CN112510343A - Satellite navigation antenna assembly for testing - Google Patents
Satellite navigation antenna assembly for testing Download PDFInfo
- Publication number
- CN112510343A CN112510343A CN202011490739.7A CN202011490739A CN112510343A CN 112510343 A CN112510343 A CN 112510343A CN 202011490739 A CN202011490739 A CN 202011490739A CN 112510343 A CN112510343 A CN 112510343A
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- antenna
- satellite navigation
- shaped
- shaped support
- mounting seat
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- 238000012360 testing method Methods 0.000 title claims abstract description 46
- 238000013016 damping Methods 0.000 claims description 17
- 238000009434 installation Methods 0.000 claims description 6
- 239000000853 adhesive Substances 0.000 claims description 4
- 230000001070 adhesive effect Effects 0.000 claims description 4
- 238000003825 pressing Methods 0.000 claims description 3
- 238000010276 construction Methods 0.000 claims description 2
- 239000002184 metal Substances 0.000 description 4
- 239000007769 metal material Substances 0.000 description 3
- 238000003466 welding Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000032683 aging Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910052755 nonmetal Inorganic materials 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
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Classifications
-
- 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
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
- G01S19/23—Testing, monitoring, correcting or calibrating of receiver elements
-
- 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
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/52—Means for reducing coupling between antennas; Means for reducing coupling between an antenna and another structure
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/52—Means for reducing coupling between antennas; Means for reducing coupling between an antenna and another structure
- H01Q1/526—Electromagnetic shields
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Remote Sensing (AREA)
- General Physics & Mathematics (AREA)
- Radar, Positioning & Navigation (AREA)
- Electromagnetism (AREA)
- Astronomy & Astrophysics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Computer Networks & Wireless Communication (AREA)
- Details Of Aerials (AREA)
Abstract
The utility model provides a test is with satellite navigation antenna module, includes T shape support and satellite navigation antenna, is equipped with an antenna mount pad in the vertical portion of T shape support, and satellite navigation antenna sets up in the antenna mount pad, is connected with the strap between two wings of T shape support. The vertical portion and the two wings of the T-shaped support are of frame structures, the antenna mounting seat is box-shaped and is fixedly mounted with the vertical portion of the T-shaped support, a concave cavity is arranged on one side, away from the T-shaped support, of the antenna mounting seat, and the satellite navigation antenna is arranged in the cavity. When in use, the invention can be attached to the surface of a product, and can effectively save space, so that the invention can be used for testing under the condition of limited space such as a test box. The wave-absorbing plate adhered to the shielding base and the antenna mounting base can be tightly attached to a receiving window of a missile product, and the mutual influence of clutter signals and test signals in a test environment is reduced.
Description
Technical Field
The invention relates to the technical field of antenna manufacturing, in particular to a satellite navigation antenna assembly for testing.
Background
In the prior art, when an antenna is required to be used for testing the satellite navigation function of a missile product, the antenna is usually suspended above the missile product by using a tripod, and then the antenna is adjusted to a proper height and angle by combining the tripod to test the missile product. Because the existing testing process needs a tripod for assistance, the prior preparation work is needed; in addition, the product receiving antenna is easy to be interfered by clutter signals when transmitting a signal test; in addition, in the prior art, the antenna for testing needs to be suspended at a high position, so that the antenna is inconvenient to test and position with missile products, and is not suitable for test scenes with limited space, such as test boxes and the like.
Disclosure of Invention
The invention aims to provide a satellite navigation antenna assembly for testing.
In order to achieve the purpose, the invention adopts the technical scheme that: a satellite navigation antenna assembly for testing comprises a T-shaped support and a satellite navigation antenna, wherein an antenna mounting seat is arranged at the vertical part of the T-shaped support, the satellite navigation antenna is arranged in the antenna mounting seat, and a strap for fixing the T-shaped support on the surface of a missile is connected between two cross wings of the T-shaped support.
Further, the vertical portion and two wings of T shape support are frame construction, and two wings are the same angle with vertical portion and set up towards vertical portion homonymy slope, the antenna mount pad be the box-type and pass through screw fixed mounting with the vertical portion of T shape support, one side that the T shape support was kept away from to the antenna mount pad is equipped with a sunken cavity, satellite navigation antenna sets up in the cavity.
Furthermore, an antenna connecting seat is arranged in the cavity and comprises an antenna connecting plate fixedly connected with an antenna mounting seat, an antenna placing chamber is formed on the antenna connecting plate in an enclosing mode through four vertical plates, the satellite navigation antenna is arranged in the antenna placing chamber, adhesive is filled and sealed between the satellite navigation antenna and the antenna placing chamber, a notch for leading out a radio frequency line from the antenna is formed in one of the vertical plates, and a strip-shaped groove for placing the radio frequency line is correspondingly formed in the antenna mounting seat.
Furthermore, a shielding seat is arranged on one side of the vertical part of the T-shaped support close to the tail end of the vertical part and one side of the T-shaped support, which is located on the antenna mounting seat, wave-absorbing rubber plates are adhered to the surface of the shielding seat, the surface of the antenna mounting seat and the side wall of the cavity, the surfaces of the wave-absorbing rubber plates on the surface of the shielding seat and the surface of the antenna mounting seat are parts of the same arc-shaped surface, and the same arc-shaped surface can be attached to the surface of a measured object.
Furthermore, one side of the antenna mounting seat, which is provided with the cavity, is in a groove shape with the bottom being an arc surface, one part of the wave-absorbing rubber plate arranged at the position in the thickness direction is arranged in the groove, and the other part of the wave-absorbing rubber plate is exposed out of the groove.
Further, be equipped with positioner on the upper portion of T shape support, positioner include two fixed blocks with T shape support fixed connection, two fixed block intervals set up, extend towards the other side respectively in two relative one sides of fixed block and be equipped with a damping pivot, be equipped with a locating plate with two damping pivot fixed connection, be equipped with a radius and be greater than the radial 90 arc constant head tank in shaft hole with the tip in the shaft hole of damping pivot cooperation installation on the fixed block, 90 arc constant head tank and shaft hole are concentric, are equipped with the location arch of installing with 90 arc constant head tank cooperation on the locating plate, and the locating plate is through pivot mounting hole and damping pivot cooperation installation and through fastening screw and damping pivot fixed connection.
Furthermore, a cover plate is arranged at the position except the position where the antenna mounting seat and the shielding seat are arranged on one side of the T-shaped support where the antenna mounting seat is arranged.
Furthermore, an N/SMA adapter used as a satellite signal input interface is arranged on the side wall of the vertical part of the T-shaped bracket near the tail end.
Furthermore, one end of the strap is fixed at one wing end of the T-shaped support through the pressing plate, and the other end of the strap is connected with the other wing end of the T-shaped support through the lock catch.
Furthermore, a groove part for holding is arranged on the T-shaped support.
Has the advantages that:
the invention adopts the trapezoidal bracket, is light and simple, has quick operation and high reliability, and can greatly improve the test efficiency.
When in test use, the invention can be attached to the surface of a missile product, thereby not only being convenient for positioning on the surface of the missile product, but also effectively saving space, and being capable of carrying out test use under the condition of limited space such as a test box. The wave-absorbing rubber plate adhered to the shielding seat and the antenna mounting seat can be tightly attached to a receiving window of a missile product, so that the mutual influence of clutter signals and test signals in a test environment is reduced, and the electromagnetic compatibility is higher.
Drawings
Fig. 1 is a schematic perspective view of the present invention.
Fig. 2 is a rotated view of fig. 1.
Fig. 3 is a schematic structural diagram of an antenna mounting base.
Fig. 4 is an exploded view of the antenna mount.
Fig. 5 is a schematic view of an antenna connection base.
Fig. 6 is a schematic structural view of the shield seat.
Fig. 7 is a schematic structural diagram of the positioning device.
Fig. 8 is an exploded view of the positioning device.
The labels in the figure are: 1. t-shaped support, 101, the vertical portion of T-shaped support, 101a, the concave part, 102, the horizontal wing, 2, positioner, 201, the fixed block, 201a, the apron mounting hole, 202, the damping pivot, 203, the locating plate, 203a, the pivot mounting hole, 3, the shielding seat, 4, the apron, 401, the breach, 5, the antenna mount pad, 501, the cavity, 502, the lug, 503, the recess, 504, the bar groove, 6, N/SMA adapter seat, 7, satellite navigation antenna, 8, the clamp plate, 9, the strap, 10, the hasp, 11, inhale ripples rubber slab, 12, the antenna connecting seat, 1201, the antenna connecting plate, 1202, riser, 1203, the antenna settling chamber, 13, the radio frequency line.
Detailed Description
The present invention will be described in further detail with reference to the following drawings and examples, but the invention is not limited thereto.
As shown in fig. 1-2, the satellite navigation antenna assembly for the test comprises a T-shaped support 1 and a satellite navigation antenna 7, wherein an antenna mounting seat 5 is arranged on a vertical part 101 of the T-shaped support, the satellite navigation antenna 7 is arranged in the antenna mounting seat 5, and a strap 9 for fixing the T-shaped support on the surface of a missile is connected between two wings 102 of the T-shaped support. One end of the strap 9 is fixed at one cross wing end of the T-shaped support through the pressing plate 8 by using a screw, the other end of the strap 9 is connected with the other cross wing end of the T-shaped support through the lock catch 10, the lock catch structure can adopt the prior art, for example, a metal lock catch locked by passing a dead point can be adopted, the locking is reliable, certain pre-tightening force is provided, the antenna assembly can be tightly attached to a test product (for example, a missile), and leakage is reduced. The strap is made of a non-metal material with good temperature stability, and can adapt to long-time use under high and low temperature test conditions without aging. The strap 9 can realize the rapid installation and fixation between the invention and the product to be tested.
In this embodiment, the vertical portion 101 and the two wings 102 of the T-shaped bracket are both rectangular frame structures, and the two wings 102 and the vertical portion are inclined at the same angle toward the same side of the vertical portion 101.
The vertical part 101 and the two wings 102 of the T-shaped bracket may be formed by welding metal plates or profiles, for example, by welding an angle of a square profile inwards to form a rectangular frame, or by welding metal plates to form a rectangular box-shaped frame structure. The antenna mounting base 5 is box-shaped, as shown in fig. 3. The antenna mounting seat 5 is fixedly mounted with the vertical part 101 of the T-shaped support through screw mounting holes 502a arranged on the four lugs 502 through screws, a concave cavity 501 is arranged on one side, away from the T-shaped support, of the antenna mounting seat 5, and the satellite navigation antenna 7 is arranged in the cavity 501.
Preferably, an antenna connecting base 12 is disposed in the cavity 501, the antenna connecting base 12 includes an antenna connecting plate 1201 fixedly connected to the antenna mounting base 5, an antenna placing chamber 1203 is defined on the antenna connecting plate 1201 by four vertical plates 1202, the satellite navigation antenna 7 is disposed in the antenna placing chamber 1203, an adhesive is filled between the satellite navigation antenna 7 and the antenna placing chamber 1203 to adhere the satellite navigation antenna 7 and the antenna mounting chamber together, a notch for extending a radio frequency line 13 led out from the antenna is disposed on one of the vertical plates 1202 and a corresponding position of the antenna connecting plate 1201, and a strip-shaped groove 504 for placing the radio frequency line is correspondingly disposed on the antenna mounting base 5.
The antenna connection base 12 (which may also be referred to as a filling base because it is connected to the antenna by adhesive filling) is made of a non-metallic material.
The position that is close to the tail end at vertical portion 101 of T shape support and two wings 102 of T shape support are located one side of installation antenna mount pad 5 and all are provided with shielding seat 3, all paste on shielding seat 3 surface and antenna mount pad 5 surface and the cavity 501 lateral wall and inhale ripples rubber slab 11, and the ripples rubber slab surface homonymy of shielding seat surface and antenna mount pad surface is partly of same arcwall face, and same arcwall face can laminate mutually with the measured object surface. In this embodiment, the arc-shaped surface matches with the surface arc of the missile to be tested, and can be attached to the surface of the missile.
The shielding seat 3 can be made of common metal materials, plays a role in shielding related signals after the wave-absorbing rubber plate 11 is adhered to the surface, and is in flexible contact with the surface of the missile, so that the missile is prevented from being scratched.
One side of the antenna mounting seat 5, which is provided with the cavity, is in a groove shape with a cambered surface at the bottom, one part of the wave-absorbing rubber plate arranged at the position in the thickness direction is arranged in the groove 503, and the other part is exposed out of the groove. The same structure can be adopted on one side of the wave-absorbing rubber plate 11 adhered to the shielding seat.
The side wall of the T-shaped bracket is provided with a groove part 101a which is convenient for holding by hand, and the groove part 101a can be formed by adopting a mode that the metal plate is folded inwards.
As shown in fig. 1, 2 and 5, a positioning device 2 is arranged on the upper portion of the T-shaped support 1, the positioning device 2 includes two fixing blocks 201 fixedly connected with the vertical portion 101 of the T-shaped support, the two fixing blocks 201 are arranged at intervals, one sides of the two fixing blocks 201 opposite to each other extend towards each other to form a damping rotating shaft 202, a positioning plate 203 is connected with the two damping rotating shafts 202, and the positioning plate 203 rotates around the damping rotating shafts by 90 degrees to a working position and is consistent with the length direction of the vertical portion 101 of the T-shaped support.
Specifically, a 90 ° arc-shaped positioning groove 201b having a radius larger than that of the shaft hole is provided at the end of the shaft hole, which is fitted to the damping rotating shaft 202, of the fixing block 201. The 90-degree arc-shaped positioning groove positioning protrusion 203b is concentric with the shaft hole, and the positioning protrusion 203b which is matched with the 90-degree arc-shaped positioning groove 201b is arranged on the positioning plate 203. The positioning plate 203 is fittingly installed with the damping rotation shaft 202 through the rotation shaft installation hole 203a and fixedly connected with the damping rotation shaft 202 through the fastening screw 14. The matching structure of the 90-degree arc-shaped positioning groove 201b and the positioning protrusion 203b enables the positioning plate 203 to realize the positioning in the vertical direction (the vertical direction of the vertical part of the T-shaped support 1) and the horizontal direction (the position which is parallel to the top end of the T-shaped support 1).
A cover plate 4 is arranged at the position except the position where the antenna mounting seat 5 and the shielding seat 4 are arranged on one side of the T-shaped support 1 where the antenna mounting seat 5 is arranged. The cover plate 4 is fixed and connected by screws through the cover plate mounting holes 201a arranged on the fixing blocks 201, and a notch 401 convenient for operating the positioning plate 203 is arranged on the cover plate 4 corresponding to the retraction position of the positioning plate, which is positioned at the upper part of the vertical part 101 of the T-shaped bracket and corresponds to the positioning device.
An N/SMA adapter 6 used as a satellite signal input interface is arranged on the side wall of the vertical part 101 of the T-shaped bracket near the tail end.
In order to better fit with the product to be tested, the vertical part 101 and the two wings of the T-shaped bracket are made into an arc shape which is consistent with the surface of the product.
When the device is used, the antenna mounting seat 5 and the wave-absorbing rubber plate 11 on the surface of the shielding seat 3 are tightly attached to the receiving window of a missile product, so that the influence of surrounding clutter on a test can be reduced, and the radiation influence of the satellite navigation antenna 7 on the surrounding space can be reduced.
When the positioning plate 203 in the positioning device 2 is installed with a missile product, the positioning plate is firstly screwed out of the T-shaped support 1, an angle of 90 degrees is formed between the positioning plate and the top end of the T-shaped support 1, the top end of the positioning plate touches an axial positioning reference arranged on a test object to realize axial positioning, a vertical linear groove is carved in the center of the positioning plate, and the positioning plate can be aligned with a central line of a circumferential positioning reference arranged on the upper surface of the missile, so that the (circumferential) angle positioning on the surface of the missile is realized. After the missile function test is completed, the invention is taken down from the missile product, and the positioning plate 203 is retracted to be flush with the top end of the T-shaped bracket after being rotated by 90 degrees. The storage and placement of the invention are not affected.
The invention has the advantages of light and simple structure, quick operation and high reliability, and can greatly improve the test efficiency. When in test use, the invention can be attached to the surface of a missile product, thereby effectively saving space and being capable of being used for testing under the condition of limited space such as a test box. The wave-absorbing rubber plate 11 adhered to the shielding base 3 and the antenna mounting base 5 can be tightly attached to a receiving window of a missile product, so that the mutual influence of clutter signals and test signals in a test environment is reduced, and higher electromagnetic compatibility is achieved.
The above embodiments are only intended to illustrate the technical solution of the present invention and not to limit the same, and it should be understood by those of ordinary skill in the art that the specific embodiments of the present invention can be modified or substituted with equivalents with reference to the above embodiments, and any modifications or equivalents without departing from the spirit and scope of the present invention are within the scope of the claims to be appended.
Claims (10)
1. A test satellite navigation antenna assembly, comprising: the missile antenna fixing device comprises a T-shaped support (1) and a satellite navigation antenna (7), wherein an antenna mounting seat (5) is arranged at a vertical part (101) of the T-shaped support, the satellite navigation antenna (7) is arranged in the antenna mounting seat (5), and a strap (9) for fixing the T-shaped support on the surface of a missile is connected between two cross wings of the T-shaped support.
2. The test satellite navigation antenna assembly of claim 1, wherein: vertical portion (101) and two wings (102) of T shape support are frame construction, and two wings (102) are the same angle with vertical portion and set up towards vertical portion (101) homonymy slope, antenna mount pad (5) be the box-type and pass through screw fixed mounting with vertical portion (101) of T shape support, one side that T shape support was kept away from in antenna mount pad (5) is equipped with a sunken cavity (501), satellite navigation antenna (7) set up in cavity (501).
3. The test satellite navigation antenna assembly of claim 2, wherein: be equipped with an antenna connecting seat (12) in cavity (501), antenna connecting seat (12) including one be used for with antenna mount pad (5) fixed connection's antenna connecting plate (1201), it has an antenna to lay room (1203) to enclose through four riser (1202) on antenna connecting plate (1201), satellite navigation antenna (7) set up in antenna laying room (1203), the embedment has the adhesive between satellite navigation antenna (7) and antenna laying room (1203), be provided with the breach that supplies to stretch out from radio frequency line (13) that the antenna was drawn forth on one of them riser (1202), it supplies strip-shaped groove (504) that the radio frequency line was placed to correspond to be equipped with on antenna mount pad (5).
4. The test satellite navigation antenna assembly of claim 2, wherein: the antenna structure is characterized in that a shielding seat (3) is arranged on one side of the vertical part of the T-shaped support close to the tail end of the vertical part and one side of two cross wings (102) of the T-shaped support located on an antenna mounting seat, wave-absorbing rubber plates (11) are adhered to the surface of the shielding seat (3), the surface of the antenna mounting seat (5) and the side wall of the cavity (501), the surfaces of the wave-absorbing rubber plates on the surface of the shielding seat and the surface of the antenna mounting seat are parts of the same arc-shaped surface, and the same arc-shaped surface can be attached to the surface of a measured object.
5. The test satellite navigation antenna assembly of claim 3, wherein: one side of the antenna mounting seat (5) provided with the cavity is in a groove shape with the bottom being a cambered surface, one part of the wave-absorbing rubber plate arranged at the position in the thickness direction is arranged in the groove, and the other part of the wave-absorbing rubber plate is exposed out of the groove.
6. The test satellite navigation antenna assembly of claim 3, wherein: the upper part of the T-shaped bracket is provided with a positioning device (2), the positioning device (2) comprises two fixing blocks (201) fixedly connected with the T-shaped bracket, the two fixing blocks are arranged at intervals, one side of the two fixed blocks opposite to each other is respectively provided with a damping rotating shaft (202) extending towards each other, a positioning plate (203) is fixedly connected with the two damping rotating shafts, a 90-degree arc positioning groove (201 b) with the radius larger than that of the shaft hole is arranged at the end part of the shaft hole which is arranged on the fixing block and matched with the damping rotating shafts, the 90-degree arc positioning groove is concentric with the shaft hole, the positioning plate (203) is provided with a positioning bulge (203 b) which is matched and installed with the 90-degree arc-shaped positioning groove (201 b), and the positioning plate (203) is matched and installed with the damping rotating shaft (202) through a rotating shaft installation hole (203 a) and is fixedly connected with the damping rotating shaft (202) through a fastening screw (14).
7. The test satellite navigation antenna assembly of claim 4, wherein: a cover plate (4) is arranged at one side of the T-shaped support (1) where the antenna mounting seat (5) is arranged, except the positions where the antenna mounting seat (5) and the shielding seat (3) are arranged.
8. The test satellite navigation antenna assembly of claim 3, wherein: an N/SMA adapter (6) used as a satellite signal input interface is arranged on the side wall of the vertical part (101) of the T-shaped bracket and close to the tail end.
9. The test satellite navigation antenna assembly of claim 1, wherein: one end of the strap (9) is fixed at one wing end of the T-shaped support through the pressing plate (8), and the other end of the strap (9) is connected with the other wing end of the T-shaped support through a lock catch.
10. The test satellite navigation antenna assembly of claim 1, wherein: the T-shaped bracket is provided with a groove part (101 a) for holding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011490739.7A CN112510343A (en) | 2020-12-16 | 2020-12-16 | Satellite navigation antenna assembly for testing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011490739.7A CN112510343A (en) | 2020-12-16 | 2020-12-16 | Satellite navigation antenna assembly for testing |
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| Publication Number | Publication Date |
|---|---|
| CN112510343A true CN112510343A (en) | 2021-03-16 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011490739.7A Pending CN112510343A (en) | 2020-12-16 | 2020-12-16 | Satellite navigation antenna assembly for testing |
Country Status (1)
| Country | Link |
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| CN (1) | CN112510343A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1772742A1 (en) * | 2005-10-10 | 2007-04-11 | The Boeing Company | Correction of the distance between phase centres of two directional antenneas of a navigational satellite |
| CN110265779A (en) * | 2019-07-23 | 2019-09-20 | 福州大学 | A kind of high low elevation gain satellite navigation terminal antennae of diesis shape broadband |
| CN111077762A (en) * | 2018-10-22 | 2020-04-28 | 张建城 | Beidou multimode time service receiving device |
| CN214203938U (en) * | 2020-12-16 | 2021-09-14 | 凯迈（洛阳）测控有限公司 | Satellite navigation antenna assembly for testing |
-
2020
- 2020-12-16 CN CN202011490739.7A patent/CN112510343A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1772742A1 (en) * | 2005-10-10 | 2007-04-11 | The Boeing Company | Correction of the distance between phase centres of two directional antenneas of a navigational satellite |
| CN111077762A (en) * | 2018-10-22 | 2020-04-28 | 张建城 | Beidou multimode time service receiving device |
| CN110265779A (en) * | 2019-07-23 | 2019-09-20 | 福州大学 | A kind of high low elevation gain satellite navigation terminal antennae of diesis shape broadband |
| CN214203938U (en) * | 2020-12-16 | 2021-09-14 | 凯迈（洛阳）测控有限公司 | Satellite navigation antenna assembly for testing |
Non-Patent Citations (1)
| Title |
|---|
| 褚瑞等: ""基于锥形微波暗室的北斗导航天线测试系统"", 《环境技术》, vol. 36, no. 4, 31 August 2018 (2018-08-31), pages 103 - 107 * |
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