receiving antennas 80a and 80b constantly change hands. Therefore, INTELLIAN's VSAT must use two independent receiving antennas 80a and 80b. Therefore, not only the cost increases, but also the operational complexity of two independent receiving antennas constantly changing hands is a disadvantage. This type of patent is also disclosed in patent cases such as US20210399416A1 and US20190157765A1.

In addition, among low-orbit satellite related technologies, the antenna 90 used by SpaceX's Starlink system is shown in Figure 2. When the Starlink user-end antenna communicates, it does not connect to a single satellite, but is aligned. Therefore, the entire satellite flight track must be realized using a phased array antenna board 91 instead of the traditional directional satellite antenna 80 as shown in Figure 1. This is because the phased array antenna board 91 supports beam shaping. shape, making it easier to target satellites as they glide across the sky. The phased array antenna board 91 has a motor device 92 on the back. In addition, the Starlink antenna 90 also includes a power supply 93 and a router 94 .

Phased array technology uses multiple antenna units to control the radiation pattern or beam by changing the relative phase of each unit, and uses microwave transmission lines and power divider systems to connect the antenna units. In the phased array antenna 90 design, interference or "beamforming" between two or more radiated signals is used to control the direction of the transmit beam. The antenna board 91 implements beamforming by adjusting the phase difference between the drive signals sent to each transmitter in the array. SpaceX's U.S. Patent Publication No. 20180241122 discloses the working mechanism of some phased array antennas. The antenna has a motor and has automatic mechanical adjustment capabilities. It should be noted that this motor adjustment only has the mechanical adjustment capability in one direction. It is basically certain that this motor adjustment is only used to adjust the pitch angle. The terminal can automatically adjust the pitch angle according to its longitude and latitude geographical location, and adopts phase control. The array realizes automatic tracking of sent and received signals.

According to Wei Cha, the antenna used by the Starlink system for star finding and tracking usually uses an electronically scanned array radar (electronically scanned array). However, the cost of using an electronically scanned array radar is very high, and the failure rate is also high. Therefore, how to reduce antenna costs and failure rates has become an urgent problem to be solved.

The company has decades of experience in manufacturing synchronous satellite receiving antennas, so it is actively researching and developing how to use traditional satellite receiving antennas to solve the above problems of Starlink system antennas.

The main purpose of this new model is to provide a composite mechanism Starlink satellite receiving antenna, which uses two dish antennas on a single receiving device to cross and swing in opposite directions to form a "composite" that can be quickly switched to a new target satellite. The "mechanical" receiving antenna can replace the two independent antennas currently used in traditional small satellite ground terminal equipment (Very Small Aperture Terminal, VSAT) and the "phased array" electronic antenna of the Starlink system, reducing costs and failure rates. Low efficiency is improved.

In order to achieve the above purpose, the technical means used in this new model include: a base with an upright central axis; a horizontal axis adjustment device located on the base, including: a slewing base with a bottom connected A first pulley is installed on the central shaft; a first motor is installed on the slewing base, and its rotating shaft drives the first pulley through a first transmission belt, and then the slewing base can be connected to the first pulley. The central axis rotates clockwise or counterclockwise; a Starlink satellite orbit adjustment device is located above the slewing seat, including: an upright frame, with a vertical frame on the front and rear ends of the upright frame. A first shaft seat and a second shaft seat can be respectively provided with a first rotating shaft and a second rotating shaft, and a bearing seat is connected longitudinally between the first rotating shaft and the second rotating shaft, and the longitudinal length of the bearing seat is greater than Its lateral width enables the bearing to swing left and right with the rotation of the second rotating shaft; furthermore, a transverse shaft is provided in the middle of the bearing, and the left and right ends of the transverse shaft extend through the bearing. The left and right ends of the transverse axis are respectively connected to a second pulley and a third pulley; a set of dish antennas is composed of a first dish antenna and a second dish antenna , symmetrically arranged on the left and right sides of the support in the opposite direction, and are driven by a first arm and a second arm respectively, and the first arm and the second arm are respectively connected and fixed on On the second pulley and the third pulley, the second pulley and the third pulley are driven by a second motor and a third motor respectively with a second transmission belt and a third transmission belt, so that they are connected and fixed respectively. The first arm and the second arm on the second pulley and the third pulley can rotate on the left and right ends of the transverse axis, thereby driving the first dish antenna and the second dish antenna on the bearing. It swings crosswise in opposite directions forward and backward to track the Starlink satellites in low orbit with a handover; an elevation adjustment device is provided on the upright frame and includes: a fourth motor and a fourth pulley. Located on the second rotating shaft, the fourth motor drives the fourth pulley through a fourth transmission belt, and then drives the bearing to swing left and right with the first and second rotating shafts as the center to adjust the third rotating shaft. the elevation angles of a dish antenna and a second dish antenna; and a set of polarization adjustment devices, consisting of a first polarization adjustment device and a second polarization adjustment device, respectively located on the first arm and the third arm Above the two arms, the first polarization adjustment device includes: a support base, which is a hollow body and the inner end is fixed on the upper end of the first arm; a fifth motor is located at the bottom of the support base, which rotates The shaft extends into the support base and drives a fifth pulley through a fifth transmission belt. The fifth pulley can rotate on an axis, and its upper end protrudes above the support base, thereby linking the first disc. type antenna deflection; and the second polarization adjustment device has the same structure as the first polarization adjustment device to drive the second polarization adjustment device. The dish antenna is deflected; thereby, it is combined into a composite mechanism Starlink satellite receiving antenna, which can control the first dish antenna and the second dish antenna to track the Starlink satellite orbit by changing hands, and can simultaneously adjust the horizontal axis, elevation angle and Polarization direction to receive signals from Starlink satellites.

According to the front-facing feature, the second motor and the third motor are respectively provided on the first arm and the second arm.

According to the front-opening feature, the fourth motor is located on the second shaft seat.

According to the aforementioned characteristics, an antenna control device is further included, which includes: a receiver, a controller and a memory. The controller can be used to process the data received by the receiver and the data stored in the memory, and then The control signals used to control the mechanical Starlink satellite receiving antenna can be generated to control the rotation of the first motor, the second motor, the third motor, the fourth motor, and the fifth motor respectively to control the rotation of the mechanical Starlink satellite receiving antenna. Elevation angle, Oblique angle, Azimuth angle and polarization position.

According to the aforementioned characteristics, the first dish antenna and the second dish antenna include: rectangular, circular or elliptical.

In this way, this new type uses a mechanical structure to form a composite Starlink satellite receiving antenna that can be quickly switched to a new target satellite, replacing the two independent satellite ground terminal equipment (Very Small Aperture Terminal, VSAT) currently used. Antennas and phased array electronic antennas used in Starlink systems can reduce costs and failure rates, thereby increasing the popularity and stability of Starlink satellite antennas.

10: Base

11:Central axis

20: Horizontal axis adjustment device

21:Revolving seat

22:First pulley

23:First motor

24:Rotation axis

25:First drive belt

30: Dish antenna

30a: The first dish antenna

30b: Second dish antenna

300a: The first rectangular dish antenna

300b: Second rectangular dish antenna

31a: first arm

31b:Second arm

32a, 32b: Waveguide

33a: Electronic equipment

40: Starlink satellite orbit adjustment device

41:upright stand

42:First axis seat

43:Second axis seat

421:First axis

431:Second axis

44:Bearing

441:Transverse axis

45:Second pulley

451: Second motor

452:Second drive belt

46:Third pulley

461:Third motor

462:Third drive belt

50: Elevation angle adjustment device

51:Fourth motor

52:Fourth pulley

521:Fourth drive belt

60:Polarization adjustment device

60A: First polarization adjustment device

60B: Second polarization adjustment device

61: Support base

62:Fifth motor

621:Rotation axis

63:Fifth drive belt

64:Fifth pulley

641:Upper end

65:Axis

70A: Composite mechanism Starlink satellite receiving antenna

70B: Rectangular composite mechanism Starlink satellite receiving antenna

A: Horizontal axis

B: Starlink satellite orbit

C: Elevation angle

D:Polarization

Figure 1A is a three-dimensional view of the structure of a conventional low-orbit satellite receiving antenna.

Figure 1B is a reference diagram of the usage status of a conventional low-orbit satellite receiving antenna.

Figure 2 is a schematic diagram of the antenna used in the conventional Starlink system.

Figure 3 is an appearance perspective view of a preferred embodiment of the present invention.

Figure 4 is an enlarged perspective view of the main structure in Figure 3.

Figure 5 is a perspective view of the main structure of the new elevation adjustment device.

Figure 6A is a side view of a preferred embodiment of the present invention, which shows that the first dish antenna is aligned with the Starlink satellite orbit B.

Figure 6B is a side view of a preferred embodiment of the present invention, which shows that the second dish antenna is aligned with the Starlink satellite orbit B by changing hands.

Figure 6C is a side view of the new horizontal axis adjustment device.

Figure 7A is a top view of a preferred embodiment of the present invention, showing that the dish antenna can be adjusted along the horizontal axis A.

Figure 7B is a top view of a preferred embodiment of the present invention, showing that the dish antenna is adjusted counterclockwise by an angle (θ) .

Figure 8A is a cross-sectional view showing the new polarization adjustment device of the present invention.

Figure 8B is a top view showing the new polarization adjustment device of the present invention.

Figure 9 is an appearance perspective view of another possible embodiment of the present invention.

Figure 10 is a control schematic diagram of the new antenna control device.

The following description takes the accompanying drawings as embodiments, but is not limited thereto. The present invention can also be implemented in other embodiments, and well-known steps or components are not described in detail to avoid unnecessary limitations on the present invention. . Please note that the drawings are for schematic purposes only and do not represent the actual size or quantity of components. Some details may not be fully drawn for the sake of simplicity.

First, please refer to Figures 3 to 10. A preferred and feasible embodiment of the new "composite mechanism starlink satellite receiving antenna" 70A includes: a base 10 with an upright central axis 11 ( As shown in Figure 6C, Z axis); a horizontal axis adjustment device 20 is located on the base 10, please cooperate with Figure 4 and Figure 6C at the same time, including: a swivel base 21, the bottom of which is connected to a first pulley 22 , and is disposed on the central axis 11; a first motor 23 is disposed on the slewing base 21, and its rotating shaft 24 drives the first pulley 22 through a first transmission belt 25, thereby linking the slewing base 21 It can rotate clockwise or counterclockwise on the central axis 11; the "transmission belt" or "pulley" described in the foregoing or following embodiments can be composed of a "chain" or "sprocket", and can also be implemented, which will not be described in detail. . In this embodiment, the rotary base 21 is in the shape of a rectangular plate, but it is not limited to this. It is rotatably installed on the central axis 11 and is driven by the first motor 23 to rotate, so that the rotary base 21 The dish antenna 30 on the top can be adjusted on the horizontal axis (indicated by A in the figure), which can also be said to adjust the azimuth angle (θ) of the composite starlink satellite receiving antenna 70A, as shown in Figure 7A 7 Figure B reveals that this is the first necessary means of this new type.

As shown in Figures 3 to 5, a Starlink satellite orbit adjustment device 40 is located above the slewing base 21 and includes: an upright frame 41. , is provided with a first shaft seat 42 and a second shaft seat 43, on which a first rotating shaft 421 and a second rotating shaft 431 can be respectively arranged, and a bearing is connected longitudinally between the first rotating shaft 421 and the second rotating shaft 431. The longitudinal length (Y-axis direction) of the bearing seat 44 is greater than its transverse width (X-axis direction), so that the bearing seat 44 can swing left and right along with the rotation of the second rotating shaft 431; in this embodiment , the bearing 44 is a "U"-shaped body, but is not limited to this. The bearing 44 is provided with a transverse shaft 441 (X-axis direction) in the middle. The left and right ends of the transverse shaft 441 extend out of the bearing 44 and are fixed on the bearing 44, and are respectively connected to a second pulley 45 and a second pulley 45. A third pulley 46 becomes the central axis of the second pulley 45 and the third pulley 46 , that is to say, the second pulley 45 and the third pulley 46 can rotate on both ends of the transverse axis 441 .

A set of dish antennas 30 is composed of a first dish antenna 30a and a second dish antenna 30b, which are symmetrically arranged on the left and right sides of the support 44 in opposite directions. They are respectively composed of a first arm 31a and a second arm 31b, and the first arm 31a and the second arm 31b are respectively connected and fixed on the second pulley 45 and the third pulley 46, and the second pulley 45 and the third pulley 46 are respectively driven by A second motor 451 and a third motor 461 are driven by a second transmission belt 452 and a third transmission belt 462 to connect the first arm 31a fixed on the second pulley 45 and the third pulley 46 respectively. and the second arm 31b can rotate on the left and right ends of the transverse axis 441, thereby driving the first dish antenna 30a and the second dish antenna 30b to cross on the support 44 in opposite directions. Swing for handover tracking of Starlink satellites in low orbit; in this embodiment, the second motor 451 and the third motor 461 are respectively provided on the first arm 31a and the second arm 31b. Furthermore, , the first dish antenna 30a and the second dish antenna 30b can be circular, but are not limited to this; they can also be as shown in Figure 9, the dish antenna 30 includes: a first rectangular antenna 300a, a third It is composed of two dish antennas 300b, or other elliptical shapes can be implemented. In addition, the first dish antenna 30a and the second dish antenna 30b, or the first rectangular dish antenna 300a and the second rectangular dish antenna 300b further include waveguides 32a, 32b and other receiving elements. Electronic equipment 33a for Starlink satellite signals; for example: feeders, low noise amplifiers (LNA) or downconverters, etc. However, these electronic equipment 33a are prior art (Prior Art) and are not the subject of the patent of this model and will not be described in detail. .

As shown in Figure 5, an elevation adjustment device 50 is provided on the upright frame 41 and includes: a fourth motor 51 and a fourth pulley 52, which are provided on the second rotating shaft 431. The fourth motor 51 passes through A fourth transmission belt 521 drives the fourth pulley 52, thereby driving the bearing 44 to swing left and right with the first and second rotating shafts 421, 431 as the center to adjust the first dish antenna 30a and the second rotating shaft 431. Elevation angle C of the two-dish antenna 30b. In this embodiment, the fourth motor 51 is installed on the second shaft seat 43 .

In this embodiment, the second motor 451 and the third motor 461 are used to drive the second pulley 45 and the third pulley 46, thereby driving the first dish antenna 30a and the second dish antenna 30b on the transverse axis 441. The left and right sides swing crosswise in opposite directions for handover tracking of Starlink satellites in low orbit, as shown in Figures 6A and 6B; Figure 6A shows the first dish antenna 30a (Z1 axis) alignment star For satellites in the Starlink satellite orbit B, FIG. 6B shows that the second dish antenna 30b (Z2 axis) is aligned with the satellite in the Starlink satellite orbit B. In this way, the directivities of the first dish antenna 30a and the second dish antenna 30b driven by the first arm 31a and the second arm 31b continuously cross between the Z1-Z2 axes, and the star can be aligned. This is the second necessary means of this new type of tracking of satellites in chain satellite orbits (referred to as B in the figure).

Furthermore, as shown in Figure 5, when the support 44 is driven by the fourth motor 51 and the fourth pulley 52 to swing left and right, the first dish antenna 30a and a second dish antenna on it 30b, can still be driven by the second motor 451 and the third motor 461 to operate smoothly, and does not affect the operation of the Starlink satellite orbit adjustment device 40 at all. The "elevation angle adjustment" C here can also be said to be the left and right tilt angle adjustment. , for example: adjust to left (L) tilt angle or adjust to right (R) tilt angle. Furthermore, the Starlink satellite orbit adjustment device 40 and the elevation angle adjustment device 50 are cleverly combined on the slewing base 21, making the overall space configuration and operation very smooth. This is the third necessary means of the present invention.

As shown in Figure 5, Figure 8A and Figure 8B, a set of polarization adjustment devices 60 is composed of a first polarization adjustment device 60A (left) and a second polarization adjustment device 60B (right), which are respectively provided. Above the first arm 31a and the second arm 31b, the first polarization adjustment device 60A includes: a support base 61, which is a hollow body and the inner end is fixed to the upper end of the first arm 31a; a fifth fifth The motor 62 is located at the bottom of the support base 61, and its rotating shaft 621 extends into the support base 61, and drives a fifth pulley 64 through a fifth transmission belt 63. The fifth pulley 64 can be mounted on an axis 65 Rotate, and its upper end 641 protrudes above the support base 61, thereby causing the first dish antenna 30a to deflect (as indicated by D). In addition, the second polarization adjustment device 60B is located above the second arm 31b. It has the same structure as the first polarization adjustment device 60A and is used to drive the second dish antenna 30b to deflect, so its structure will not be described again. . The so-called "polarization of the antenna" refers to the direction of the electric field intensity formed when the antenna radiates. Since directional antennas have the maximum radiation or reception direction and have relatively strong anti-interference ability, they need to be optimally adjusted; as for the principle of antenna polarization: There is no need to go into details about the previous technology. The polarization adjustment device 60 of the present invention can adjust the polarization directions of the first dish antenna 30a and the second dish antenna 30b (referring to D in Figures 3, 8A and 8B ) . This is the feature of the present invention. The fourth necessary means.

This new model combines the above four technical means to form a composite mechanism Starlink satellite receiving antenna 70A, which can control the first dish antenna 30a and the second dish antenna 30b to track the Starlink satellite orbit by changing hands, and can simultaneously Adjust the horizontal axis, elevation angle and polarization direction to quickly and accurately receive Starlink satellite signals. Of course, as shown in Figure 9, a rectangular composite mechanism starlink satellite receiving antenna 70B composed of two first rectangular dish antennas 300a and second rectangular dish antennas 300b can also achieve the same purpose. effect.

Please refer to Figure 10 again, a control schematic diagram of the new antenna control device. The new antenna control device 100 can receive ephemeris information from satellites S1 and S2, and can control the composite mechanism satellite based on the ephemeris information. Chain satellite receiving antenna 70A. The ephemeris information may include information such as the azimuth angle and elevation angle of satellites S1 and S2. In addition, although the antenna control device 100 is shown separately from the composite mechanism Starlink satellite receiving antenna 70A, the antenna control device 100 can also be embodied in the antenna 70A as needed.

In this embodiment, the antenna control device 100 may include a receiver 101 and a controller 102. The receiver 101 may receive ephemeris information of satellites S1 and S2, and may also include a memory 103. The ephemeris information may be stored in the memory 103 in advance. . The ephemeris information may include information about the orbits on which the satellites S1 and S2 move hour by hour, and the receiver 101 may output the received ephemeris information to the controller 102 . In addition, the receiver 101 can store the received ephemeris information in the memory 103, and the controller 102 can include a single processor or multiple processors, and it can use the processor to process the ephemeris information, from The mechanism controls the Starlink satellite receiving antenna. However, the antenna control device 100 and the reception of ephemeris information are prior art and are not the subject of the patent of the present invention, so they will not be described in detail.

The present invention mainly uses the controller 102 to process the data received by the receiver 101 and the data stored in the memory 103, and then the controller 102 can generate a control signal for controlling the composite mechanism Starlink satellite receiving antenna 70A. . That is to say, the controller 102 can control the rotation of the first motor 23, the second motor 451, the third motor 461, the fourth motor 51, and the fifth motor 62 (there are two) respectively for the composite mechanism Starlink satellite. The elevation angle (Elevation angle), tilt angle (Oblique angle), azimuth angle (Azimuth angle), polarization position, etc. of the receiving antenna 70A. Among them, the important feature is that by controlling the forward or reverse rotation of the second motor 451 and the third motor 461, the first dish antenna 30a and the second dish antenna 30b can be synchronously controlled to exhibit an inversely symmetrical cross swing. , change hands to track satellites S1, S2... in Starlink satellite orbit B, and can adjust the horizontal axis, elevation angle and polarization direction at the same time to achieve fast and accurate reception of Starlink satellite signals.

In this way, this new type uses two dish antennas on one receiving device to cross and swing in opposite directions to form a "composite mechanism" receiving antenna that can be quickly switched to a new target satellite, and can replace traditional small satellite ground terminal equipment. (Very Small Aperture Terminal, VSAT) currently uses two independent antennas and the "phased array" electronic antenna of the Starlink system to reduce costs and failure rates, thereby popularizing and improving the stability of Starlink satellite antennas. Its efficacy is enhanced.

To sum up, the technical means disclosed in this new model indeed meet the requirements for new patents such as "novelty", "progressivity" and "available for industrial utilization". We pray that the Jun Bureau will grant patents to encourage new types and without any restrictions. Sense of morality.

However, the above disclosed drawings and descriptions are only the preferred embodiments of the present invention. Modifications or equivalent changes made by those familiar with the art in accordance with the spirit of the present case should still be included in the patent application scope of the present case.

10: Base

20: Horizontal axis adjustment device

21:Revolving seat

23:First motor

30: Dish antenna

30a: The first dish antenna

30b: Second dish antenna

31a: first arm

31b:Second arm

32a, 32b: Waveguide

33a: Electronic equipment

40: Starlink satellite orbit adjustment device

60:Polarization adjustment device

60A: First polarization adjustment device

70A: Composite mechanism Starlink satellite receiving antenna

A: Horizontal axis

B: Starlink satellite orbit

C: Elevation angle

D:Polarization

Claims (5)

A composite mechanism starlink satellite receiving antenna includes: a base, which is provided with an upright central axis; a horizontal axis adjustment device, which is located on the base and includes: a swivel base, the bottom of which is connected to a first A pulley is provided on the central shaft; a first motor is provided on the slewing base, and its rotating shaft drives the first pulley through a first transmission belt, which in turn drives the slewing base to rotate on the central shaft. The rotating base rotates clockwise or counterclockwise; a Starlink satellite orbit adjustment device is installed above the rotating base, including: an upright frame, with a first axis seat and a first axis seat longitudinally provided at the front and rear ends of the upright frame. Two shaft seats, on which a first rotating shaft and a second rotating shaft can be respectively arranged, and a bearing seat is connected longitudinally between the first rotating shaft and the second rotating shaft, and the longitudinal length of the bearing seat is greater than its transverse width, so that the first rotating shaft and the second rotating shaft are longitudinally connected. The bearing can swing left and right with the rotation of the second rotating shaft; furthermore, a transverse shaft is provided in the middle of the bearing, and the left and right ends of the transverse shaft extend out of the bearing and are fixed on the bearing. On the top, the left and right ends of the transverse axis are respectively connected to a second pulley and a third pulley; a set of dish antennas is composed of a first dish antenna and a second dish antenna, arranged in front of and behind. The direction is symmetrically arranged on the left and right sides of the support, which are driven by a first arm and a second arm respectively, and the first arm and the second arm are respectively connected and fixed on the second pulley and the third On the pulley, the second pulley and the third pulley are driven by a second motor and a third motor respectively with a second transmission belt and a third transmission belt, so that they are connected and fixed to the second pulley and the third pulley respectively. The first arm and the second arm on the pulley can rotate on the left and right ends of the transverse axis, thereby driving the first dish antenna and the second dish antenna on the bearing in opposite directions, front and back. Cross swing to track Starlink satellites in low orbit with a handover; An elevation adjustment device is provided on the upright frame and includes: a fourth motor and a fourth pulley, which are provided on the second rotating shaft. The fourth motor drives the fourth pulley through a fourth transmission belt, and then The bearing is driven to swing left and right with the first and second rotating axes as the center to adjust the elevation angles of the first dish antenna and the second dish antenna; and a set of polarization adjustment devices is provided by a first The polarization adjustment device and a second polarization adjustment device are respectively arranged above the first arm and the second arm. The first polarization adjustment device includes: a support base, which is a hollow body and has an inner end. Fixed on the upper end of the first arm; a fifth motor is located at the bottom of the support base, and its rotating shaft extends into the support base, driving a fifth pulley through a fifth transmission belt, and the fifth pulley can The second polarization adjustment device has the same structure as the first polarization adjustment device. It is used to drive the second dish antenna to deflect; thereby, it is combined into a composite mechanism Starlink satellite receiving antenna, which can control the first dish antenna and the second dish antenna to track the Starlink satellite orbit by changing hands, and can simultaneously Adjust the horizontal axis, elevation angle and polarization direction to receive signals from Starlink satellites. For the composite mechanism starlink satellite receiving antenna described in item 1 of the patent application, the second motor and the third motor are respectively provided on the first arm and the second arm. For the composite mechanism starlink satellite receiving antenna described in item 1 of the patent application, the fourth motor is located on the second axis seat. The composite mechanism starlink satellite receiving antenna described in item 1 of the patent application scope further includes an antenna control device, which includes: a receiver, a controller and a memory Memory, the controller can be used to process the data received by the receiver and the data stored in the memory, and then can generate a control signal for controlling the mechanism-type Starlink satellite receiving antenna, which can control the first motor and the second motor respectively. The motor, the third motor, the fourth motor and the fifth motor rotate to determine the elevation angle (Elevation angle), oblique angle (Oblique angle), azimuth angle (Azimuth angle) and polarization position of the Starlink satellite receiving antenna. For example, in the composite mechanism starlink satellite receiving antenna described in item 1 of the patent application, the first dish antenna and the second dish antenna are composed of: rectangular, circular or elliptical.