CN108539360A - Satellite folded form directional antenna device - Google Patents
Satellite folded form directional antenna device Download PDFInfo
- Publication number
- CN108539360A CN108539360A CN201810308764.5A CN201810308764A CN108539360A CN 108539360 A CN108539360 A CN 108539360A CN 201810308764 A CN201810308764 A CN 201810308764A CN 108539360 A CN108539360 A CN 108539360A
- Authority
- CN
- China
- Prior art keywords
- antenna
- satellite
- rotating mechanism
- antenna module
- pitch rotation
- 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
Links
Classifications
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/08—Means for collapsing antennas or parts thereof
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q3/00—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
- H01Q3/02—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole
- H01Q3/08—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole for varying two co-ordinates of the orientation
Abstract
The present invention proposes that a kind of satellite folded form directional antenna device, support base may be mounted to the installation position of satellite health；Pitch rotation mechanism connects support base, and connection orientation rotating mechanism；Orientation rotating mechanism connects antenna module；Restraint device connects antenna module, and antenna module can be constrained in not rotatable and folded against by pitch rotation mechanism and support base on orientation rotating mechanism by restraint device；When restraint device constraint relief, pitch rotation mechanism can relatively rotate, orientation rotating mechanism can relatively rotate, and the rotation of pitch rotation mechanism is axial axially perpendicular with the rotation of orientation rotating mechanism, antenna module can rotate direction in different directions by orientation rotating mechanism and pitch rotation mechanism.It is installed and used in spatial dimension in limited satellite, the installation of realization antenna simultaneously has separate celestial body reduction celestial body environment influence and two-dimensional rotary direction communication function after antenna expansion.
Description
Technical field
The present invention relates to satellite antenna technical field more particularly to a kind of high-gain narrow beams of satellite communication
Two-dimentional directional antenna.
Background technology
In certain model satellite engineering, need to develop the high-gain aerial with two-dimensional rotary function for communicating over the ground.
Since antenna installation space is very narrow, simultaneously because occlusion effect of the satellite load layout to antenna, it is desirable that antenna is in-orbit to be made
Used time need to be far as possible from celestial body mounting surface, and reducing celestial body environment as far as possible influences antenna radiation performance, while antenna needs to have
Standby two-dimensional rotary function.
Currently, the well known same type two dimension directional antenna for satellite, mostly uses expansion locking mechanism, X-Y type two dimensions
The allocation plan of mechanism high gain reflector antenna.Using above-mentioned classical scheme, disadvantage is：1) system layout is complicated, accounts for
It is more with resource, need independent a set of unfolding mechanism to realize in-orbit expansion function；Whole system includes 3 sets of independent driving machines altogether
Structure causes system reliability to reduce, of high cost；2) such as only with conventional two-dimensional mechanism scheme, then Antenna Operation position is away from satellite
Celestial body is excessively close, and antenna radiation performance is influenced by celestial body, cannot be satisfied working performance demand.
Invention content
Technical problem to be solved by the invention is to provide a kind of satellite folded form directional antenna devices, are defended limited
Star is installed and used in spatial dimension, and realizing reflector antenna installation and having separate celestial body after antenna expansion reduces celestial body environment
It influences, and has and be directed toward communication function in two-dimensional rotary.
To solve the above problems, the present invention proposes a kind of satellite folded form directional antenna device, including：Antenna module,
Support base, pitch rotation mechanism, orientation rotating mechanism and restraint device；
The support base may be mounted to the installation position of satellite health；First side of the pitch rotation mechanism connects institute
Support base is stated, the second side connects the first side of the orientation rotating mechanism；The second side of the orientation rotating mechanism connects
The antenna module；The restraint device connects antenna module, and the antenna module can constrain in institute by the restraint device
It states not rotatable and folded against by the pitch rotation mechanism and the support base on orientation rotating mechanism；It is described about
It when bundle device constraint relief, can be relatively rotated between the first side and the second side of the pitch rotation mechanism, the orientation rotation
It can be relatively rotated between first side of mechanism and the second side, and the rotation of the pitch rotation mechanism is axially rotated with the orientation
The rotation of mechanism is axially perpendicular, and the antenna module can be by the orientation rotating mechanism and the pitch rotation mechanism not
Tongfang is rotated up direction.
According to one embodiment of present invention, the plane for being installed to the installation position of the support base is as installation
When the height of reference plane, the support base and the pitch rotation mechanism makes the antenna module fold, antenna module, side
The peak of position rotating mechanism and restraint device is not higher by the peak of the pitch rotation mechanism and the support base, most
Low spot is not less than the minimum point of the pitch rotation mechanism and the support base.
According to one embodiment of present invention, further include rotation frame；The orientation rotating mechanism passes through the rotating bezel
Frame is connected in the pitch rotation mechanism, to increase the antenna module position far from satellite health upon deployment.
According to one embodiment of present invention, the restraint device is locking releasing device；Before satellite launch, the locking
The antenna module is fixed by release device；And after satellier injection, locking releasing device unlock and described in discharging
Antenna module.
According to one embodiment of present invention, the restraint device is priming system locking releasing device, is risen by priming system
It is quick-fried unlock and discharge the antenna module.
According to one embodiment of present invention, the side of the locking releasing device connects turning for the orientation rotating mechanism
Axle portion position, the other side connect the shaft position of the pitch rotation mechanism；The locking releasing device is by compressing the orientation
The shaft position of rotating mechanism and/or the shaft position of the pitch rotation mechanism and realize being fixed for both sides.
According to one embodiment of present invention, the antenna module includes reflector antenna and radio frequency feed line；The reflection
Surface antenna is used for the transmitting-receiving of antenna radio-frequency signal, and realization communicates over the ground；The radio frequency feed line is used for the reflector antenna and defends
The R-T unit of star body connects.
According to one embodiment of present invention, Installation posture of the reflector antenna on the orientation rotating mechanism,
So that its greatest irradiation beam position is axial perpendicular to the rotation of the orientation rotating mechanism.
According to one embodiment of present invention, the reflector antenna is mounted on the distal-most position after device expansion.
According to one embodiment of present invention, the maximum expansion degree of device meets the enveloping space range allowed.
After adopting the above technical scheme, the present invention has the advantages that compared with prior art：
It is mounted on satellite health using support base, it can be within the scope of the enveloping space that system allows, by antenna installation
Extreme higher position in envelope, far from satellite body, reducing celestial body environment influences；In the limited largest enveloping range that satellite allows
It is interior, add orientation rotating mechanism form to set up antenna module by using folded form pitching, reflector antenna installation is realized, in antenna
Can reduce celestial body environment far from celestial body after expansion influences, and has and is directed toward communication function in two-dimensional rotary, and can be rolled over before entering the orbit
It folds and is constrained by restraint device and fixed, to meet narrow antenna installation space.
Description of the drawings
Fig. 1 is the structural representation of the satellite folded form directional antenna folding device rounding state of one embodiment of the invention
Figure；
Fig. 2 is the Facad structure signal of the satellite folded form directional antenna device unfolded state of one embodiment of the invention
Figure；
Fig. 3 is the side structure signal of the satellite folded form directional antenna device unfolded state of one embodiment of the invention
Figure.
Description of symbols in figure：
1- antenna modules, 2- support bases, 3- pitch rotations mechanism, the orientation 4- rotating mechanism, 5- restraint devices, 6- rotations
Frame.
Specific implementation mode
In order to make the foregoing objectives, features and advantages of the present invention clearer and more comprehensible, below in conjunction with the accompanying drawings to the present invention
Specific implementation mode be described in detail.
Many details are elaborated in the following description in order to fully understand the present invention.But the present invention can be with
Much implement different from other manner described here, those skilled in the art can be without prejudice to intension of the present invention the case where
Under do similar popularization, therefore the present invention is not limited to the specific embodiments disclosed below.
Referring to Fig. 1-3, in one embodiment, satellite folded form directional antenna device may include：Antenna module 1,
Support base 2, pitch rotation mechanism 3, orientation rotating mechanism 4 and restraint device 5.
Antenna module 1 is used for realizing that radiofrequency signal transmission-receiving function, antenna structure refer to directional antenna, real through the invention
Unfolded can be realized by applying the satellite folded form directional antenna device of example.Support base 2 may be mounted to satellite health (in figure not
Show) installation position, for the datum clamp face in satellite health, in the high antenna module of the height space restocking of permission 1.
First side of pitch rotation mechanism 3 connects support base 2, and the of the second side connection orientation rotating mechanism 4 of pitch rotation mechanism 3
Side, pitch rotation mechanism 3 have a function that antenna module 1 is collapsed and is unfolded, and when transmitting can be effectively by antenna module 1
It collapses, to meet narrow antenna installation space, and antenna module 1 can be deployed into further from the position of celestial body after entering the orbit
It sets, and its rotation axis is in state free to rotate at this time, can rotate direction in the pitch direction.The of orientation rotating mechanism 4
Two sides connect the antenna module 1, and when in orientation, the rotation axis of rotating mechanism 4 is free, antenna module 1 can relatively rotate.It is described
Restraint device 5 connects antenna module 1, and restraint device 5 is constrained and entering the orbit for realizing that antenna module 1 is collapsed in launching phase
Stage unlock.
The antenna module 1 can be constrained in by the restraint device 5 on the orientation rotating mechanism 4 it is not rotatable, and
It is folded against with the support base 2 by the pitch rotation mechanism 3；When 5 constraint relief of restraint device, the pitching
It can be relatively rotated between first side of rotating mechanism 3 and the second side, between the first side and the second side of the orientation rotating mechanism 4
It can relatively rotate, and the rotation of the pitch rotation mechanism 3 is axial axially perpendicular with the rotation of the orientation rotating mechanism 4,
The antenna module 1 can rotate direction in different directions by the orientation rotating mechanism 4 and the pitch rotation mechanism 3.
Orientation rotating mechanism 4 may be implemented the rotation of antenna module 1 in the azimuth direction and be directed toward, and pitch rotation mechanism 3 can
To realize that the rotation of antenna module 1 in the pitch direction is directed toward, so that antenna module 1, which has two-dimensional rotary, is directed toward communication
Function.
It is mounted on satellite health using support base 2, it can be within the scope of the enveloping space that system allows, by antenna installation
Extreme higher position in envelope, far from satellite body, reducing celestial body environment influences；In the limited largest enveloping range that satellite allows
It is interior, add orientation rotating mechanism form to set up antenna module 1 by using folded form pitching, reflector antenna installation is realized, in day
Can reduce celestial body environment far from celestial body after line expansion influences, and has and is directed toward communication function in two-dimensional rotary, and can before entering the orbit
It folds and is constrained by restraint device 5 and fixed, to meet narrow antenna installation space.
In one embodiment, the plane for being installed to satellite health installation position of support base 2 is as datum clamp face,
When the height of support base 2 and pitch rotation mechanism 3 makes the antenna module 1 fold, antenna module 1, orientation rotating mechanism 4
And the peak of restraint device 5 is not higher by the peak of pitch rotation mechanism 3 and support base 2, antenna module 1, orientation rotation
Mechanism 4 and the minimum point of restraint device 5 are not less than the minimum point of pitch rotation mechanism 3 and support base 2.
Specifically, when antenna module 1 collapses, pitch rotation mechanism 3, which folds, to be collapsed, and 1 maximum height of antenna module is not at this time
More than 3 peak 305mm of pitch rotation mechanism.Before satellite launch, antenna module 1 is by pitch rotation mechanism 3 by antenna module 1
It folds and collapses on celestial body surface, reduce antenna total height；Pitching is turned by pitch rotation mechanism 3 and support base 2 at this time
Moving axis frame height is to the full-size requirement allowed, and antenna peak is located on pitching rotating shaft at this time, 305mm height in this way.Fig. 1
The horizontal direction of structure, by making full use of 3 lengths of frame of pitch rotation mechanism, makes day on the 400mm width dimensions of permission
Line component 1 is mounted in 400mm size ranges.The bore of the antenna structure of antenna module 1 is 350mm.To sum up, which installs
Space envelope requires to be not more than 305mm*400mm*350mm, and expansion aft antenna radiation center is not less than away from celestial body mounting surface
500mm；Antenna has two axis rotating functions；It is subject to benchmark zero degree, two axis rotational angles are not less than ± 30 °.
By using the embodiment of the present invention, realizes appearance and size when antenna folds collapse and be not more than 305mm*400mm*
350mm meets envelope requirement；After expansion as shown in Figures 2 and 3, aerial radiation centre-to-centre spacing celestial body mounting surface total height reaches 500mm；
Using state shown in Fig. 2 and 3 as antenna reference zero-bit state, antenna is not less than in azimuth direction and pitch orientation slewing area
± 30 °, meet index request.
In one embodiment, satellite folded form directional antenna device can also include rotation frame 6.The orientation turns
Motivation structure 4 is connected to by the rotation frame 6 in the pitch rotation mechanism 3, to increase the antenna module 1 upon deployment
Position far from satellite health.The rotation satisfaction of frame 6 makes device generally in the permission enveloping space in device rounding state
In range, while rotating frame 6 and having longest structure size as much as possible, it, can be by day after the expansion of satellier injection antenna module
Line component 1 is set up to away from celestial body mounting surface highest distance position.
Coordinate support base 2 using rotation frame 6, the reduced size of single unit system in a folded configuration may be implemented, and
The high height of single unit system in the deployed state.
In one embodiment, the restraint device 5 is locking releasing device.Before satellite launch, the locking release dress
It sets and is fixed the antenna module 1 so that antenna module 1 can not be rotated relative to support base 2, to which whole device locks
In a folded configuration；And after satellier injection, the locking releasing device unlocks and discharges the antenna module 1 so that realizes
Antenna module 1 rotate each joint it is rotatable, to whole device can realize expansion and can be as needed direction and adjust
Rotational angle.
Preferably, the restraint device 5 is priming system locking releasing device, by priming system detonates and unlocks described in release
Antenna module 1.Priming system locking releasing device can not only lock more secured, adapt to space environment, reliability is high, and can keep away
Exempt from complicated locking-unlocking device, referring to Fig. 3, part can be detached with device after unlocking, mitigate weight and volume.
Preferably, the side of locking releasing device connects the shaft position of the orientation rotating mechanism 4, locking releasing device
The other side connect the shaft position of the pitch rotation mechanism 3.Locking releasing device is by compressing turning for orientation rotating mechanism 4
Axle portion position and/or the shaft position of pitch rotation mechanism 3 and realize being fixed for both sides.
Locking releasing device passes through clamping shaft position so that shaft position can not rotate, moreover, because orientation rotating machine
The steering at the shaft position of structure 4 and the shaft position of pitch rotation mechanism 3 is different, thus passes through locking releasing device one
It is whole to compress two shaft positions, it can preferably limit the relative motion of the two.Locking releasing device can be only fixed
One rotary part, e.g. compresses orientation rotating mechanism, another rotary part is taken advantage of a situation and is just compacted.Locking releasing device can
It to be symmetrically positioned at the both sides at each shaft position, is compressed by way of clamping, when the corresponding shaft position quilt in one end
When being fixedly clamped, the other end is also clamped.
In one embodiment, antenna module 1 includes reflector antenna and radio frequency feed line.The reflector antenna is used for day
The transmitting-receiving of line radiofrequency signal, realization communicate over the ground.The radio frequency feed line is used for the transmitting-receiving of the reflector antenna and satellite health
Device connects.
Preferably, Installation posture of the reflector antenna on the orientation rotating mechanism 4 so that reflector antenna
Greatest irradiation beam position is axial perpendicular to the rotation of the orientation rotating mechanism 4, to which radiation signal can be most strong on being directed toward.
Preferably, the reflector antenna is mounted on the distal-most position after device expansion.
Preferably, the maximum expansion degree of satellite folded form directional antenna device meets the enveloping space range allowed.
Although the present invention is disclosed as above with preferred embodiment, it is not for limiting claim, any this field
Technical staff without departing from the spirit and scope of the present invention, can make possible variation and modification, therefore the present invention
Protection domain should be subject to the range that the claims in the present invention are defined.
Claims (10)
1. a kind of satellite folded form directional antenna device, which is characterized in that including：Antenna module, support base, pitch rotation
Mechanism, orientation rotating mechanism and restraint device；
The support base may be mounted to the installation position of satellite health；First side of the pitch rotation mechanism connects the branch
Pedestal is supportted, the second side connects the first side of the orientation rotating mechanism；Described in the second side connection of the orientation rotating mechanism
Antenna module；The restraint device connects antenna module, and the antenna module can constrain in the side by the restraint device
It is not rotatable and folded against by the pitch rotation mechanism and the support base on the rotating mechanism of position；It is described about to get one's things ready
When setting constraint relief, it can be relatively rotated between the first side and the second side of the pitch rotation mechanism, the orientation rotating mechanism
The first side and the second side between can relatively rotate, and the rotation of the pitch rotation mechanism is axial with the orientation rotating mechanism
Rotation it is axially perpendicular, the antenna module can be by the orientation rotating mechanism and the pitch rotation mechanism in not Tongfang
It is rotated up direction.
2. satellite as described in claim 1 folded form directional antenna device, which is characterized in that the installation of the support base
To the installation position plane as datum clamp face, the height of the support base and the pitch rotation mechanism makes institute
When stating antenna module folding, the peak of antenna module, orientation rotating mechanism and restraint device is not higher by the pitch rotation machine
The peak of structure and the support base, minimum point are minimum not less than the pitch rotation mechanism and the support base
Point.
3. satellite as claimed in claim 2 folded form directional antenna device, which is characterized in that further include rotation frame；Institute
It states orientation rotating mechanism to be connected in the pitch rotation mechanism by the rotation frame, opened up with increasing the antenna module
Position far from satellite health when opening.
4. satellite as described in claim 1 folded form directional antenna device, which is characterized in that the restraint device is locking
Release device；Before satellite launch, the antenna module is fixed by the locking releasing device；And after satellier injection, institute
It states locking releasing device unlock and discharges the antenna module.
5. satellite as claimed in claim 4 folded form directional antenna device, which is characterized in that the restraint device is firer
Product locking releasing device discharges the antenna module by priming system detonates and unlocks.
6. satellite as claimed in claim 4 folded form directional antenna device, which is characterized in that the locking releasing device
Side connects the shaft position of the orientation rotating mechanism, and the other side connects the shaft position of the pitch rotation mechanism；It is described
Locking releasing device is by compressing the shaft position of the orientation rotating mechanism and/or the shaft position of the pitch rotation mechanism
And realize being fixed for both sides.
7. satellite as described in claim 1 folded form directional antenna device, which is characterized in that the antenna module includes anti-
Penetrate surface antenna and radio frequency feed line；The reflector antenna is used for the transmitting-receiving of antenna radio-frequency signal, and realization communicates over the ground；The radio frequency
Feeder line is connected for the R-T unit of the reflector antenna and satellite health.
8. satellite as claimed in claim 7 folded form directional antenna device, which is characterized in that the reflector antenna is in institute
State the Installation posture on orientation rotating mechanism so that rotation of its greatest irradiation beam position perpendicular to the orientation rotating mechanism
It is axial.
9. satellite as claimed in claim 7 folded form directional antenna device, which is characterized in that the reflector antenna installation
Distal-most position after device expansion.
10. the satellite folded form directional antenna device as described in any one of claim 1-9, which is characterized in that device
Maximum expansion degree meet allow enveloping space range.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810308764.5A CN108539360B (en) | 2018-04-08 | 2018-04-08 | Folding directional antenna device for satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810308764.5A CN108539360B (en) | 2018-04-08 | 2018-04-08 | Folding directional antenna device for satellite |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108539360A true CN108539360A (en) | 2018-09-14 |
| CN108539360B CN108539360B (en) | 2020-02-18 |
Family
ID=63483384
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810308764.5A Active CN108539360B (en) | 2018-04-08 | 2018-04-08 | Folding directional antenna device for satellite |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108539360B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109326866A (en) * | 2018-11-06 | 2019-02-12 | 上海航天测控通信研究所 | A kind of two-dimentional directional antenna with initial direction-pointing function suitable for high rail satellite |
| CN110085963A (en) * | 2019-04-30 | 2019-08-02 | 西安电子科技大学 | A kind of deployable rigid reflector antenna |
| CN113013633A (en) * | 2021-02-07 | 2021-06-22 | 上海航天测控通信研究所 | Conformal design method for large-caliber reflector antenna with pointing mechanism |
| CN113137978A (en) * | 2021-05-08 | 2021-07-20 | 上海航天电子通讯设备研究所 | Two-dimensional pointing mechanism precision measurement device |
| CN114069188A (en) * | 2021-12-27 | 2022-02-18 | 浙江众星志连科技有限责任公司 | Pico-nano satellite antenna unfolding and locking device |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040227655A1 (en) * | 2003-03-05 | 2004-11-18 | King Lael D. | Semi-automatic satellite locator system |
| US20070241244A1 (en) * | 2006-04-18 | 2007-10-18 | X-Ether, Inc. | Method and apparatus for eliminating keyhole problems in an X-Y gimbal assembly |
| CN201994402U (en) * | 2011-02-24 | 2011-09-28 | 北京波尔通导科技有限公司 | Automatically folding-supporting frame |
| CN107834155A (en) * | 2017-10-30 | 2018-03-23 | 四川道勤信业科技有限公司 | One kind rotates in a circumferential direction antenna |
-
2018
- 2018-04-08 CN CN201810308764.5A patent/CN108539360B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040227655A1 (en) * | 2003-03-05 | 2004-11-18 | King Lael D. | Semi-automatic satellite locator system |
| US20070241244A1 (en) * | 2006-04-18 | 2007-10-18 | X-Ether, Inc. | Method and apparatus for eliminating keyhole problems in an X-Y gimbal assembly |
| CN201994402U (en) * | 2011-02-24 | 2011-09-28 | 北京波尔通导科技有限公司 | Automatically folding-supporting frame |
| CN107834155A (en) * | 2017-10-30 | 2018-03-23 | 四川道勤信业科技有限公司 | One kind rotates in a circumferential direction antenna |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109326866A (en) * | 2018-11-06 | 2019-02-12 | 上海航天测控通信研究所 | A kind of two-dimentional directional antenna with initial direction-pointing function suitable for high rail satellite |
| CN110085963A (en) * | 2019-04-30 | 2019-08-02 | 西安电子科技大学 | A kind of deployable rigid reflector antenna |
| CN110085963B (en) * | 2019-04-30 | 2021-01-19 | 西安电子科技大学 | Deployable rigid reflector antenna |
| CN113013633A (en) * | 2021-02-07 | 2021-06-22 | 上海航天测控通信研究所 | Conformal design method for large-caliber reflector antenna with pointing mechanism |
| CN113137978A (en) * | 2021-05-08 | 2021-07-20 | 上海航天电子通讯设备研究所 | Two-dimensional pointing mechanism precision measurement device |
| CN114069188A (en) * | 2021-12-27 | 2022-02-18 | 浙江众星志连科技有限责任公司 | Pico-nano satellite antenna unfolding and locking device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108539360B (en) | 2020-02-18 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108539360A (en) | Satellite folded form directional antenna device | |
| US10587035B2 (en) | Deployable reflector | |
| EP1987604B1 (en) | System of stowing and deploying multiple phased arrays or combinations of arrays and reflectors | |
| US20060071872A1 (en) | Ground based inflatable antenna | |
| EP3229313B1 (en) | Three axis reflector deployment and pointing mechanism | |
| CN108054515B (en) | Satellite-borne two-dimensional driving data transmission antenna system capable of realizing specific initial pointing | |
| US6448940B1 (en) | Triple reflector antenna deployment and storage systems | |
| EP2708464B1 (en) | Vertical suport system such as a retractable aircraft landing gear | |
| US5945961A (en) | Antenna dish system having constrained rotational movement | |
| JP2007501569A (en) | Phased array antenna absorber and related method | |
| WO2002025767A1 (en) | Deployment of an electronically scanned reflector | |
| CN112768952A (en) | Spaceborne cassegrain umbrella type mesh SAR antenna | |
| JP5320340B2 (en) | Phased array radar device and vehicle equipped with the same | |
| US5966104A (en) | Antenna having movable reflectors | |
| US20070008232A1 (en) | Inflatable antenna system | |
| US20040245402A1 (en) | Foldable and deployable assembly of elements mounted on board a spacecraft | |
| US8390526B1 (en) | Wide scan phased array antenna element | |
| US7683845B2 (en) | Antenna system compensating a change in radiation characteristics | |
| US7138959B2 (en) | Method for improving isolation of an antenna mounted on a structure | |
| US3699581A (en) | Large area deployable spacecraft antenna | |
| CA2612488A1 (en) | Isostatic support structure for fixed or re-orientable large size antenna reflectors | |
| CN112490616A (en) | Novel solid surface expandable antenna structure | |
| CN110085963A (en) | A kind of deployable rigid reflector antenna | |
| RU2785023C2 (en) | Deployment device | |
| CN220272725U (en) | Portable antenna |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB02 | Change of applicant information | ||
| CB02 | Change of applicant information |
Address after: 201109 Minhang District, Shanghai Road, No. 1777 spring Applicant after: Shanghai Aerospace Measurement Control Communication Institute Address before: 200080 Shanghai city Hongkou District street Xingang Tianbao Road No. 881 Applicant before: Shanghai Aerospace Measurement Control Communication Institute |
|
| GR01 | Patent grant | ||
| GR01 | Patent grant |