GB2594104A - Ultralight satellite portable station - Google Patents

Ultralight satellite portable station Download PDF

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Publication number
GB2594104A
GB2594104A GB2010490.7A GB202010490A GB2594104A GB 2594104 A GB2594104 A GB 2594104A GB 202010490 A GB202010490 A GB 202010490A GB 2594104 A GB2594104 A GB 2594104A
Authority
GB
United Kingdom
Prior art keywords
antenna
pitching
azimuth
fine adjustment
folding hinge
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
GB2010490.7A
Other versions
GB202010490D0 (en
GB2594104B (en
Inventor
Ju Zhengfeng
Li Wei
Qiu Delong
Li Wenming
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Nanjing Zhongwang Satelite Communications Co Ltd
Original Assignee
Nanjing Zhongwang Satelite Communications Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from CN201910681884.4A external-priority patent/CN110311230B/en
Application filed by Nanjing Zhongwang Satelite Communications Co Ltd filed Critical Nanjing Zhongwang Satelite Communications Co Ltd
Publication of GB202010490D0 publication Critical patent/GB202010490D0/en
Publication of GB2594104A publication Critical patent/GB2594104A/en
Application granted granted Critical
Publication of GB2594104B publication Critical patent/GB2594104B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • HELECTRICITY
    • H01ELECTRIC ELEMENTS
    • H01QANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00Details of, or arrangements associated with, antennas
    • H01Q1/12Supports; Mounting means
    • H01Q1/1235Collapsible supports; Means for erecting a rigid antenna
    • HELECTRICITY
    • H01ELECTRIC ELEMENTS
    • H01QANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00Details of, or arrangements associated with, antennas
    • H01Q1/08Means for collapsing antennas or parts thereof
    • HELECTRICITY
    • H01ELECTRIC ELEMENTS
    • H01QANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00Details of, or arrangements associated with, antennas
    • H01Q1/12Supports; Mounting means
    • H01Q1/125Means for positioning
    • HELECTRICITY
    • H01ELECTRIC ELEMENTS
    • H01QANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00Details of, or arrangements associated with, antennas
    • H01Q1/12Supports; Mounting means
    • H01Q1/22Supports; Mounting means by structural association with other equipment or articles
    • H01Q1/24Supports; Mounting means by structural association with other equipment or articles with receiving set
    • H01Q1/247Supports; Mounting means by structural association with other equipment or articles with receiving set with frequency mixer, e.g. for direct satellite reception or Doppler radar
    • HELECTRICITY
    • H01ELECTRIC ELEMENTS
    • H01QANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00Details of, or arrangements associated with, antennas
    • H01Q1/27Adaptation for use in or on movable bodies
    • HELECTRICITY
    • H01ELECTRIC ELEMENTS
    • H01QANTENNAS, i.e. RADIO AERIALS
    • H01Q19/00Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic
    • H01Q19/10Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces
    • H01Q19/12Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces wherein the surfaces are concave
    • H01Q19/13Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces wherein the surfaces are concave the primary radiating source being a single radiating element, e.g. a dipole, a slot, a waveguide termination
    • H01Q19/132Horn reflector antennas; Off-set feeding
    • HELECTRICITY
    • H01ELECTRIC ELEMENTS
    • H01QANTENNAS, i.e. RADIO AERIALS
    • H01Q19/00Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic
    • H01Q19/10Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces
    • H01Q19/18Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces having two or more spaced reflecting surfaces
    • H01Q19/19Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces having two or more spaced reflecting surfaces comprising one main concave reflecting surface associated with an auxiliary reflecting surface
    • H01Q19/192Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces having two or more spaced reflecting surfaces comprising one main concave reflecting surface associated with an auxiliary reflecting surface with dual offset reflectors
    • HELECTRICITY
    • H01ELECTRIC ELEMENTS
    • H01QANTENNAS, i.e. RADIO AERIALS
    • H01Q19/00Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic
    • H01Q19/10Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces
    • H01Q19/18Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces having two or more spaced reflecting surfaces
    • H01Q19/19Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces having two or more spaced reflecting surfaces comprising one main concave reflecting surface associated with an auxiliary reflecting surface
    • H01Q19/193Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces having two or more spaced reflecting surfaces comprising one main concave reflecting surface associated with an auxiliary reflecting surface with feed supported subreflector
    • HELECTRICITY
    • H01ELECTRIC ELEMENTS
    • H01QANTENNAS, i.e. RADIO AERIALS
    • H01Q3/00Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
    • H01Q3/02Arrangements 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
    • H01Q3/08Arrangements 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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  • Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Variable-Direction Aerials And Aerial Arrays (AREA)
  • Support Of Aerials (AREA)
  • Details Of Aerials (AREA)

Abstract

The present application relates to the technical field of communication satellites, and in particular to an ultralight satellite portable station, which comprises an antenna assembly and a support frame. The antenna assembly comprises an antenna surface, a feed support, a pitch transmission mechanism, and an azimuth transmission mechanism. An electrical box is integrated on the back side of the antenna surface. The feed support is located on both sides of the antenna surface. The feed support is connected to the pitch transmission mechanism. The pitch transmission mechanism is connected to the azimuth transmission mechanism. The azimuth transmission mechanism is connected to the support frame by means of a fast installation mechanism. The front side of the antenna surface is connected at fixed included angles to a radio frequency transceiver assembly and a secondary reflection surface by means of a radio frequency transceiver assembly limit rod. An antenna controller, a satellite modem, a built-in device and so on are placed on the back side of the antenna surface, thereby preventing the direct irradiation of sunlight and optimizing the counterweight of the antenna. The antenna surface employs a folding hinge design, which eliminates the need for traditional multi-lobe assembly links, greatly saves on installation time and enhances the integrity of the antenna.

Description

ULTRALIGHT PORTABLE SATELLITE STATION
CROSS-REFERENCE TO RELATED APPLICATION
[0001] This application claims the benefit of the Chinese application No. 5 201910681884.4 filed on July 26, 2019, titled "ULTRALIGHT PORTABLE SATELLITE STATION", which is incorporated herein by reference in its entirety.
FIELD OF THE INVENTION
[0002] The present invention relates to the field of satellite communication technologies, and in particular, to an ultralight portable satellite station.
BACKGROUND OF THE INVENTION
[0003] In the current application, an offset feed satellite antenna generally employs a box structure. As shown in Fig.1, the whole antenna is generally formed by an antenna face 1-1, a feed source support 1-2, a feed source system, an azimuth pitching drive component 1-4, an electrical box 1-3, a windproof support 1-6 and a carrying handle 1-5, etc. An electrical box body and the azimuth pitching drive component are mounted on a bottom plate of the antenna structure, and an antenna feed system is mounted on the azimuth pitching drive component of the antenna. Such an antenna structure can meet the requirements of ordinary communication and has the advantages of compact volume after being folded and large electrical box volume for accommodating multiple communication machines. However, it also has the following disadvantages: [0004] The electrical box is located on the bottom of the antenna, thus it has no wading ability; [0005] The feed source support part has devices such as a power amplifier and a RF, etc., and the weight is large, while no corresponding counterweight is provided on the back of the antenna face, thus the gravity center of the pitching rotating part is located at the front end, and a larger retarder and a larger motor are required during pitching rotation; [0006] The antenna electrical box is located at the front end of the antenna, it may be directed exposed to the sunlight at a high temperature in summer, which may result in the failure of communication devices due to the abnormal rise of temperature in the box; [0007] The antenna face employs a multi-petal assembling mode, and a certain assembling time is needed for antenna construction; [0008] The weight is large, which cannot meet the increasingly miniaturization requirement on the antenna.
[0009] In conclusion, such an antenna structure is generally applied to a situation of high-capacity broadband communication.
[0010] China Patent Publication No. CN104518271A discloses "A Portable Automatic Satellite-Searching System", which employs a prime focus antenna structure. As shown in Fig.2, in this solution, a quadripod is employed as the support structure, an azimuth pitching drive structure is placed on the quadripod 2-1, an antenna face 2-2 employs a multi-petal assembling solution, and a power amplifier RF system 2-3 is placed on the back of the antenna face. Such a solution has the following advantages: the wading ability of the antenna may be improved; the electrical box may be prevented from being exposed to direct sunlight; and the pitching center is near to the rotational axis, etc. However, it also has certain disadvantages as follows.
[0011] 1. The antenna face generally employs eight-petal assembling, and the assembling and construction time for the antenna face is long.
[0012] 2. The feed source rod of the antenna face needs to be disassembled during folding, and it needs to be connected onto the central disc of the antenna face via screw thread in use.
[0013] 3. The overall structure of the antenna is heavy, thus it can only be carried in a box, rather than being carried on the back, which is inconvenient in a complex terrain such as a mountainous area.
[0014] 4. The speed of the manual azimuth and pitching adjustment structure is low, and there exists no fast angle adjustment and angle fine adjustment structure.
[0015] The volume of the control box is small, and it can only accommodate the control part and the drive part of the antenna itself, with no space for a built-in modem and other business devices.
SUMMARY OF THE INVENTION
[0016] Therefore, the objects of the present invention are to overcome the disadvantages of the prior art and to provide an ultralight portable satellite station with a small volume, a light weight and a high use and mounting efficiency.
[0017] In order to solve the above technical problem, the invention employs the following technical solutions: [0018] An ultralight portable satellite station, which includes an antenna assembly and a support frame, wherein the antenna assembly includes an antenna face, a feed source support, a pitching drive mechanism and an azimuth drive mechanism, the rear face of the antenna face is integrally provided with an electrical box, the feed source support is located on two sides of the antenna face, the feed source support is connected with a pitching drive mechanism, the pitching drive mechanism is connected with the azimuth drive mechanism, the azimuth drive mechanism is connected with the is support frame via a quick assembly mechanism, and a front face of the antenna face is connected with an RF transceiver assembly and a secondary reflecting surface at a fixed angle via an RF transceiver assembly limit lever; [0019] A feed source and polarization drive mechanism is further connected on the feed source support, the feed source is connected with a duplexer, the receiving end of the duplexer is connected with a down-conversion amplifier, and the transmitting end of the duplexer is connected with an up-conversion amplifier.
[0020] Further, the antenna face is hinged by three antenna panels via an antenna face folding hinge.
[0021] Further, the antenna face includes a primary antenna face, two secondary antenna faces, an antenna face folding hinge and a locking hasp, wherein the two secondary antenna faces are provided on two sides of the primary antenna face, and the secondary antenna face is connected with the primary antenna face via the antenna face folding hinge and the locking hasp; [0022] The antenna face folding hinge includes a folding hinge fastener and a folding hinge rotor; one end of the folding hinge fastener is connected with one end of the folding hinge rotor via a hinge shaft; a fixing nut is set on one end of the hinge shaft that is adjacent to the folding hinge fastener; a damping gasket is set on the hinge shaft, and the damping gasket is located between the folding hinge fastener and the folding hinge rotor; [0023] The secondary antenna face is connected with one end of the folding hinge rotor that is far from the hinge shaft; one end of the folding hinge fastener matching the folding hinge rotor, which is far from the hinge shaft, is connected with the primary antenna face.
[0024] Further, the support frame includes a support rod mounting base, the support rod mounting base is hinged with several support rods, and a gas spring is connected between each support rod and the support rod mounting base.
[0025] Further, a lower surface of the support rod mounting base is provided with a connecting rod, one end of each gas spring is hinged with a bottom edge of the connecting rod, and the other end is connected with the support rod via a connecting piece and a screw bolt.
[0026] Further, the azimuth drive mechanism includes an azimuth coarse adjustment sleeve, an azimuth coarse adjustment axis, an azimuth coarse adjustment locking knob, an azimuth fine adjustment reduction gearbox, an azimuth fine adjustment motor and an azimuth fine adjustment manual knob.
[0027] The upper surface of the support rod mounting base is provided with an antenna drive connecting piece, the azimuth coarse adjustment axis is connected with the antenna drive connecting piece via screw thread, and the azimuth coarse adjustment sleeve is provided with an azimuth coarse adjustment locking knob.
[0028] The azimuth coarse adjustment sleeve is further provided with an azimuth fine adjustment reduction gearbox. The azimuth fine adjustment reduction gearbox is a gear worm driving structure. One end of the worm of the azimuth fine adjustment reduction gearbox is connected with an azimuth fine adjustment manual knob, and the other end of the worm is connected with an azimuth fine adjustment motor. The upper part of the azimuth fine adjustment reduction gearbox is connected with a pitching drive mechanism.
[0029] Further, a windproof support rod is further connected onto the support frame. One end of the windproof support rod is connected with the support rod via an axle pin, and the other end is connected with the support rod via a fixing screw.
[0030] Further, the pitching drive mechanism includes a pitching coarse adjustment axis sleeve, a pitching coarse adjustment locking knob, a pitching fine adjustment reduction gearbox, a pitching fine adjustment motor, a pitching fine adjustment manual knob, a pitching coarse adjustment angle limit screw and a pitching output shaft.
[0031] The pitching fine adjustment reduction gearbox is a gear worm driving structure. 10 One end of the worm is connected with the pitching fine adjustment manual knob, and the other end of the worm is connected with the pitching fine adjustment motor. A worm gear output hole in the pitching fine adjustment reduction gearbox is connected with the pitching output shaft via a key, and the pitching output shaft is fixed to the primary antenna face via the pitching coarse adjustment angle limit screw.
is [0032] Further, the secondary reflecting surface and the feed source support are connected via a secondary reflecting surface rotating shaft, and a limit mechanism and a locking mechanism are further provided between the secondary reflecting surface and the feed source support.
[0033] Further, the polarization drive mechanism includes a polarization rotating motor and a polarization rotating motor and an angle sensor [0034] Further, the electrical box is mounted with an antenna controller, a satellite modem and other built-in devices, and the electrical box is further provided with an electrical box cover and a heat sink.
[0035] The technical solutions of the invention have the beneficial effects below.
[0036] 1. The antenna face employs a 0.75 m equivalent Gregorian antenna face, which is compatible with KU/KA frequency range, and communication in KU and KA frequency ranges is realized by changing RF assemblies in different frequency ranges. [0037] 2. The base support of the antenna employs a carbon fiber support frame structure, which can ensure a high strength while reducing the weight and has a wading depth of about 15 cm.
[0038] 3. The azimuth rotation of the antenna employs a large-scale angle fast adjustment and azimuth angle manual fine adjustment or electric fine adjustment structure, which can greatly reduce the satellite alignment time. During angle adjustment, the azimuth angle is first rotated rapidly to around the theoretic azimuth angle, and the fast adjustment structure is locked, and then manual or electric fine adjustment is carried out to align with the satellite.
[0039] 4. Antenna pitching rotation also employs a large-scale angle fast adjustment and pitching manual fine adjustment or electric fine adjustment structure. During angle adjustment, the pitching angle is first rotated rapidly to the theoretic pitching angle, and In the fast adjustment structure is locked, and then manual or electric fine adjustment is carried out to align with the satellite.
[0040] 5. The antenna face employs a folding hinge-type design, thus a traditional multi-petal assembling stage may be avoided, the erection time may be greatly saved, and the integrity of the antenna may be reinforced.
[0041] 6. The antenna controller, the satellite modem and the built-in device, etc., are placed on the back of the antenna face, thereby avoiding direct sunlight and optimizing the counterweight of the antenna.
BRIEF DESCRIPTION OF THE DRAWINGS
[0042] In order to more clearly illustrate the technical solutions of the embodiments of the invention or of the prior art, the drawings needed in the description of the embodiments or the prior art will be briefly introduced below. Apparently, the drawings in the description below are only some embodiments of the invention, and other drawings may also be obtained by one of ordinary skills in the art according to these drawings without creative work.
[0043] Fig.1 is a three-dimensional diagram of a common box-type offset feed antenna.
[0044] Fig.2 is a three-dimensional diagram of a common prime focus antenna.
[0045] Fig.3 is a three-dimensional diagram showing the overall working state of an ultralight portable satellite station.
[0046] Fig.4 is a three-dimensional diagram showing the folded state of a support frame.
[0047] Fig.5 is a three-dimensional diagram showing the unfolded state of a support frame.
[0048] Fig.6 is a three-dimensional diagram showing the folded state of an antenna assembly.
[0049] Fig.7 is a three-dimensional diagram showing the assembled state of the antenna assembly and the support frame.
[0050] Fig.8 is a partial three-dimensional diagram of an azimuth and pitching drive in structure.
[0051] Fig.9 is a cutaway view of an azimuth and pitching drive structure.
[0052] Fig.10 is a partial three-dimensional diagram of a polarization drive structure. [0053] Fig.11 is an unfolded view of an antenna face.
[0054] Fig.12 is a structural representation of an antenna face folding hinge.
[0055] List of the reference numbers in the drawings: 1 Support Frame 101 Gas Spring 102 Locking Nut 103 Fixing Screw 104 Antenna Drive Connecting Piece 2 Windproof Support Rod 3 Azimuth Drive Mechanism 301 Azimuth Coarse Adjustment Locking Knob 302 Azimuth Coarse Adjustment Sleeve 303 Azimuth Fine Adjustment Manual Knob 304 Azimuth Fine Adjustment Reduction Gearbox 305 Azimuth Fine Adjustment Motor 306 Azimuth Coarse Adjustment Axis 4 Pitching Drive Mechanism 401 Pitching Coarse Adjustment Locking Knob 402 Pitching Coarse Adjustment Axis Sleeve 403 Pitching Fine Adjustment Reduction Gearbox 404 Pitching Fine Adjustment Manual Knob 405 Pitching Fine Adjustment Motor 406 Pitching Coarse Adjustment Angle Limit Screw 407 Pitching Output Shaft Electrical Box 6 Antenna Face 7 RF Transceiver Assembly Limit Lever 8 RF Transceiver Assembly 9 Secondary Reflecting Surface Feed Source Support 11 Antenna Assembly 12 Antenna Face Folding Hinge 121 Folding Hinge Fastener 122 Folding Hinge Rotor 123 Hinge Shaft 124 Fixing Nut Damping Gasket 13 Antenna Panel 131 Primary Antenna Face 132 Secondary Antenna Face 133 Locking Hasp 14 Up-Conversion Amplifier 15 Rotating Joint 16 Duplexer 17 Polarization Rotating Motor 18 Angle Sensor 19 Feed Source 20 Down-Conversion Amplifier 21 Secondary Reflecting Surface Rotating Shaft
DETAILED DESCRIPTION OF THE EMBODIMENTS
[0056] The invention will be further described in detail below in conjunction with the drawings. These drawings are all simplified schematic diagrams and merely illustrate the basic structure of the invention in a schematic way. Therefore, the drawings only show the parts related to the invention.
[0057] Referring to Figs. 3-12, it should be noted that, all the structures, scales and sizes shown in the drawings of the invention are merely provided for matching the contents disclosed in the invention and for one skilled in the art to understand the in invention, rather than limiting the implementation conditions of the invention, and thus have no technically substantial meanings. Therefore, any modifications of the structures, variations of the scale relations or adjustments of the sizes made without affecting the functions and objects of the invention will fall into the technical scope of the invention. At the same time, terms such as "upper" and "lower", etc., are used in the invention for more apparently illustrating the invention, rather than limiting the implementation scope of the invention, and variations or adjustments of the relative relations, without essentially modifying the technical contents, should be regarded as pertaining to scope of the invention.
[0058] The support frame 1 in the invention is preferably a tripod.
[0059] Fig.3 is a three-dimensional diagram showing the overall working state of an ultralight portable satellite station.
[0060] Fig.10 is a partial three-dimensional diagram of a polarization drive structure. [0061] As shown in Fig.3 and Fig.10, an ultralight portable satellite station according to the invention is illustrated by taking an equivalent 0.75 m Ku band antenna as an embodiment, wherein an antenna face 6 employs a 0.75 m equivalent Gregorian antenna face 6, which is compatible with KU/KA frequency range, and KU and KA frequency range communication is realized by changing radio frequency (RF) assemblies of different frequency ranges, and the structure thereof mainly employs aluminum and carbon fiber.
[0062] The ultralight portable satellite station of the invention includes an antenna assembly 11 and a support frame 1. The antenna assembly 11 includes an antenna face 6, a feed source support 10, a pitching drive mechanism 4 and an azimuth drive mechanism 3. The rear face of the antenna face 6 is integrally provided with an electrical box 5. The feed source support 10 is located on two sides of the antenna face 6. The feed source support 10 is connected with the pitching drive mechanism 4, and the pitching drive mechanism 4 is connected with the azimuth drive mechanism 3. The azimuth drive mechanism 3 is connected with the support frame 1 via a quick assembly mechanism. The front face of the antenna face 6 is connected with an RF transceiver assembly 8 and a secondary reflecting surface 9 at a fixed angle. The RF transceiver assembly 8 is connected with a feed source 19 and a polarization drive mechanism. The feed source 19 is connected with a duplexer 16. The receiving end of the duplexer 16 is connected with a down-conversion amplifier 20, and the transmitting end of the duplexer 16 is connected with an up-conversion amplifier 14 via a rotating joint 15 and a wave guide. The polarization drive mechanism includes a polarization rotating motor 17 and an angle sensor 18. The polarization rotating motor 17 drives the feed source 19 to rotate, and the angle sensor 18 is configured for angle feedback.
[0063] Working principle: during satellite alignment operation, the whole antenna assembly 11 is first manually rotated, so that the azimuth drive mechanism 3 rotates right and left around the support frame 1, and when the antenna is rotated to the theoretic azimuth angle according to the data on a rear display of the antenna face 6, the knob is locked, and hence the azimuth coarse adjustment is accomplished; after azimuth coarse adjustment is accomplished, the whole antenna assembly 11 is manually rotated up and down, so that the pitching drive mechanism 4 rotates up and down around a pitching coarse adjustment axis sleeve 402, and when the antenna is rotated to the theoretic pitching angle according to the data on a rear display of the antenna face 6, the knob is locked, and hence pitching coarse adjustment is accomplished. The support frame 1 functions to support the whole antenna and can provide a wading depth of about 15cm. In this embodiment, the support frame 1 employs a carbon fiber support frame structure, and it may ensure a high strength while reducing the weight. An electrical box 5 is provided on the rear face of the antenna, and an antenna controller, a satellite modem and other built-in devices are mounted in the electrical box 5. The antenna controller, the satellite modem and other built-in devices, etc., are placed on the back of the antenna face 6, thereby avoiding direct sunlight and optimizing the counterweight of the antenna. The electrical box 5 is further provided with an electrical box cover, which may protect the devices in the electrical box 5.
[0064] In order to reduce the erection time of the whole apparatus, the antenna face 6 in this embodiment is formed by hinging three antenna panels 13 via antenna face folding hinges 12. That is, it includes a primary antenna face and two side panels, the two side panels may be turned over and folded on the primary antenna face under the action of the connecting piece, and during turning, the turning order of the two side panels is optional. The antenna face 6 employs a folding hinge-type design, thus a traditional multi-petal assembling stage may be avoided, the construction time may be greatly saved, and the integrity of the antenna may be reinforced.
[0065] In one possible implementation mode, as shown in Fig.11, the antenna face 6 includes a primary antenna face 131, two secondary antenna faces 132, an antenna face folding hinge 12 and a locking hasp 133. The two secondary antenna faces 132 are provided on the two sides of the primary antenna face 131, and the secondary antenna face 132 is connected with the primary antenna face 131 via the antenna face folding hinge 12 and the locking hasp 133.
[0066] It should be noted that, when it is not erected, the two secondary antenna faces 132 may be turned over onto one end face of the primary antenna face 131 via the antenna face folding hinge 12. During erection, the two secondary antenna faces 132 may be turned over from the one end face of the primary antenna face 131 to the two sides of the primary antenna face 131 via the folding hinge 12, and then the relative positions of the two secondary antenna faces 132 and the primary antenna face 131 may be fixed by the locking hasp 133. In this embodiment of the invention, an assembling stage may be avoided, thereby having the characteristics of fast deployment and easy operating.
[0067] In some embodiments, the locking hasp 133 includes a locking hasp subpiece and a locking hasp masterpiece matching the locking hasp subpiece.
[0068] The locking hasp subpiece is provided on the secondary antenna face 132, and the primary antenna face 131 is provided with a locking hasp masterpiece matching the locking hasp subpiece, or the locking hasp masterpiece is provided on the secondary antenna face 132, and the primary antenna face 131 is provided with a locking hasp subpiece matching the locking hasp masterpiece.
[0069] In the embodiment of the invention, the number of the locking hasp 133 is two, and the two locking hasps 133 are respectively provided at the midpoint of the connection part between the primary antenna face 131 and the two secondary antenna faces 132. In the invention, the number of the locking hasp 133 is at least two, and the specific number is not limited here.
[0070] As shown in Fig.12, the antenna face folding hinge 12 includes a folding hinge fastener 121 and a folding hinge rotor 122; one end of the folding hinge fastener 121 is connected with one end of the folding hinge rotor 122 via a hinge shaft 123; the fixing nut 124 is set on one end of the hinge shaft 123 that is adjacent to the folding hinge fastener 121; the hinge shaft 123 is set with a damping gasket 125, and the damping gasket 125 is located between the folding hinge fastener 121 and the folding hinge rotor 122.
[0071] In use, the folding hinge fastener 121 and the folding hinge rotor 122 may rotate relatively around the hinge shaft 123, and the damping gasket 125 may prevent the connection part between the folding hinge fastener 121 and the folding hinge rotor 122 from being worn out.
[0072] The secondary antenna face 132 is connected with one end of the folding hinge rotor 122 that is far from the hinge shaft 123; and one end of the folding hinge fastener 121 matching the folding hinge rotor 122, which is far from the hinge shaft 123, is connected with the primary antenna face 131.
[0073] In the embodiment of the invention, the number of the antenna face folding hinge 12 is four, and the folding hinge fasteners 121 of the four antenna face folding hinges 12 are respectively connected with the four corners of the primary antenna face 131. Four folding hinge rotors 122 matching the folding hinge fastener 121 are correspondingly provided on the two secondary antenna faces 132 respectively. Fig.4 is a three-dimensional diagram showing the folded state of the support frame 1.
[0074] Fig.5 is a three-dimensional diagram showing the unfolded state of the support frame 1.
[0075] As shown in Fig.4 and Fig.5, in order to improve the convenience of use of the support frame 1, the support frame 1 in this embodiment includes a support rod mounting base. The support rod mounting base is hinged with several support rods, and a gas spring 101 is connected between each support rod and the support rod mounting base; the lower surface of the support rod mounting base is provided with a connecting rod, one end of each gas spring 101 is hinged with the bottom edge of the connecting rod, and the other end is connected with the support rod via a connecting piece and a screw bolt; the support frame 1 is in the state shown in Fig.4 when it is taken out from a bag, and when the strapping on the support frame 1 is released, the support frame 1 extends automatically under the action of several gas springs 101, till the gas springs 101 reach the maximum stroke, and hence the overall deployment of the support frame 1 is accomplished. The support frame 1 is further connected with a strap, and after the support frame 1 is folded, the support frame 1 may be tied up by the strap in the state shown in Fig.4. In such a way, the folding of the support frame 1 will be more convenient, and less space will be occupied.
[0076] In order to improve the windproof strength of the whole apparatus in use, the support frame 1 is connected with a windproof support rod 2, one end of the windproof support rod 2 is connected with the support rod via an axle pin, and the other end is connected with the support rod via a fixing screw 103. The support rod is provided with a connecting piece via a screw bolt and a screw nut, and the connecting piece is provided with a connection hole for being connected with the fixing screw 103. The support frame 1 is in the state shown in Fig.4 when it is taken out from the bag, and a pair of windproof support rods is fixed on the support frame 1 via the fixing screw 103 for the windproof support rod 2. After the whole apparatus are unfolded and mounted, the other end of the windproof support rod 2 is connected with the rear face of the antenna via the fixing screw 103, so that other apparatus such as the rear face of the antenna is stably fixed on the support frame 1, and the portable satellite station can be used normally even in a bad weather such as gale. In this embodiment, the windproof support rod 2 is a telescopic rod that includes two support rod segments, and the two support rod segments are connected via a telescopic locking nut 102.
[0077] Fig.8 is a partial three-dimensional diagram of an azimuth and pitching drive structure.
[0078] Fig.9 is a cutaway view of an azimuth and pitching drive structure.
[0079] As shown in Fig.8 and Fig.9, the azimuth drive mechanism 3 includes an azimuth coarse adjustment sleeve 302, an azimuth coarse adjustment axis 306, an azimuth coarse adjustment locking knob 301, an azimuth fine adjustment reduction gearbox 304, an azimuth fine adjustment motor 305 and an azimuth fine adjustment manual knob 303.
[0080] The upper surface of the support rod mounting base is provided with an antenna drive connecting piece 104, the azimuth coarse adjustment axis 306 is connected with the antenna drive connecting piece 104 via screw thread, and the azimuth coarse adjustment sleeve 302 is provided with the azimuth coarse adjustment locking knob 301.
[0081] The azimuth coarse adjustment sleeve 302 is further provided with the azimuth fine adjustment reduction gearbox 304, and the azimuth fine adjustment reduction gearbox 304 is a gear worm driving structure. One end of the worm of the azimuth fine adjustment reduction gearbox 304 is connected with the azimuth fine adjustment manual knob 303, and the other end of the worm is connected with the azimuth fine adjustment motor 305. The upper part of the azimuth fine adjustment reduction gearbox 304 is connected with the pitching drive mechanism 4, and the azimuth fine adjustment motor 305 in this embodiment is a DC geared motor [0082] The pitching drive mechanism 4 includes a pitching coarse adjustment axis sleeve 402, a pitching coarse adjustment locking knob 401, a pitching fine adjustment reduction gearbox 403, a pitching fine adjustment motor 405, a pitching fine adjustment manual knob 404, a pitching coarse adjustment angle limit screw 406 and a pitching output shaft 407.
[0083] The pitching fine adjustment reduction gearbox 403 may rotate freely in the pitching coarse adjustment axis sleeve 402 to attain the object of pitching coarse adjustment. The pitching coarse adjustment axis sleeve 402 is provided with a pitching coarse adjustment angle limit screw 406, and the pitching coarse adjustment angle limit screw 406 functions to restrict the pitching coarse adjustment angle. The pitching coarse adjustment axis sleeve 402 is provided with a pitching coarse adjustment locking knob 401, and the pitching coarse adjustment locking knob 401 may tightly fix the pitching fine adjustment reduction gearbox 403 and the pitching coarse adjustment axis sleeve 402.
[0084] One end of the worm of the pitching fine adjustment reduction gearbox 403 is connected with the pitching fine adjustment manual knob 404, and the other end of the worm is connected with the pitching fine adjustment motor 405. In this embodiment, the pitching fine adjustment motor 405 is a DC geared motor The worm gear output hole in the pitching fine adjustment reduction gearbox 403 is connected with the pitching output shaft 407 via a key, and the pitching output shaft 407 is fixed to the primary antenna face via the pitching coarse adjustment angle limit screw 406.
[0085] As shown in Fig.10, in order to further improve the folding convenience of the portable satellite station, in this embodiment, the secondary reflecting surface 9 and the feed source support 10 are connected via a secondary reflecting surface rotating shaft 21, and a limit mechanism and a locking mechanism are further provided between the secondary reflecting surface 9 and the feed source support 10. By such a structure, in use, the secondary reflecting surface 9 rotates around the secondary reflecting surface rotating shaft 21 to a working position and is locked by a locking mechanism. When the portable satellite station needs to be folded, the secondary reflecting surface 9 rotates around the secondary reflecting surface rotating shaft 21 to a position parallel to the feed source support 10, and hence the secondary reflecting surface 9 may abut upon the antenna face 6, that is, it may be in a folded position, thus the folded volume may be reduced.
[0086] The antenna assembly 11 is in the state shown in Fig.6 when it is taken out 30 from a backpack. As shown in Fig.7, the antenna assembly 11 is connected with the support frame 1, and a satellite alignment operation may be carried out when the antenna face 6 is extended. After the satellite alignment operation is accomplished, the two windproof support rods 2 on the support frame 1 are fixed to the back of the antenna face 6 via the windproof support rod fixing screw 103.
[0087] In conclusion, the invention has the advantages of light weight, fast satellite alignment and easy construction, etc., and satellite alignment and communication may be carried out so long as the support frame 1 is connected with the antenna assembly 11.
[0088] The objects, technical solutions and beneficial effects of the invention have in been illustrated in detail by the above specific embodiments. However, it should be understood that the above embodiments are only some specific embodiments of the invention, rather than limiting the protection scope of the invention. All modifications, equivalent substitutions and improvements made without departing from the spirit and principle of the invention should be construed as pertaining to the protection scope of the invention.

Claims (10)

  1. WHAT IS CLAIMED IS: 1. An ultralight portable satellite station, comprising: an antenna assembly (11) and a support frame (1), the antenna assembly comprises an antenna face (6), a feed source support (10), a pitching drive mechanism (4) and an azimuth drive mechanism (3), the rear face of the antenna face is integrally provided with an electrical box (5), the feed source support is located on two sides of the antenna face, the feed source support is connected with the pitching drive mechanism, the pitching drive mechanism is connected with the azimuth drive mechanism, the azimuth drive mechanism is connected with the support frame via a quick assembly mechanism, and a front face of 10 the antenna face is connected with an RF transceiver assembly (8) and a secondary reflecting surface (9) at a fixed angle via an RF transceiver assembly limit lever (7); a feed source (19) and a polarization drive mechanism are further connected on the feed source support, the feed source is connected with a duplexer (16), a receiving end of the duplexer is connected with a down-conversion amplifier (20), and a transmitting end of the duplexer is connected with an up-conversion amplifier (14).
  2. 2. The ultralight portable satellite station according to claim 1, wherein the antenna face (6) is hinged by three antenna panels (13) via an antenna face folding hinge (12).
  3. 3. The ultralight portable satellite station according to claim 2, wherein the antenna face (6) comprises a primary antenna face (131), two secondary antenna faces (132), an antenna face folding hinge (12) and a locking hasp (133), the two secondary antenna faces are provided on two sides of the primary antenna face, and the secondary antenna face is connected with the primary antenna face via the antenna face folding hinge and the locking hasp; the antenna face folding hinge comprises a folding hinge fastener (121) and a folding hinge rotor (122); one end of the folding hinge fastener is connected with one end of the folding hinge rotor via a hinge shaft (123); a fixing nut (124) is set on one end of the hinge shaft that is adjacent to the folding hinge fastener; a damping gasket (125) is set on the hinge shaft, and the damping gasket is located between the folding hinge fastener and the folding hinge rotor; the secondary antenna face is connected with one end of the folding hinge rotor that is far from the hinge shaft; one end of the folding hinge fastener matching the folding hinge rotor, which is far from the hinge shaft, is connected with the primary antenna face.
  4. 4. The ultralight portable satellite station according to claim 1, wherein the support frame (1) comprises a support rod mounting base, the support rod mounting base is hinged with several support rods, and a gas spring (101) is connected between each support rod and the support rod mounting base.
  5. 5. The ultralight portable satellite station according to claim 4, wherein a lower surface of the support rod mounting base is provided with a connecting rod, one end of each gas spring is hinged with a bottom edge of the connecting rod, and the other end is connected with the support rod via a connecting piece and a screw bolt.
  6. 6. The ultralight portable satellite station according to claim 4, wherein the azimuth drive mechanism (3) comprises an azimuth coarse adjustment sleeve (302), an azimuth coarse adjustment axis (306), an azimuth coarse adjustment locking knob (301), an azimuth fine adjustment reduction gearbox (304), an azimuth fine adjustment motor (305) and an azimuth fine adjustment manual knob (303); an upper surface of the support rod mounting base is provided with an antenna drive connecting piece (104), the azimuth coarse adjustment axis is connected with the 20 antenna drive connecting piece via screw thread, and the azimuth coarse adjustment sleeve is provided with the azimuth coarse adjustment locking knob; the azimuth coarse adjustment sleeve is further provided with an azimuth fine adjustment reduction gearbox, the azimuth fine adjustment reduction gearbox is a gear worm driving structure, one end of the worm of the azimuth fine adjustment reduction gearbox is connected with the azimuth fine adjustment manual knob, and the other end of the worm of the azimuth fine adjustment reduction gearbox is connected with the azimuth fine adjustment motor, and an upper part of the azimuth fine adjustment reduction gearbox is connected with a pitching drive mechanism (4).
  7. 7. The ultralight portable satellite station according to claim 1, wherein a windproof support rod (2) is further connected onto the support frame (1), one end of the windproof support rod is connected with the support rod via an axle pin, and the other end is connected with the support rod via a fixing screw (103).
  8. 8. The ultralight portable satellite station according to claim 1, wherein the pitching drive mechanism (4) comprises a pitching coarse adjustment axis sleeve (402), a pitching coarse adjustment locking knob (401), a pitching fine adjustment reduction gearbox (403), a pitching fine adjustment motor (405), a pitching fine adjustment manual knob (404), a pitching coarse adjustment angle limit screw (406) and a pitching output shaft (407); the pitching fine adjustment reduction gearbox is a gear worm driving structure, one end of the worm of the pitching fine adjustment reduction gearbox is connected with the pitching fine adjustment manual knob, the other end of the worm of the pitching fine adjustment reduction gearbox is connected with the pitching fine adjustment motor, a worm gear output hole in the pitching fine adjustment reduction gearbox is connected with the pitching output shaft via a key, and the pitching output shaft is fixed to the primary antenna face via the pitching coarse adjustment angle limit screw.
  9. 9. The ultralight portable satellite station according to claim 1, wherein the secondary reflecting surface (9) and the feed source support (10) are connected via a secondary reflecting surface rotating shaft (21), and a limit mechanism and a locking mechanism are further provided between the secondary reflecting surface and the feed source support.
  10. 10. The ultralight portable satellite station according to claim 1, wherein the electrical box (5) comprises an antenna controller and a satellite modem, and the electrical box is further provided with an electrical box cover and a heat sink.
GB2010490.7A 2019-07-26 2019-09-29 Ultralight portable satellite station Active GB2594104B (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201910681884.4A CN110311230B (en) 2019-07-26 2019-07-26 Ultra-light satellite portable station
PCT/CN2019/109041 WO2021017152A1 (en) 2019-07-26 2019-09-29 Ultralight satellite portable station

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Publication number Priority date Publication date Assignee Title
CN116073930B (en) * 2021-11-02 2024-07-09 北京广监云科技有限公司 Frequency modulation broadcast real-time monitoring device

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH01205604A (en) * 1988-02-12 1989-08-18 Toshiba Shiyutoken Service Kk Offset parabolic antenna
GB2313957A (en) * 1996-06-04 1997-12-10 Nec Corp Antenna assembly
CN2694516Y (en) * 2003-09-15 2005-04-20 上海赛天通信技术有限公司 Vehicle mounted satellite communication antenna
US20070052607A1 (en) * 2005-09-08 2007-03-08 Norsat International Inc. Antenna positioner for portable satellite terminal
CN102868023A (en) * 2012-09-21 2013-01-09 广州海格通信集团股份有限公司 Satellite antenna pitching adjusting device
CN102983902A (en) * 2012-11-30 2013-03-20 西安欧赛通信科技有限公司 1.2m feedback full-automatic portable emergency satellite communication antenna servo system
CN103490173A (en) * 2013-09-30 2014-01-01 无锡华信雷达工程有限责任公司 Portable carbon fiber double reverse satellite communication antenna
US20140118196A1 (en) * 2012-10-25 2014-05-01 Pulse Finland Oy Modular cell antenna apparatus and methods
WO2014198224A1 (en) * 2013-06-13 2014-12-18 南京中网卫星通信股份有限公司 Integrated and disassemblable portable satellite communication station
CN105846041A (en) * 2016-05-24 2016-08-10 海中信(北京)卫星通信股份公司 Novel dismounting-free portable satellite communication antenna terminal
CN205564955U (en) * 2016-04-25 2016-09-07 王凯 New -type satellite receiving antenna
RU190369U1 (en) * 2019-02-05 2019-06-28 Общество с ограниченной ответственностью "Информационно-контрольные технологии и системы" Satellite Antenna Device

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH01205604A (en) * 1988-02-12 1989-08-18 Toshiba Shiyutoken Service Kk Offset parabolic antenna
GB2313957A (en) * 1996-06-04 1997-12-10 Nec Corp Antenna assembly
CN2694516Y (en) * 2003-09-15 2005-04-20 上海赛天通信技术有限公司 Vehicle mounted satellite communication antenna
US20070052607A1 (en) * 2005-09-08 2007-03-08 Norsat International Inc. Antenna positioner for portable satellite terminal
CN102868023A (en) * 2012-09-21 2013-01-09 广州海格通信集团股份有限公司 Satellite antenna pitching adjusting device
US20140118196A1 (en) * 2012-10-25 2014-05-01 Pulse Finland Oy Modular cell antenna apparatus and methods
CN102983902A (en) * 2012-11-30 2013-03-20 西安欧赛通信科技有限公司 1.2m feedback full-automatic portable emergency satellite communication antenna servo system
WO2014198224A1 (en) * 2013-06-13 2014-12-18 南京中网卫星通信股份有限公司 Integrated and disassemblable portable satellite communication station
CN103490173A (en) * 2013-09-30 2014-01-01 无锡华信雷达工程有限责任公司 Portable carbon fiber double reverse satellite communication antenna
CN205564955U (en) * 2016-04-25 2016-09-07 王凯 New -type satellite receiving antenna
CN105846041A (en) * 2016-05-24 2016-08-10 海中信(北京)卫星通信股份公司 Novel dismounting-free portable satellite communication antenna terminal
RU190369U1 (en) * 2019-02-05 2019-06-28 Общество с ограниченной ответственностью "Информационно-контрольные технологии и системы" Satellite Antenna Device

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