CN113131188A - Multi-star assembled antenna device - Google Patents
Multi-star assembled antenna device Download PDFInfo
- Publication number
- CN113131188A CN113131188A CN202110427786.5A CN202110427786A CN113131188A CN 113131188 A CN113131188 A CN 113131188A CN 202110427786 A CN202110427786 A CN 202110427786A CN 113131188 A CN113131188 A CN 113131188A
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- satellite
- antenna
- fixing structure
- module
- fixing
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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
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
- H01Q1/288—Satellite antennas
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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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- Engineering & Computer Science (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Support Of Aerials (AREA)
- Details Of Aerials (AREA)
Abstract
The invention provides a multi-satellite assembled antenna device, which comprises at least one satellite antenna module, wherein the satellite antenna module comprises an antenna module and a satellite module, the antenna module is arranged on the satellite module, and at least one group of fixed modules is arranged on the antenna module; the fixing module comprises a first fixing structure and a second fixing structure which are matched with each other, and the first fixing structure and the second fixing structure are respectively arranged at two opposite ends of the antenna module; the satellite antenna modules are moved to drive the adjacent satellite antenna modules to approach each other, and in-orbit assembly or disassembly is realized through the first fixing structure and the second fixing structure. The multi-satellite assembled antenna device breaks through the inherent mode of the satellite-borne antenna, can be assembled, and has high use value.
Description
Technical Field
The invention relates to the technical field of satellite-borne antennas, in particular to a multi-satellite assembled antenna device.
Background
The larger the aperture of the satellite-borne antenna is, the higher the antenna gain is, the size of the conventional antenna is limited due to the size of a rocket fairing, and the large-aperture antenna cannot be launched. The air environment is complex, and the antenna cannot be repaired once being damaged. The size and the shape of the conventional satellite-borne antenna cannot be changed, and the expansion of new functions cannot be realized.
Disclosure of Invention
The invention provides a multi-satellite assembled antenna device aiming at the problems in the background art, which comprises at least one satellite antenna module, wherein the satellite antenna module comprises an antenna module and a satellite module, the antenna module is arranged on the satellite module, and at least one group of fixed modules is arranged on the antenna module; the fixing module comprises a first fixing structure and a second fixing structure which are matched with each other, and the first fixing structure and the second fixing structure are respectively arranged at two opposite ends of the antenna module; the satellite antenna modules are moved to drive the adjacent satellite antenna modules to approach each other, and in-orbit assembly or disassembly is realized through the first fixing structure and the second fixing structure.
In some embodiments, the first fixing structure includes a first main body portion, and the first main body portion is provided with a fixing rail; the second fixing structure comprises a second main body part, an elastic piece is arranged on the second main body part, one end of the elastic piece is fixed on the second main body part, and a pressing wheel is arranged at the other end of the elastic piece; and the first fixing structure and the second fixing structure are connected by inserting the pinch roller into the fixing track.
In some embodiments, a side of the first fixing structure facing away from the satellite module is provided with a chute extending vertically and opened at two ends, edges of two sides of the chute are provided with extending portions extending along a width direction of the chute, the extending portions are provided with limiting plates protruding towards a bottom direction of the chute, and the limiting plates, the extending portions and side walls of the chute form a fixed track; a clamping part which is concave inwards towards one side far away from the bottom of the tank is arranged on one side of the limiting plate facing the bottom of the tank;
the other end of the elastic piece is symmetrically provided with the pinch roller left and right, and the pinch roller is circumferentially provided with a groove matched with the limiting plate; the elastic piece drives the pinch roller to be inserted into the sliding groove, the limiting plate is located in the groove, and the pinch roller moves to the clamping portion along the limiting plate to achieve locking.
In some embodiments, the side of the limiting plate facing the bottom of the groove is an arc segment with two continuous ends, and the joint of the two arc segments forms a clamping part.
In some embodiments, the slot bottom of the chute is rounded.
In some embodiments, two sets of the fixing modules are arranged in parallel on the antenna module.
Due to the adoption of the technical scheme, compared with the prior art, the invention has the following advantages and positive effects:
the multi-satellite assembled antenna device provided by the invention has the advantages that the antenna modules are respectively arranged on each satellite module, the satellite modules provide power to realize in-orbit assembly and disassembly among the satellite antenna modules, the satellite antenna modules operate in orbit as independent systems, and the multi-satellite networking function can be realized. Moreover, the satellite antenna module is assembled in a high-precision mode through the fixing module, and in-orbit assembly and operation of the large-caliber antenna can be achieved; when the antenna of the large-aperture antenna part is damaged, the satellite module is separated with the antenna module, and a new satellite antenna module is assembled in orbit to complete the replacement of the damaged antenna part; the satellite antenna module in orbit operation can be expanded and disassembled according to requirements, a new satellite antenna module is launched into orbit and assembled, the expansion of an assembled antenna can be completed, the existing antenna satellite module is disassembled, and the reduction of the assembled antenna can be completed. The multi-satellite assembled antenna device breaks through the inherent mode of the satellite-borne antenna, can be assembled, and has high use value.
Drawings
The above and other features and advantages of the present invention will be more clearly understood from the following detailed description taken in conjunction with the accompanying drawings, in which:
fig. 1 is a schematic structural diagram of a multi-satellite assembled antenna apparatus provided in the present invention;
FIG. 2 is a schematic diagram of the assembly of adjacent satellite antenna modules according to the present invention;
FIG. 3 is a schematic structural diagram of a satellite antenna module according to the present invention;
FIG. 4 is a schematic structural view of a first fixing structure according to the present invention;
FIG. 5 is a schematic structural view of a second fixing structure according to the present invention;
fig. 6 is a schematic connection diagram of the first fixing structure and the second fixing structure according to the present invention.
Detailed Description
The present invention will be described in more detail below with reference to the accompanying drawings, which illustrate embodiments of the invention. This invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. In the drawings, the size and relative sizes of hierarchical regions may be exaggerated for clarity.
It should be noted that all the directional indicators (such as up, down, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.
Referring to fig. 1-6, the invention provides a multi-satellite assembled antenna device, which comprises at least one satellite antenna module 01, wherein the satellite antenna module 01 comprises an antenna module 2 and a satellite module 1, the antenna module 2 is installed on the satellite module 1, and at least one group of fixing modules 3 is arranged on the antenna module 2; the fixing module 3 comprises a first fixing structure 301 and a second fixing structure 302 which are matched, and the first fixing structure 301 and the second fixing structure 302 are respectively arranged at two opposite ends of the antenna module 2; the satellite module 1 moves to drive the adjacent satellite antenna module 01 to approach, and the first fixing structure 301 and the second fixing structure 302 are used for realizing on-orbit assembly or disassembly.
According to the multi-satellite assembled antenna device, the antenna modules are respectively arranged on the satellite modules, the satellite modules provide power to realize in-orbit assembly and disassembly of the satellite antenna modules 01, the satellite antenna modules 01 operate in orbit as independent systems, and the multi-satellite networking function can be realized. Moreover, the satellite antenna module 01 is assembled with high precision through the fixing module, and in-orbit assembly and operation of the large-caliber antenna can be realized; when the antenna of the large-aperture antenna part is damaged, the satellite module 1 is separated with the antenna module 2, and the new sky satellite antenna module 01 is assembled in orbit to complete the replacement of the damaged antenna part; the satellite antenna module 01 in orbit can be expanded and disassembled according to requirements, a new satellite antenna module 01 is transmitted into orbit and assembled, the expansion of an assembled antenna can be completed, the existing antenna satellite module is disassembled, and the reduction of the assembled antenna can be completed. The multi-satellite assembled antenna device breaks through the inherent mode of the satellite-borne antenna, can be assembled, and has high use value.
In the embodiment, the antenna module 2 is rectangular, and the bottom of the satellite module 1 is fixed on the antenna module 2; the antenna module 1 is provided with two groups of fixing modules 3, and the two groups of fixing modules 3 are respectively arranged at two sides of the antenna module 2 in the width direction, as shown in fig. 3; of course, in other embodiments, the specific shape of the antenna module 2 may be adjusted according to specific situations, and the number of the fixing modules 3 may also be adjusted according to specific situations, which are not limited herein.
In this embodiment, the first fixing structure 301 includes a first main body 3011, and the first main body 3011 is provided with a fixing rail; the second fixing structure 302 includes a second main body 3021, an elastic member 3022 is disposed on the second main body 3021, one end of the elastic member 3022 is fixed on the second main body 3021, and a pressing wheel 3023 is disposed on the other end; the connection between the first fixing structure 301 and the second fixing structure 302 is achieved by the insertion of the pinch rollers 3023 into the fixing rails.
Further, as shown in fig. 4, a sliding slot 3012 extending vertically and having two open ends is disposed on one side of the first fixing structure 3011 facing away from the satellite module 1, extending portions 3013 extending along the slot width direction are disposed on both side edges of the sliding slot 3012, a position-limiting plate 3014 extending and protruding toward the slot bottom direction is disposed on the extending portions 3013, and the position-limiting plate 3014, the extending portions 3013 and the side walls of the sliding slot 3012 form a fixed track; a clamping part 3015 which is concave inwards towards one side far away from the bottom of the groove is arranged on one side, facing the bottom of the groove, of the limiting plate 3014; a pressing wheel 3023 is symmetrically arranged on the other end of the elastic piece 3022 left and right, and grooves matched with the limiting plates are circumferentially arranged on the pressing wheel 3023; the elastic component drives in the pinch roller 3023 inserts the spout, and limiting plate 3014 is in the recess position, and pinch roller 3023 moves to screens portion 3015 department along limiting plate 3014, and the function sticiss through elastic component 3022 elasticity in screens portion, has realized about, spacing around, to realize the locking, when needs split, exert force on vertical, make pinch roller 3023 leave screens portion 3015, and along limiting plate 3014 roll-off spout.
The limiting plate 3014 is an arc segment with two continuous ends on the side facing the bottom of the slot, the joint of the two arc segments forms the clamping portion 3015, and the bottom of the slot 3012 is arc-shaped, as shown in fig. 4, so that the pressing wheel 3023 can slide into the clamping portion 3015 quickly and smoothly.
The first fixing structure 301 and the second fixing structure 302 provided in this embodiment are simple in structure, fast and convenient to assemble and disassemble, and high in connection precision. Of course, in other embodiments, the specific structural form of the first fixing structure 301 and the second fixing structure 302 may also be adjusted according to specific situations, and is not limited herein.
It will be appreciated by those skilled in the art that the invention can be embodied in many other specific forms without departing from the spirit or scope thereof. Although embodiments of the present invention have been described, it is to be understood that the present invention should not be limited to those precise embodiments, and that various changes and modifications can be effected therein by one skilled in the art without departing from the scope or spirit of the invention as defined by the appended claims.
Claims (6)
1. The multi-satellite assembled antenna device is characterized by comprising at least one satellite antenna module, wherein the satellite antenna module comprises an antenna module and a satellite module, the antenna module is arranged on the satellite module, and at least one group of fixing modules is arranged on the antenna module; the fixing module comprises a first fixing structure and a second fixing structure which are matched with each other, and the first fixing structure and the second fixing structure are respectively arranged at two opposite ends of the antenna module; the satellite antenna modules are moved to drive the adjacent satellite antenna modules to approach each other, and in-orbit assembly or disassembly is realized through the first fixing structure and the second fixing structure.
2. The multi-satellite splicing antenna device according to claim 1, wherein the first fixing structure comprises a first main body part, and a fixing track is arranged on the first main body part; the second fixing structure comprises a second main body part, an elastic piece is arranged on the second main body part, one end of the elastic piece is fixed on the second main body part, and a pressing wheel is arranged at the other end of the elastic piece; and the first fixing structure and the second fixing structure are connected by inserting the pinch roller into the fixing track.
3. The multi-satellite assembled antenna device according to claim 2, wherein a sliding groove extending vertically and having two open ends is disposed on a side of the first fixing structure facing away from the satellite module, the edges of two sides of the sliding groove are both provided with extending portions extending along a groove width direction, the extending portions are provided with limiting plates protruding in a groove bottom direction, and the limiting plates, the extending portions and the side walls of the sliding groove form a fixed track; a clamping part which is concave inwards towards one side far away from the bottom of the tank is arranged on one side of the limiting plate facing the bottom of the tank;
the other end of the elastic piece is symmetrically provided with the pinch roller left and right, and the pinch roller is circumferentially provided with a groove matched with the limiting plate; the elastic piece drives the pinch roller to be inserted into the sliding groove, the limiting plate is located in the groove, and the pinch roller moves to the clamping portion along the limiting plate to achieve locking.
4. The multi-satellite antenna assembly of claim 3, wherein the limiting plate is a circular arc segment with two continuous ends on the side facing the bottom of the slot, and the joint of the two circular arc segments forms a clamping portion.
5. The multi-star erectable antenna assembly of claim 3, wherein the slot bottom of the chute is arc-shaped.
6. The multi-satellite erectable antenna assembly of claim 1, wherein said antenna modules are provided with two sets of said fixed modules arranged in parallel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110427786.5A CN113131188B (en) | 2021-04-20 | 2021-04-20 | Multi-star assembled antenna device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110427786.5A CN113131188B (en) | 2021-04-20 | 2021-04-20 | Multi-star assembled antenna device |
Publications (2)
| Publication Number | Publication Date |
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| CN113131188A true CN113131188A (en) | 2021-07-16 |
| CN113131188B CN113131188B (en) | 2022-07-12 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110427786.5A Active CN113131188B (en) | 2021-04-20 | 2021-04-20 | Multi-star assembled antenna device |
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Citations (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5940047A (en) * | 1998-02-25 | 1999-08-17 | Pfnister; David | Satellite antenna cover device |
| US5977922A (en) * | 1998-02-19 | 1999-11-02 | Hemmingsen, Ii; Robert J. | Satellite antenna alignment device |
| AU5181601A (en) * | 2001-06-08 | 2002-12-12 | Kuang Yi Liu | Satellite antenna rack |
| US20050107030A1 (en) * | 2003-11-19 | 2005-05-19 | Imtiaz Zafar | Integrated AM/FM/SDARS radio |
| CN201319405Y (en) * | 2008-11-07 | 2009-09-30 | 南京中网通信有限公司 | Portable fast-installation satellite antenna |
| CN201682045U (en) * | 2010-04-16 | 2010-12-22 | 西安欧赛通信科技有限公司 | Portable satellite communication antenna |
| CN101950843A (en) * | 2010-07-21 | 2011-01-19 | 北京市信息技术应用研究所 | Portable satellite antenna system and star finding method thereof |
| CN106816712A (en) * | 2015-11-30 | 2017-06-09 | 南京中网卫星通信股份有限公司 | A kind of Manual portable satellite antenna |
| CN110140443B (en) * | 2014-05-20 | 2017-06-30 | 上海宇航系统工程研究所 | A kind of satellite antenna two-dimensional pointing mechanism of splice type |
| CN207637987U (en) * | 2017-12-29 | 2018-07-20 | 新疆联星网络科技有限公司 | A kind of tool-free satellite antenna immobilizing foundation easy to install |
| CN109149058A (en) * | 2018-08-02 | 2019-01-04 | 苏州频聿精密机械有限公司 | A kind of multi-standard card connector adapeted that stability is strong |
| CN109149050A (en) * | 2018-08-01 | 2019-01-04 | 苏州频聿精密机械有限公司 | A kind of satellite antenna joint structure |
| CN109356913A (en) * | 2018-10-22 | 2019-02-19 | 北京航空航天大学 | A kind of passive docking mechanism for the in-orbit assembling of large-scale antenna space |
| CN110112574A (en) * | 2019-05-15 | 2019-08-09 | 中国电子科技集团公司第三十八研究所 | A kind of restructural ultra wide band array antenna |
| CN111092285A (en) * | 2020-01-06 | 2020-05-01 | 上海航天测控通信研究所 | Satellite-borne deployable parabolic cylinder antenna |
| CN111555032A (en) * | 2020-04-27 | 2020-08-18 | 广州市易恒信息技术有限公司 | Satellite antenna device with flat plate chassis |
| CN112531319A (en) * | 2020-11-30 | 2021-03-19 | 西北工业大学 | Construction method of multisection expansion arm of satellite-borne mesh antenna |
-
2021
- 2021-04-20 CN CN202110427786.5A patent/CN113131188B/en active Active
Patent Citations (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5977922A (en) * | 1998-02-19 | 1999-11-02 | Hemmingsen, Ii; Robert J. | Satellite antenna alignment device |
| US5940047A (en) * | 1998-02-25 | 1999-08-17 | Pfnister; David | Satellite antenna cover device |
| AU5181601A (en) * | 2001-06-08 | 2002-12-12 | Kuang Yi Liu | Satellite antenna rack |
| US20050107030A1 (en) * | 2003-11-19 | 2005-05-19 | Imtiaz Zafar | Integrated AM/FM/SDARS radio |
| CN201319405Y (en) * | 2008-11-07 | 2009-09-30 | 南京中网通信有限公司 | Portable fast-installation satellite antenna |
| CN201682045U (en) * | 2010-04-16 | 2010-12-22 | 西安欧赛通信科技有限公司 | Portable satellite communication antenna |
| CN101950843A (en) * | 2010-07-21 | 2011-01-19 | 北京市信息技术应用研究所 | Portable satellite antenna system and star finding method thereof |
| CN110140443B (en) * | 2014-05-20 | 2017-06-30 | 上海宇航系统工程研究所 | A kind of satellite antenna two-dimensional pointing mechanism of splice type |
| CN106816712A (en) * | 2015-11-30 | 2017-06-09 | 南京中网卫星通信股份有限公司 | A kind of Manual portable satellite antenna |
| CN207637987U (en) * | 2017-12-29 | 2018-07-20 | 新疆联星网络科技有限公司 | A kind of tool-free satellite antenna immobilizing foundation easy to install |
| CN109149050A (en) * | 2018-08-01 | 2019-01-04 | 苏州频聿精密机械有限公司 | A kind of satellite antenna joint structure |
| CN109149058A (en) * | 2018-08-02 | 2019-01-04 | 苏州频聿精密机械有限公司 | A kind of multi-standard card connector adapeted that stability is strong |
| CN109356913A (en) * | 2018-10-22 | 2019-02-19 | 北京航空航天大学 | A kind of passive docking mechanism for the in-orbit assembling of large-scale antenna space |
| CN110112574A (en) * | 2019-05-15 | 2019-08-09 | 中国电子科技集团公司第三十八研究所 | A kind of restructural ultra wide band array antenna |
| CN111092285A (en) * | 2020-01-06 | 2020-05-01 | 上海航天测控通信研究所 | Satellite-borne deployable parabolic cylinder antenna |
| CN111555032A (en) * | 2020-04-27 | 2020-08-18 | 广州市易恒信息技术有限公司 | Satellite antenna device with flat plate chassis |
| CN112531319A (en) * | 2020-11-30 | 2021-03-19 | 西北工业大学 | Construction method of multisection expansion arm of satellite-borne mesh antenna |
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| Publication number | Publication date |
|---|---|
| CN113131188B (en) | 2022-07-12 |
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