CN107240764A - The directing mechanism that a kind of spaceborne Complex Radar antenna high rigidity offset is fixed - Google Patents
The directing mechanism that a kind of spaceborne Complex Radar antenna high rigidity offset is fixed Download PDFInfo
- Publication number
- CN107240764A CN107240764A CN201710362307.XA CN201710362307A CN107240764A CN 107240764 A CN107240764 A CN 107240764A CN 201710362307 A CN201710362307 A CN 201710362307A CN 107240764 A CN107240764 A CN 107240764A
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- China
- Prior art keywords
- fixed
- radar antenna
- spaceborne
- headgear
- compression
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Classifications
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q3/00—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
- H01Q3/02—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole
-
- 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
Abstract
The invention discloses the directing mechanism that a kind of spaceborne Complex Radar antenna high rigidity offset is fixed, the mechanism includes：Active expansion locking mechanism, extending arm, two dimensional servomechanism, compression relieving mechanism and floating bracket；Compressing relieving mechanism includes：Pressed glass, support component, compressor arm, compression headgear, vibration damping headgear；The present invention installs fixed and in-orbit positioned to target following for spaceborne Complex Radar antenna and provides a kind of effective solution, has the advantages that envelope size is small, the rigidity of structure is big and easy for installation.
Description
Technical field
The present invention relates to Aero-Space field of electromechanical technology, more particularly to a kind of spaceborne Complex Radar antenna high rigidity biasing
The directing mechanism that formula is fixed.
Technical background
One of core component of antenna directing mechanism formula radar system, is that radar antenna is tracked orientation to target and held
Row mechanism.As modern spacecraft carries the continuous expansion of radar function, radar antenna is sent out by the plate aerial less than half meter of bore
The parabola antenna of the bore more than 2 meters is opened up, structure also complicates development, and the mechanical environment that transmitter section is born is more severe.
Therefore, radar antenna is pressed on satellite side in the gathering of satellite launch stage and meets envelope and mechanical condition requirement, is lifted after entering the orbit
It is raised to the position away from satellite side plate and is tracked positioning to target again.
With the complication being continuously increased with the structure development of radar antenna bore, radar antenna is installed after traditional sensing machine
There is envelope size big, transmitter section vibratory response is big, compress installation difficulty, the problems such as installation period is long, it is impossible to meet modern boat
The growth requirement of its device.It is badly in need of the directing mechanism that a kind of envelope size of design is small, rigidity is high and is easily installed.
The content of the invention
In order to solve the above problems, the invention provides the finger that a kind of spaceborne Complex Radar antenna high rigidity offset is fixed
To mechanism, including：Active expansion locking mechanism, extending arm, two dimensional servomechanism, compression relieving mechanism and floating bracket；It is described
The active expansion locking mechanism turning end of extending arm one end connection, other end connection two dimensional servomechanism base；Active expansion locking
Mechanism is fixedly installed on satellite side plate, and the two dimensional servomechanism other end is fixed on the radar antenna back side；Compress relieving mechanism peace
Loaded on extending arm one end and with the centrosymmetric surrounding of radar antenna；Described floating bracket one end is fixed on two dimensional servomechanism
In support frame, other end float support driving joint cantilever end.
Further, the compression relieving mechanism includes：Pressed glass, support component, compressor arm, compression headgear, vibration damping headgear；
The pressed glass is fixed on antenna installation foot, and hold-down head wore the mounting hole of pressed glass, was fixed in pressed glass, support group
Part is fixed on satellite mounting surface, and compressor arm is screwed into support component screwed hole through headgear is compressed, by radar antenna and its sensing
Mechanism is fixed on satellite mounting surface, and damping headgear is secured transverse on compression headgear lug.
Further, the handle hole of the pressed glass side is towards on the outside of radar antenna.
Further, carbon fiber reinforcement is glued between the radar antenna back side is respectively compressed a little and improves antenna body rigidity and each
The coupling stiffness between point is compressed, radar antenna flange is offset to antenna side, and flange is located between two compression points of its both sides
On pre-buried rigid beam, two dimensional servomechanism is fixed on the flange.
Further, the floating bracket is half open type support.
The present invention uses above technical scheme, is allowed to compared with prior art, with advantages below：
1) connection between directing mechanism and radar antenna is installed using offset, is reduced radar antenna and is installed in satellite
The setting height(from bottom) in face, reduces the envelope size of radar system, improves the rigidity of radar system.
2) driving joint cantilever end is supported in the support frame of two dimensional servomechanism using between the floating of half opening formula, is carried
The integral rigidity of high two dimensional servomechanism, reduces satellite launch section driving Joint mechanics response, improves directing mechanism power
Learn ability to bear.
3) damping headgear is secured transverse on compression headgear lug, and which is easy to the dismounting of damping headgear.
4) two dimensional servomechanism is vacantly arranged on the rigid beam between its two side compressions point, and this two compress point not only again
For two dimensional servomechanism and radar antenna, compression is counted out less and easy for installation.
Brief description of the drawings
Fig. 1 is a kind of peace of the directing mechanism of spaceborne Complex Radar antenna high rigidity offset fixation of the present invention on satellite
Fill schematic diagram；
Fig. 2 is the structural representation for the directing mechanism that a kind of spaceborne Complex Radar antenna high rigidity offset of the present invention is fixed
Figure；
Fig. 3 is two dimensional servomechanism and floating bracket scheme of installation；
Fig. 4 is to compress relieving mechanism composition schematic diagram；
Fig. 5 is to compress relieving mechanism sectional view；
Fig. 6 is radar antenna schematic diagram.
Embodiment
The present invention is described in detail below in conjunction with the accompanying drawings：Illustrate：
1-active expansion locking mechanism, 2-extending arm, 3-two dimensional servomechanism, 4-compress relieving mechanism, 5-floating
Support, 6-satellite installing plate, 7-radar antenna, 301-driving joint, 401-pressed glass, 402-support component, 403-
Compressor arm, 404-compression headgear, 405-vibration damping headgear, 701-carbon fiber reinforcement, 702-rigid beam, 703-antenna
Flange
The present invention provides the directing mechanism that a kind of spaceborne Complex Radar antenna high rigidity offset is fixed, it is characterised in that
The mechanism includes：Active expansion locking mechanism 1, extending arm 2, two dimensional servomechanism 3, compression relieving mechanism 4 and floating bracket 5；
Compressing relieving mechanism 4 includes：Pressed glass 401, support component 402, compressor arm 403, compression headgear 404, vibration damping headgear 405.
The one end of extending arm 2 is screwed in the active expansion turning end of locking mechanism 1, and the other end is screwed in two dimension
The base of servo control mechanism 3, it is fixed by seam between extending arm 2 and active expansion locking mechanism 1 turning end, the base of two dimensional servomechanism 1
Position；Active expansion locking mechanism 1, which is screwed, to be installed on satellite side plate；The other end of two dimensional servomechanism 3 is screwed
At the radar antenna back side, positioned with pin；Compress relieving mechanism 4 and be installed on the one end of extending arm 2 and with the Central Symmetry of radar antenna 7
Surrounding.
Pressed glass 403 is screwed on the installation foot of antenna surrounding, and hold-down head wore the peace of pressed glass, extending arm
Hole is filled, is fixed in pressed glass 401；Support component is screwed on satellite mounting surface, and compressor arm 403, which is passed through, compresses headgear
404 are screwed into the screwed hole of support component 402, and radar antenna 7 and its directing mechanism are fixed on satellite side plate.
Four of the surrounding of radar antenna 7 compression points, the handle hole of the side of pressed glass 401 is towards the outside of radar antenna 7, damping
Headgear 405 is secured transverse on the compression lug of headgear 404, is screwed.
It is glued carbon fiber reinforcement 701 between each compression point and improves antenna body rigidity and each compression in the back side of radar antenna 7
Coupling stiffness between point, radar antenna flange 703 is offset to antenna side, and antenna flange 703 is located at two compressions of its both sides
Between point on pre-buried rigid beam 702, two dimensional servomechanism 3 is fixed on the flange.
Floating bracket 5 is half open type support, and one end is fixed in the support frame of two dimensional servomechanism 3, the other end
Float support is fixed in the driving cantilever end of joint 301 by screw.
Claims (5)
1. the directing mechanism that a kind of spaceborne Complex Radar antenna high rigidity offset is fixed, it is characterised in that the mechanism includes：Have
Source expansion locking mechanism, extending arm, two dimensional servomechanism, compression relieving mechanism and floating bracket；Extending arm one end connection
Active expansion locking mechanism turning end, other end connection two dimensional servomechanism base；Active expansion locking mechanism is fixedly installed in
On satellite side plate, the two dimensional servomechanism other end is fixed on the radar antenna back side；Compress relieving mechanism and be installed on extending arm one end
With with the centrosymmetric surrounding of radar antenna；Described floating bracket one end is fixed in the support frame of two dimensional servomechanism, separately
One end float support driving joint cantilever end.
2. the directing mechanism that a kind of spaceborne Complex Radar antenna high rigidity offset as claimed in claim 1 is fixed, its feature
It is, the compression relieving mechanism includes：Pressed glass, support component, compressor arm, compression headgear, vibration damping headgear；
The pressed glass is fixed on antenna installation foot, and hold-down head wore the mounting hole of pressed glass, was fixed in pressed glass, branch
Support component is fixed on satellite mounting surface, and compressor arm is screwed into support component screwed hole through headgear is compressed, by radar antenna and its
Directing mechanism is fixed on satellite mounting surface, and damping headgear is secured transverse on compression headgear lug.
3. the directing mechanism that a kind of spaceborne Complex Radar antenna high rigidity offset as claimed in claim 2 is fixed, its feature
It is, the handle hole of the pressed glass side is towards on the outside of radar antenna.
4. the directing mechanism that a kind of spaceborne Complex Radar antenna high rigidity offset as claimed in claim 1 is fixed, its feature
It is, the radar antenna back side is glued carbon fiber reinforcement and improved between antenna body rigidity and each compression point between respectively compressing a little
Coupling stiffness, radar antenna flange is offset to antenna side, flange rigidity pre-buried between two compression points of its both sides
On crossbeam, two dimensional servomechanism is fixed on the flange.
5. the directing mechanism that a kind of spaceborne Complex Radar antenna high rigidity offset as claimed in claim 1 is fixed, its feature
It is, the floating bracket is half open type support.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710362307.XA CN107240764B (en) | 2017-05-22 | 2017-05-22 | High-rigidity offset type fixed pointing mechanism of satellite-borne complex radar antenna |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710362307.XA CN107240764B (en) | 2017-05-22 | 2017-05-22 | High-rigidity offset type fixed pointing mechanism of satellite-borne complex radar antenna |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107240764A true CN107240764A (en) | 2017-10-10 |
| CN107240764B CN107240764B (en) | 2020-08-28 |
Family
ID=59985657
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710362307.XA Active CN107240764B (en) | 2017-05-22 | 2017-05-22 | High-rigidity offset type fixed pointing mechanism of satellite-borne complex radar antenna |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107240764B (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108054515A (en) * | 2017-10-27 | 2018-05-18 | 上海卫星工程研究所 | The specific spaceborne two-dimentional driving number being initially directed toward can be achieved and pass antenna system |
| CN108054512A (en) * | 2017-12-08 | 2018-05-18 | 上海宇航系统工程研究所 | A kind of high-torque anti-interference antenna directing mechanism for survey of deep space |
| CN108183305A (en) * | 2018-01-25 | 2018-06-19 | 哈尔滨工业大学 | The method of adjustment of satellite antenna space mast end position and attitude error |
| CN109552672A (en) * | 2018-11-12 | 2019-04-02 | 上海宇航系统工程研究所 | A kind of hard limit adjustable position-limit mechanism of angle |
| CN109616741A (en) * | 2018-11-15 | 2019-04-12 | 上海宇航系统工程研究所 | Active matrix driving two-dimensional development formula antenna |
| CN111193095A (en) * | 2020-01-06 | 2020-05-22 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Deployable mechanism of satellite-borne antenna |
| CN112623280A (en) * | 2021-01-04 | 2021-04-09 | 上海宇航系统工程研究所 | Two-degree-of-freedom solar cell array unfolding device |
| CN113753270A (en) * | 2021-09-13 | 2021-12-07 | 北京空间飞行器总体设计部 | Wide-temperature-range high-rigidity statically determinate type pressing system |
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| CN105659914B (en) * | 2008-05-06 | 2012-08-29 | 北京空间飞行器总体设计部 | A kind of satellite antenna compresses relieving mechanism |
| US20140174214A1 (en) * | 2011-12-23 | 2014-06-26 | Richard O. HORTH | Antenna pointing system |
| CN204029989U (en) * | 2013-11-27 | 2014-12-17 | 上海宇航系统工程研究所 | A kind of integrated general satellite antenna directing mechanism driven unit |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105659914B (en) * | 2008-05-06 | 2012-08-29 | 北京空间飞行器总体设计部 | A kind of satellite antenna compresses relieving mechanism |
| CN105659919B (en) * | 2011-12-12 | 2014-06-04 | 北京空间飞行器总体设计部 | A kind of spaceborne servomechanism system |
| US20140174214A1 (en) * | 2011-12-23 | 2014-06-26 | Richard O. HORTH | Antenna pointing system |
| CN204029989U (en) * | 2013-11-27 | 2014-12-17 | 上海宇航系统工程研究所 | A kind of integrated general satellite antenna directing mechanism driven unit |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108054515B (en) * | 2017-10-27 | 2020-10-27 | 上海卫星工程研究所 | Satellite-borne two-dimensional driving data transmission antenna system capable of realizing specific initial pointing |
| CN108054515A (en) * | 2017-10-27 | 2018-05-18 | 上海卫星工程研究所 | The specific spaceborne two-dimentional driving number being initially directed toward can be achieved and pass antenna system |
| CN108054512A (en) * | 2017-12-08 | 2018-05-18 | 上海宇航系统工程研究所 | A kind of high-torque anti-interference antenna directing mechanism for survey of deep space |
| CN108054512B (en) * | 2017-12-08 | 2020-09-08 | 上海宇航系统工程研究所 | High-torque anti-interference antenna pointing mechanism for deep space exploration |
| CN108183305A (en) * | 2018-01-25 | 2018-06-19 | 哈尔滨工业大学 | The method of adjustment of satellite antenna space mast end position and attitude error |
| CN108183305B (en) * | 2018-01-25 | 2019-11-15 | 哈尔滨工业大学 | The method of adjustment of satellite antenna space mast end position and attitude error |
| CN109552672A (en) * | 2018-11-12 | 2019-04-02 | 上海宇航系统工程研究所 | A kind of hard limit adjustable position-limit mechanism of angle |
| CN109616741A (en) * | 2018-11-15 | 2019-04-12 | 上海宇航系统工程研究所 | Active matrix driving two-dimensional development formula antenna |
| CN111193095A (en) * | 2020-01-06 | 2020-05-22 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Deployable mechanism of satellite-borne antenna |
| CN111193095B (en) * | 2020-01-06 | 2022-05-17 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Deployable mechanism of satellite-borne antenna |
| CN112623280A (en) * | 2021-01-04 | 2021-04-09 | 上海宇航系统工程研究所 | Two-degree-of-freedom solar cell array unfolding device |
| CN113753270A (en) * | 2021-09-13 | 2021-12-07 | 北京空间飞行器总体设计部 | Wide-temperature-range high-rigidity statically determinate type pressing system |
| CN113753270B (en) * | 2021-09-13 | 2023-08-29 | 北京空间飞行器总体设计部 | Wide-temperature-range high-rigidity statically-determined compression system |
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|---|---|
| CN107240764B (en) | 2020-08-28 |
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