CN112259952A - Special-shaped seat frame for ship-borne low-orbit satellite VSAT antenna - Google Patents
Special-shaped seat frame for ship-borne low-orbit satellite VSAT antenna Download PDFInfo
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- CN112259952A CN112259952A CN202011006260.1A CN202011006260A CN112259952A CN 112259952 A CN112259952 A CN 112259952A CN 202011006260 A CN202011006260 A CN 202011006260A CN 112259952 A CN112259952 A CN 112259952A
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/12—Supports; Mounting means
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/12—Supports; Mounting means
- H01Q1/125—Means for positioning
- H01Q1/1264—Adjusting different parts or elements of an aerial unit
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/34—Adaptation for use in or on ships, submarines, buoys or torpedoes
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q3/00—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
- H01Q3/02—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole
- H01Q3/08—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole for varying two co-ordinates of the orientation
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Abstract
The invention relates to a novel seat frame for a ship-borne low-orbit satellite VSAT antenna, which is an improved A-C-E special-shaped seat frame and shortens and develops an azimuth axis into a cross rolling beam slide rail; the rolling beam tilts upwards to form an angle of 60-80 degrees with the plane of the azimuth turntable. This seat frame includes azimuth axis, roller and every single move axle: the antenna main reflecting surface performs pitching rotation along a pitching shaft, a pitching motor combination is arranged on one side of the pitching shaft, and a navigation attitude motor and a course attitude reference unit are arranged on the other side of the pitching motor combination; two ends of the pitching rotating shaft are connected with a rolling beam, and the rolling beam is driven by a rolling motor to drive the pitching shaft and the antenna reflecting surface to roll around the rolling shaft along the sliding rail; the lower part of the transverse rolling beam sliding rail is fixedly connected with the azimuth turntable; the middle part of the azimuth turntable is provided with a radio frequency rotary joint and a signal slip ring, and the azimuth turntable is driven by an azimuth motor to drive the whole antenna to rotate around an azimuth axis in azimuth. The invention has the advantages that: the pitching motion range of the antenna electric axis is close to 180 degrees, the structure is light in weight, and the power consumption is low.
Description
Technical Field
The invention belongs to the technical field of satellite mobile tracking communication, and particularly relates to a special-shaped seat frame for a ship-borne low-orbit satellite VSAT antenna.
Background
The main strength of future satellite communication lies in low-orbit communication, and ships far away from the land must be equipped with low-orbit satellite communication terminals. The low orbit satellites at home and abroad are being arranged in a tightening mode, and ground terminals track the low orbit satellites, so that the ground terminals need key technical researches on beacon-free, transit-through, frequent switching and the like, and the terminal fast acquisition and tracking, satellite overhead environment and the like are required.
For low earth orbit communication satellites, the phenomena of low-angle satellite acquisition and tracking and satellite over-top movement relative to a shipborne antenna are inevitable.
For a turntable with an A-E biaxial structure, the influence of mutual coupling during tracking motion of an A axis and an E axis exists, the azimuth velocity tends to infinity during overhead tracking, and a top tracking blind area exists in practical use.
The method for solving the over-top tracking is four in the prior art, and an X-Y rotary table, an A-E seat frame and a third axis A-E-C seat frame or an A-C-E seat frame are used, the program is over-top, and the azimuth axis of an antenna upright column is inclined. The four schemes are basically provided aiming at an antenna which is statically installed and used on the ground, an X-Y type rotary table which can be tracked by passing through the top in an antenna of a ground station has a pitching low-angle tracking blind area, and an A-E seat frame without a low-elevation blind area has a top tracking blind area, so that the antenna can not be simply moved to a ship for use.
The currently used shipboard station antennas cannot be directly used for low-orbit satellite communication or require additional use conditions. The existing A-C-E antenna turntable suitable for ship-borne use has the maximum pitching range of-11 degrees to +120 degrees, and cannot meet the requirement of tracking a low-orbit satellite at approximately 180 degrees and the requirement of tracking the satellite when the satellite passes the top.
The antenna pedestal turntables cannot be simply integrated, the requirements of reaching the movement range and the movement speed must be met structurally, and a set of applicable control system can meet the requirements of the use environment.
The technical difficulties include: the response bandwidth and the motion range of a seat frame formed by the structural form, the driving system and the servo control are required to meet the main challenges of no beacon, fast transit, frequent switching and the like of the low-orbit satellite.
Disclosure of Invention
The invention aims to solve the problems and provides a special-shaped seat frame for a ship-borne low-earth-orbit satellite VSAT antenna, which has the advantages of simple structure, light weight, low power consumption, low cost and high reliability.
In order to achieve the purpose, the invention provides the following technical scheme:
the invention relates to a special-shaped seat frame for a ship-borne low-orbit satellite VSAT antenna, which is an improved A-C-E seat frame and shortens and develops an azimuth upright post into a cross rolling beam slide rail; the plane of the transverse rolling beam faces upwards and forms an angle of 60-80 degrees with the plane of the azimuth turntable. The seat frame comprises an antenna main reflecting surface and a pitching rotating shaft rotating around the back surface of the antenna main reflecting surface, wherein the antenna main reflecting surface performs pitching rotation along the pitching shaft, one side of the pitching shaft is provided with a pitching motor combination and a motor driver, and the other side far away from the pitching motor combination and the motor driver is provided with a heading attitude stepping motor and a heading attitude reference unit (AHRS); the two ends of the pitching rotating shaft are connected with a rolling beam, and the rolling beam is driven by a rolling motor to drive the pitching shaft and the antenna reflecting surface to make rolling motion along the sliding rail; the lower part of the transverse rolling beam sliding rail is fixedly connected with the azimuth turntable; the middle part of the azimuth turntable is provided with a rotary joint, and the azimuth turntable is driven by an azimuth motor to drive the whole antenna to rotate around an azimuth axis in azimuth. The invention has the advantages of simple structure, light weight, low power consumption, low cost and high reliability. The antenna system installed on the moving carrier (ship) not only has the characteristics of the traditional communication-in-motion antenna, but also the electric axis of the main reflecting surface can rotate at a high speed within the range of 180 degrees (slightly less than) along the pitching axis. The mounting is particularly suitable for aerial flying objects with low altitude orbits, such as low orbit communication satellites, tracked by the antenna.
Furthermore, the special-shaped seat frame is an improved A-C-E seat frame, the azimuth upright post is shortened and developed into a rolling beam slide rail, and the rolling beam slide rail is fixedly connected to the azimuth turntable.
Furthermore, the transverse rolling beam is of an arc-shaped sliding rail structure.
Furthermore, the special-shaped seat frame rotates in the directions of azimuth, roll and pitch, and under all movement postures, three axes of azimuth, pitch and roll and a polarization axis are intersected in pairs and are kept vertical.
Furthermore, the motion range of the pitch angle of the antenna electric axis above the top is 0-180 degrees (slightly smaller), and the motion range of the azimuth angle is 0-360 degrees.
Preferably, the frame of the special-shaped seat frame is made of light aluminum alloy materials.
Compared with the prior art, the invention has the beneficial effects that:
aiming at the requirements and the possibility of actual installation and use of the shipborne communication-in-motion antenna, the special-shaped seat frame analyzes the advantages and weaknesses of four modes in the prior art, integrates the principle characteristics of the four modes, and provides a variant A-C-E seat frame scheme. The structure of the device can adapt to the shipborne disturbance environment, overcomes the X shaft end blind area when the X-Y seat frame is at a low elevation angle, utilizes the characteristic of the transverse rolling shaft to replace the azimuth shaft inclination, and has the advantages of simple structure, light weight, low power consumption, low cost and high reliability on the premise of realizing the functional performance.
Drawings
In order to more clearly illustrate the technical solution of the embodiment of the present invention, the drawings needed to be used in the description of the embodiment will be briefly introduced below, it is obvious that the drawings in the following description are only for more clearly illustrating the embodiment of the present invention or the technical solution in the prior art, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic view of a conventional A-C-E mount configuration;
FIG. 2 is a schematic view of the A-C-E mount configuration of the present invention;
FIGS. 3-4 are schematic diagrams of an embodiment of an antenna system constructed using the present mount;
in the figure, 1-antenna main reflection surface, 101-antenna surface lug, 2-pitching rotating shaft, 3-feed source, 4-pitching motor, 5-motor driver, 6-circular polarizer, 7-LNB, 8-orthogonal mode coupler, 9-BUC, 10-attitude stepping motor, 11-AHRS, 12-rolling beam, 13-damping base, 14-main control unit, 15-receiver, 16-power supply module, 17-offset bridge, 18-radio frequency rotary joint and signal slip ring, 19-azimuth motor, 20-interface board, 21-rolling motor, 22-rolling drive unit, 23-azimuth drive unit, 24-azimuth shaft, 25-azimuth turntable, 26-rolling beam sliding rail and 27-rolling shaft.
Detailed Description
In order to make the technical solutions of the present invention better understood and implemented by those skilled in the art, the present invention is further described with reference to the following specific examples, which are provided for illustration only and are not intended to limit the present invention.
An antenna example system formed by a special-shaped seat frame of a ship-borne low-earth orbit satellite VSAT antenna shown in fig. 3-4 comprises an antenna main reflecting surface 1 and a pitching rotating shaft 2, wherein the back surface of the antenna main reflecting surface 1 rotates around the antenna main reflecting surface, a feed source 3 is arranged on the front surface of the antenna main reflecting surface 1, a circular polarizer 6, an OMT8, an LNB7 and a BUC9 are sequentially arranged in the middle of the pitching rotating shaft 2 from front to back, a pitching motor 4 and a motor driver 5 are arranged on one side of the pitching rotating shaft 2, and a navigation attitude stepping motor 10 and an AHRS11 are arranged on the other side of the pitching motor 4 and the; the two ends of the pitching rotating shaft 2 are connected with the rolling beams 12, rolling beam slide rails 26 are arranged below the rolling beams 12, the rolling beam slide rails 26 are fixedly connected to the direction turntable 25, and the direction turntable 25 is provided with a main control unit 14, a multimode receiver 15, a power supply module 16, a bias bridge 17, a direction motor 19, a rolling motor 21, a rolling driving unit 22 and a direction driving unit 23. The roll driving unit 22 and the azimuth driving unit 23 are arranged behind the roll motor 21, the main control unit 14 and the power module 16 are sequentially arranged on one side of the azimuth driving unit 23 away from the roll driving unit 22, the receiver 15 is arranged above the power module 16, and the offset bridge 17 is arranged behind the power module 16; the shock absorption base 13 is provided with a plurality of interface boards 20, and the shock absorption base 13 absorbs shock through springs. And a rotary joint is arranged in the middle of the azimuth turntable 25, and an azimuth motor 19 is fixedly connected to the azimuth turntable 25.
The invention relates to a structural special-shaped A-C-E seat frame.
The commonly used Ka frequency band of low earth orbit satellite communication, its parabolic aerial lobe extremely narrow, about 1 degree, must guarantee the all range, all speed movement in-process azimuth, roll, pitching three-axis move accurately, in order to make the antenna electric axis point to the target satellite tracked accurately in real time. In the structure designed by the invention, the traditional A-E, X-Y, A-C-E, A-E-C, A-X-Y seat frame advantages are combined together, and the respective weak points are avoided.
The seat frame analyzes the advantages and weaknesses of the four seat frames according to the requirements of the shipborne communication-in-motion antenna and the possibility of actual installation and use, integrates the principle characteristics of the four seat frames, and provides a variant A-C-E seat frame scheme. The horizontal rolling bearing can adapt to the shipborne disturbance environment, overcomes the X shaft end blind area when the X-Y seat frame is at a low elevation angle, utilizes the characteristics of the horizontal rolling shaft 27 to replace the inclination of an azimuth shaft, and has the advantages of simple structure, light weight and power consumption, low cost and high reliability on the premise of realizing the functional performance.
The variant A-C-E seat frame provided by the scheme has the function of over-jacking by adding the C axis based on the A-E seat frame, but the elevation angle of the pitch angle of the traditional A-C-E seat frame (see the attached figure 1) is limited by structural constraint and can only reach about 120 degrees. The improved seat frame only lifts the transverse rolling beam to be vertical, the rotating axis of the C shaft and the working mechanism are unchanged, and A, C, E three shafts are intersected at one point of the tail end of the electric shaft, so that the pitch angle of the electric shaft of the antenna can move in a range of approximately 180 degrees above the top.
The modified structure looks very similar to the a-X-Y structure, i.e. the X-Y turntable is placed on the azimuth turntable (see fig. 2). However, the working mechanism of the scheme is not completely the same as that of an A-X-Y structure, and the scheme is mainly characterized in that when the tracking is carried out in a non-overhead space region, the function of the tracking is completely the same as that of a traditional A-C-E turntable, the function of the C axis is to ensure that the E axis is always parallel to the horizontal plane, so that a good horizontal reference is provided for the adjustment of the pitch angle of the antenna, the coupling interference of azimuth motion to the pitch angle is isolated, and the complicated calculation and the harsh sensor precision requirement on the control mechanism of the X-Y turntable are avoided. But in over-the-top tracking, it is similar to an X-Y mount with an azimuth axis of rotation a, the pitch E axis being the Y axis, and the cross (roll) C axis between the azimuth and pitch axes serving as the X axis. The E-axis and the C-axis form two axes in an X-Y coordinate system, and the C-axis is used as the X-axis in the X-Y coordinate system, thereby realizing the over-top function like an X-Y turntable.
The seat frame comprises a special-shaped A-C-E structure seat frame (a rotary table) and a matched servo control system. The appearance and the components of the scheme are shown in figure 3.
The invention relates to an A-C-E special-shaped seat frame, which is an improvement on the basis of the A-C-E type seat frame. The antenna is a dissimilarity form of a traditional azimuth-cross (roll) -pitching axis (A-C-E) type antenna seat frame in a ship-borne China-China domestic market product. The azimuth upright post (shown in figure 2) of a common A-C-E turntable seat frame is shortened to only keep the height required by the installation of an azimuth bearing, the appearance is changed into a cross-rolling beam slide rail, the middle part of a cross-rolling beam 12 is reduced and changed into an arc shape, the scheme keeps the characteristics of the A-C-E seat frame, and the A-C-E turntable seat frame has good over-top tracking capability and is particularly suitable for low-orbit satellite tracking.
This way the lowered roll beam 12 is designed to move on a circular arc shaped slide rail, which allows the radome to have a minimum outer diameter.
The whole system frame is subjected to surface anti-corrosion treatment by using a light aluminum alloy material, so that the self weight is reduced, and the load of a driving system is reduced.
The structural design firstly considers the influence of the rotational inertia of each shaft on the servo motion bandwidth of the system and the swing clearance of each shaft, and ensures the tracking performance; and the corresponding structural materials and salt mist corrosion prevention treatment are adopted in consideration of the influence of the marine use environment.
Each part is an outfield replaceable part, and the synchronous belt with the expired service life is replaced, so that the replacement is convenient, and other parts do not need to be detached.
The space in the cover is fully utilized, and all parts (replaceable units) are integrated in the antenna pedestal, so that the whole system is reasonable and compact in structure, the length of a cable is shortened, and the integration level of the system is improved.
The antenna seat frame (turntable) developed by the invention has the rotation capability in three directions of azimuth, roll and pitch, and ensures that the antenna tracks the low-orbit communication satellite under the condition that a carrier is a ship. The tracking range is 360 degrees in azimuth, 0-180 degrees in pitch (slightly smaller), and the tracking speed is 60 degrees/s. There is neither a low elevation blind zone nor an over-the-top blind zone.
The A-C-E seat frame adopted by the scheme avoids the problem of mutual coupling interference when two shafts of the A-E seat frame are adjusted, and the adjustment can be respectively carried out only according to the antenna azimuth angle and the pitch angle under the earth coordinate system calculated above. And adjusting the pitch angle of the antenna electric shaft in real time by taking an attitude horizontal platform plane formed by the antenna inertial sensor after the system is subjected to servo isolation environmental disturbance as a reference, wherein the attitude horizontal platform plane is not influenced by azimuth angle change. And azimuth adjustment, namely controlling a rotating antenna surface of a seat frame azimuth turntable to align a satellite to an azimuth deviation range according to an electric axis north azimuth angle given by a double-Beidou/GPS antenna direction-finding system, and carrying out fine adjustment according to effective information intensity transmitted by the satellite and collected by a double-mode (beacon) receiver, so that the precise alignment of the satellite is realized, and the adjustment process is independent of a pitch angle.
The technical indexes that this seat frame can reach:
the motion characteristic is as follows:
adapt to the ship body work-carrying range
Key points and protection points of the invention:
1) precise structural design
The arc-shaped transverse roller 27 has to move smoothly without jumping points, and under all movement postures, the three axes of azimuth, pitch and roll and the polarization axis have to intersect with each other and keep vertical.
The transmission mechanism drives the speed reducer through the motor and drives the corresponding shaft to rotate through the transmission belt, the return error is 1.5-2.5 arc minutes, namely 0.025-0.04 degrees, and the error requirement of system control precision distribution is met, so that the pointing precision and the tracking precision of the antenna are ensured.
2) Intelligent servo control system
The servo control mechanism (sensor signal processing and drive control) is needed for the large angle range, large speed range tracking and over-the-top tracking of the seat frame and the low-orbit satellite. Due to the adoption of the low-transverse-rolling beam design, the center of gravity and the load moment of the antenna structure are continuously changed by the BUC9 part with the antenna reflecting surface bearing thousands of grams in the tracking process, and uncertain factors brought to the design of a servo control system need to be eliminated by adopting intelligent measures.
Description of the drawings:
this patent only discusses the technology of the seat frame, and other devices associated with the VSAT antenna system for low earth orbit satellite communication, and the acquisition, tracking, dual antenna switching techniques, etc. are not within the scope of this patent application and are not described.
English concept explanation in this scheme:
LNB: low noise down converter
OMT: orthogonal mode coupler
BUC: up-conversion power amplifier
AHRS: course attitude reference system
The details of the present invention not described in detail are prior art.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (5)
1. A profile mount for an on-board low earth orbit satellite VSAT antenna, comprising: the antenna main reflecting surface (1) is fixedly connected to a pitching rotating shaft (2) rotating around the antenna main reflecting surface (1) through a reflecting surface support lug (101), a pitching motor (4) is arranged on one side of the antenna main reflecting surface (1), and a navigation attitude stepping motor (10) and an AHRS (11) are arranged on the other side, far away from the pitching motor (4); the two ends of the pitching rotating shaft (2) are connected with a rolling beam (12), a rolling beam sliding rail (26) is arranged below the rolling beam (12), and the rolling beam (12) is driven by a rolling motor (21) to roll along the rolling beam sliding rail (26); an azimuth turntable (25) is fixedly connected below the transverse rolling beam sliding rail (26); the middle part of the azimuth turntable (25) is provided with a radio frequency rotary joint and a signal slip ring (18), and the azimuth turntable (25) is driven by an azimuth motor (19) arranged on the azimuth turntable to rotate around an azimuth shaft (24) in azimuth; the azimuth rotary table (25) rotates in azimuth relative to a shock absorption base (13) fixedly connected to a ship carrier.
2. The profiled mount for a ship-borne low earth orbit satellite VSAT antenna of claim 1, characterized in that the profiled mount is a modified a-C-E mount, the azimuth post is shortened and evolved into a roller track (26) attached to the azimuth turntable (25) such that the roller track (12) plane is tilted up to an angle of 60 ° -80 ° from the azimuth turntable (25) plane.
3. The profiled mounting for a ship-borne low earth orbit satellite VSAT antenna of claim 2, characterized in that the roll beam (12) is a circular arc shaped slide rail structure.
4. The contoured mount of claim 1, wherein the contoured mount rotates in three directions, azimuth, roll and pitch, and the three axes of azimuth, pitch, roll and polarization intersect in pairs and remain perpendicular in all attitudes of motion.
5. The profiled mount for a VSAT antenna for a ship-borne low earth orbit satellite according to any of claims 1 to 4, wherein the frame of the profiled mount is made of a light aluminum alloy material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011006260.1A CN112259952A (en) | 2020-09-23 | 2020-09-23 | Special-shaped seat frame for ship-borne low-orbit satellite VSAT antenna |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011006260.1A CN112259952A (en) | 2020-09-23 | 2020-09-23 | Special-shaped seat frame for ship-borne low-orbit satellite VSAT antenna |
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| CN202011006260.1A Pending CN112259952A (en) | 2020-09-23 | 2020-09-23 | Special-shaped seat frame for ship-borne low-orbit satellite VSAT antenna |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112928444A (en) * | 2021-01-23 | 2021-06-08 | 新万基卫星技术有限公司 | Shipborne universal antenna in motion |
| CN113300106A (en) * | 2021-06-08 | 2021-08-24 | 中国电子科技集团公司第五十四研究所 | Two-axis antenna overhead method |
| CN113922088A (en) * | 2021-10-18 | 2022-01-11 | 北京微纳星空科技有限公司 | Low-orbit satellite antenna turntable and low-orbit satellite antenna |
| CN117074798A (en) * | 2023-08-11 | 2023-11-17 | 河北斐然科技有限公司 | Satellite antenna test turntable applied to navigation function aircraft |
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| 刘敏杰等: "舰载飞机自动着舰仿真系统建模", 《空军工程大学学报(自然科学版)》 * |
| 姜安等: "导航卫星跟踪体制及精度分析", 《现代雷达》 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112928444A (en) * | 2021-01-23 | 2021-06-08 | 新万基卫星技术有限公司 | Shipborne universal antenna in motion |
| CN113300106A (en) * | 2021-06-08 | 2021-08-24 | 中国电子科技集团公司第五十四研究所 | Two-axis antenna overhead method |
| CN113922088A (en) * | 2021-10-18 | 2022-01-11 | 北京微纳星空科技有限公司 | Low-orbit satellite antenna turntable and low-orbit satellite antenna |
| CN117074798A (en) * | 2023-08-11 | 2023-11-17 | 河北斐然科技有限公司 | Satellite antenna test turntable applied to navigation function aircraft |
| CN117074798B (en) * | 2023-08-11 | 2024-05-17 | 河北斐然科技有限公司 | Satellite antenna test turntable applied to navigation function aircraft |
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