CN107658538A - Equipment and its installation method for spaceborne radar deployed condition dress star - Google Patents
Equipment and its installation method for spaceborne radar deployed condition dress star Download PDFInfo
- Publication number
- CN107658538A CN107658538A CN201710628690.9A CN201710628690A CN107658538A CN 107658538 A CN107658538 A CN 107658538A CN 201710628690 A CN201710628690 A CN 201710628690A CN 107658538 A CN107658538 A CN 107658538A
- Authority
- CN
- China
- Prior art keywords
- radar
- equipment
- balancer
- crossbeam
- deployed condition
- 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
- 238000009434 installation Methods 0.000 title claims abstract description 29
- 238000000034 method Methods 0.000 title claims abstract description 16
- 239000000725 suspension Substances 0.000 claims abstract description 18
- 230000007246 mechanism Effects 0.000 claims abstract description 17
- 238000010586 diagram Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 239000002775 capsule Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000005303 weighing Methods 0.000 description 1
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
- H01Q1/18—Means for stabilising antennas on an unstable platform
-
- 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
- H01Q1/1235—Collapsible supports; Means for erecting a rigid antenna
-
- 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
Landscapes
- Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Support Of Aerials (AREA)
- Aerials With Secondary Devices (AREA)
Abstract
The present invention is provided to the equipment of spaceborne radar deployed condition dress star, including：Crossbeam；Two suspender belts, one end of suspender belt are fixed on the crossbeam, and the other end is hung on travelling crane hook；First balancer, one end are fixedly connected on crossbeam, and the other end is connected on the suspension centre of radar antenna, and the extended line of its connecting line crosses the barycenter of radar antenna；Second balancer, one end are fixedly connected on crossbeam, and the distance between first balancer is adjustable, and the other end is connected on the suspension centre of servo control mechanism, and the extended line of its connecting line crosses the barycenter of servo control mechanism.The present invention also provides the installation method of dress star equipment.For the equipment of spaceborne radar deployed condition dress star, meets Complex Radar in terms of processing safety on satellite and installation accuracy the needs of.For the installation method of spaceborne radar deployed condition dress star equipment, make dress star equipment coordinate driving to use, the six-freedom degree motion of Complex Radar deployed condition can be achieved, be easy to installation and removal of the radar on satellite.
Description
Technical field
The present invention relates to Aero-Space field of electromechanical technology, the more particularly to equipment for spaceborne radar deployed condition dress star
And its installation method.
Background technology
As the continuous improvement of spaceborne radar performance and the complication of function develop, the radar hardware outside satellite capsule
(including radar antenna and servo control mechanism) structure is increasingly sophisticated, and weight is developed into tens kilograms even more heavy by several kilograms.
For several kilograms of radar, can be mounted and dismounted by operator is hand-held on satellite.But for tens
Gram Complex Radar, then by traditional installation and removal method, not only need more people to coordinate, also there is that efficiency is low, assembled and disassembled
The problems such as journey risk is uncontrollable, installation accuracy is low.Common auxiliary dress star car is appropriate only for flat board type component simple in construction
Assembly and disassembly on satellite, assembly and disassembly of the Complex Radar for not being suitable for there is load system on satellite.
The content of the invention
It is an object of the invention to provide the equipment and its installation method for spaceborne radar deployed condition dress star, to solve
Complex Radar with load system on satellite how assemble and disassemble the problem of.
In order to solve the above-mentioned technical problem, the technical scheme is that：One kind is used for spaceborne radar deployed condition dress star
Equipment, including：Crossbeam；Two suspender belts, one end of the suspender belt are fixed on the crossbeam, and the other end hangs over travelling crane hook
On；First balancer, one end are fixedly connected on the crossbeam, and the other end is connected on the suspension centre of radar antenna, its connecting line
Extended line cross the barycenter of radar antenna；Second balancer, one end are fixedly connected on the crossbeam, with first balancer
The distance between it is adjustable, the other end is connected on the suspension centre of servo control mechanism, and the extended line of its connecting line crosses the barycenter of servo control mechanism.
Further, the equipment for spaceborne radar deployed condition dress star also includes lifting bolt and shackle, described to hang
On the crossbeam, one end of the suspender belt is connected by buckle on the lifting bolt ring screw-driving.
Further, one end of first balancer and second balancer is fixedly connected on by clip respectively
On the crossbeam, the hoop sleeve according to the distance between two clips of radar size adjusting, and uses screw on the crossbeam
Clip is fixed on the crossbeam.
Further, the equipment for spaceborne radar deployed condition dress star also includes safety rope, in clip fixing point and thunder
Up to being connected with safety rope between antenna suspension centre, and safety rope is connected between clip fixing point and servo control mechanism suspension centre.
The present invention also provides a kind of installation method for spaceborne radar deployed condition dress star equipment, including：Radar is existed
Deploy in fixing device；Two suspender belts are suspended on travelling crane hook, and are moved to above radar, the first balancer and second is flat
Weighing apparatus is connected respectively on the suspension centre of radar antenna and servo control mechanism, plays lifting star equipment, balances the first balancer and second
Device is operated in effective travel；The attachment screw between radar and fixing device is removed, by driving by radar movable to defending
Near installation site on star, if radar installation bottom surface and its mounting surface on satellite are not parallel, regulation radar makes it three
Arbitrarily rotated in individual rotational freedom, until bottom surface is parallel with its mounting surface, radar is moved into bottom surface is bonded with its mounting surface,
Radar bottom surface is fixed on mounting surface by installation attachment screw.
Provided by the present invention for the equipment of spaceborne radar deployed condition dress star, meet that Complex Radar operates peace on satellite
Demand in terms of full property and installation accuracy.
Provided by the present invention for the installation method of spaceborne radar deployed condition dress star equipment, dress star equipment is set to coordinate driving
Use, the six-freedom degree motion of Complex Radar deployed condition can be achieved, be easy to installation and removal of the radar on satellite.
Brief description of the drawings
Invention is described further below in conjunction with the accompanying drawings：
Fig. 1 is the device structure schematic diagram provided in an embodiment of the present invention that star is filled for spaceborne radar deployed condition；
Fig. 2 is the structure that the equipment provided in an embodiment of the present invention for spaceborne radar deployed condition dress star is connected with radar
Schematic diagram；
Fig. 3 be it is provided in an embodiment of the present invention for spaceborne radar deployed condition fill star equipment installation method the step of flow
Cheng Tu.
Embodiment
Below in conjunction with the drawings and specific embodiments to spaceborne radar deployed condition proposed by the present invention fill star equipment and its
Installation method is described in further detail.According to following explanation and claims, advantages and features of the invention will become apparent from.
It should be noted that accompanying drawing uses using very simplified form and non-accurately ratio, only to convenience, lucidly aid in
Illustrate the purpose of the embodiment of the present invention.
The core concept of the present invention is, the equipment that star is filled provided by the present invention for spaceborne radar deployed condition, meets
Demand of the Complex Radar on satellite in terms of processing safety and installation accuracy.Deploy shape provided by the present invention for spaceborne radar
State fills the installation method of star equipment, makes dress star equipment coordinate driving to use, and six freedom of Complex Radar deployed condition can be achieved
Degree motion, is easy to installation and removal of the radar on satellite.
Fig. 1 is the device structure schematic diagram provided in an embodiment of the present invention that star is filled for spaceborne radar deployed condition；Fig. 2 is
The structural representation that equipment provided in an embodiment of the present invention for spaceborne radar deployed condition dress star is connected with radar.Reference picture
1 and Fig. 2, a kind of equipment for spaceborne radar deployed condition dress star, including：Crossbeam 11；Two suspender belts 12, the suspender belt 12
One end be fixed on the crossbeam 11, the other end is hung on travelling crane hook；First balancer 13, one end are fixedly connected on described
On crossbeam 11, the other end is connected on the suspension centre of radar antenna 21, and the extended line of its connecting line crosses the barycenter of radar antenna 21；The
Two balancers 14, one end are fixedly connected on the crossbeam 11, adjustable, the other end of the distance between described first balancer 13
It is connected on the suspension centre of servo control mechanism 22, the extended line of its connecting line crosses the barycenter of servo control mechanism 22.
In embodiments of the present invention, the equipment for spaceborne radar deployed condition dress star also includes lifting bolt 15 and unloaded
Button 16, two lifting bolts 15 are tightened in the both ends of crossbeam 11 respectively, and one end of two suspender belts 12 is connected by shackle 16 respectively
On the lifting bolt 15.
One end of first balancer 13 and the second balancer 14 is fixedly connected on the crossbeam 11 by clip 17 respectively
On, the clip 17 is enclosed on the crossbeam 11, will be blocked according to the distance between two clips 17 of thunder size adjusting, and with screw
Hoop 17 is fixed on the crossbeam 11.Safety rope 18, Yi Ji is connected between clip fixing point and the suspension centre of radar antenna 21
Safety rope 18 is connected between clip fixing point and the suspension centre of servo control mechanism 22.
For balancer in effective travel, its value of thrust is invariable；By radar gross mass be divided into the mass of radar antenna 21 and
The value of thrust of the mass two parts of servo control mechanism 22, the first balancer 13 and the second balancer 14 respectively with radar antenna 21, servo
The quality of mechanism 22 is equal.
Fig. 3 be it is provided in an embodiment of the present invention for spaceborne radar deployed condition fill star equipment installation method the step of flow
Cheng Tu.Reference picture 3, for the installation method of spaceborne radar deployed condition dress star equipment, comprise the following steps：
S31, radar deployed on the securing means；
S32, two suspender belts are suspended on travelling crane hook, and be moved to above radar, the first balancer and second are balanced
Device is connected respectively on the suspension centre of radar antenna and servo control mechanism, is played lifting star equipment, is made the first balancer and the second balancer
It is operated in effective travel；
Attachment screw between S33, dismounting radar and fixing device, by driving a vehicle radar movable to the peace on satellite
Near holding position, if radar installation bottom surface and its mounting surface on satellite are not parallel, regulation radar makes it be rotated certainly at three
By arbitrarily being rotated in degree, until bottom surface is parallel with its mounting surface, radar is moved into bottom surface is bonded with its mounting surface, installation connection
Radar bottom surface is fixed on mounting surface by screw.
Unloading process of the radar on satellite is opposite with installation process.
Obviously, those skilled in the art can carry out the essence of various changes and deformation without departing from the present invention to the present invention
God and scope.So, if these modifications and variations of the present invention belong to the scope of the claims in the present invention and its equivalent technologies
Within, then the present invention is also intended to comprising including these changes and modification.
Claims (5)
- A kind of 1. equipment for spaceborne radar deployed condition dress star, it is characterised in that including：Crossbeam；Two suspender belts, one end of the suspender belt are fixed on the crossbeam, and the other end is hung on travelling crane hook；First balancer, one end are fixedly connected on the crossbeam, and the other end is connected on the suspension centre of radar antenna, its connecting line Extended line cross the barycenter of radar antenna；Second balancer, one end are fixedly connected on the crossbeam, adjustable, the other end of the distance between described first balancer It is connected on the suspension centre of servo control mechanism, the extended line of its connecting line crosses the barycenter of servo control mechanism.
- 2. the equipment for spaceborne radar deployed condition dress star as claimed in claim 1, it is characterised in that including lifting bolt And shackle, the lifting bolt are tightened on the crossbeam, one end of the suspender belt is connected by buckle in the suspension ring spiral shell Nail on.
- 3. the equipment for spaceborne radar deployed condition dress star as claimed in claim 1, it is characterised in that first balance One end of device and second balancer is fixedly connected on the crossbeam by clip respectively, and the hoop sleeve is in the horizontal stroke Liang Shang, clip is fixed on the crossbeam according to the distance between two clips of radar size adjusting, and with screw.
- 4. the equipment for spaceborne radar deployed condition dress star as claimed in claim 1, it is characterised in that also include insurance Rope, is connected with safety rope between clip fixing point and radar antenna suspension centre, and in clip fixing point and servo control mechanism suspension centre Between be connected with safety rope.
- A kind of 5. installation method as claimed in claim 1 for spaceborne radar deployed condition dress star equipment, it is characterised in that Including：Radar is deployed on the securing means；Two suspender belts are suspended on travelling crane hook, and are moved to above radar, the first balancer and the second balancer are connected respectively It is connected on the suspension centre of radar antenna and servo control mechanism, plays lifting star equipment, be operated in the first balancer and the second balancer Imitate in stroke；The attachment screw between radar and fixing device is removed, it is by driving a vehicle that radar movable is attached to the installation site on satellite Closely, if radar installation bottom surface and its mounting surface on satellite are not parallel, regulation radar makes it appoint in three rotational freedoms Meaning rotates, and until bottom surface is parallel with its mounting surface, radar is moved into bottom surface is bonded with its mounting surface, installs attachment screw by thunder It is fixed on up to bottom surface on mounting surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710628690.9A CN107658538B (en) | 2017-07-28 | 2017-07-28 | Device for loading star in unfolding state of satellite-borne radar and installation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710628690.9A CN107658538B (en) | 2017-07-28 | 2017-07-28 | Device for loading star in unfolding state of satellite-borne radar and installation method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107658538A true CN107658538A (en) | 2018-02-02 |
| CN107658538B CN107658538B (en) | 2020-12-22 |
Family
ID=61128140
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710628690.9A Active CN107658538B (en) | 2017-07-28 | 2017-07-28 | Device for loading star in unfolding state of satellite-borne radar and installation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107658538B (en) |
Citations (14)
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| EP0669277B1 (en) * | 1994-02-28 | 1999-04-28 | Electricite De France | Sling for the transportation of loads by helicopter |
| DE202007014023U1 (en) * | 2007-10-02 | 2008-02-07 | Terex-Demag Gmbh & Co. Kg | Last Traverse |
| CN101318611A (en) * | 2008-07-18 | 2008-12-10 | 湘潭电机股份有限公司 | An adjustable combined spreader for wind turbine assembly |
| US7837245B2 (en) * | 2006-05-24 | 2010-11-23 | Hailstone Chris D | Crane spreader beam having radio-controlled load release |
| CN201737587U (en) * | 2010-07-19 | 2011-02-09 | 中国电子科技集团公司第十四研究所 | Hoisting device for antenna array surface |
| CN102556831A (en) * | 2011-12-20 | 2012-07-11 | 北京卫星环境工程研究所 | Horizontal adjusting sling for spacecraft |
| CN202429865U (en) * | 2011-11-11 | 2012-09-12 | 中国飞行试验研究院 | Lift for mounting and demounting integral components of photoelectric radars |
| CN102849612A (en) * | 2012-03-31 | 2013-01-02 | 航天东方红卫星有限公司 | Multi-function combination lifting device for minisatellite |
| CN202671002U (en) * | 2012-07-02 | 2013-01-16 | 山重建机有限公司 | Lifting appliance for oil cylinder of excavator |
| CN202829283U (en) * | 2012-08-30 | 2013-03-27 | 广州汽车集团股份有限公司 | Spreader component |
| CN103274288A (en) * | 2013-06-05 | 2013-09-04 | 北京空间飞行器总体设计部 | Suspending and releasing system used for impact test of lander |
| CN203998583U (en) * | 2014-08-08 | 2014-12-10 | 上海卫星工程研究所 | Spacecraft is light-duty suspender attaching parts for lifting |
| CN204873425U (en) * | 2015-08-05 | 2015-12-16 | 天津卡斯特机械有限公司 | Excavator hydro -cylinder special lifting device |
| EP3002604A2 (en) * | 2014-10-03 | 2016-04-06 | Airbus Helicopters | A rotorcraft fitted with a radioaltimeter having plane antennas and a lens for modifying the field of view of the antennas |
-
2017
- 2017-07-28 CN CN201710628690.9A patent/CN107658538B/en active Active
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0669277B1 (en) * | 1994-02-28 | 1999-04-28 | Electricite De France | Sling for the transportation of loads by helicopter |
| US7837245B2 (en) * | 2006-05-24 | 2010-11-23 | Hailstone Chris D | Crane spreader beam having radio-controlled load release |
| DE202007014023U1 (en) * | 2007-10-02 | 2008-02-07 | Terex-Demag Gmbh & Co. Kg | Last Traverse |
| CN101318611A (en) * | 2008-07-18 | 2008-12-10 | 湘潭电机股份有限公司 | An adjustable combined spreader for wind turbine assembly |
| CN201737587U (en) * | 2010-07-19 | 2011-02-09 | 中国电子科技集团公司第十四研究所 | Hoisting device for antenna array surface |
| CN202429865U (en) * | 2011-11-11 | 2012-09-12 | 中国飞行试验研究院 | Lift for mounting and demounting integral components of photoelectric radars |
| CN102556831A (en) * | 2011-12-20 | 2012-07-11 | 北京卫星环境工程研究所 | Horizontal adjusting sling for spacecraft |
| CN102849612A (en) * | 2012-03-31 | 2013-01-02 | 航天东方红卫星有限公司 | Multi-function combination lifting device for minisatellite |
| CN202671002U (en) * | 2012-07-02 | 2013-01-16 | 山重建机有限公司 | Lifting appliance for oil cylinder of excavator |
| CN202829283U (en) * | 2012-08-30 | 2013-03-27 | 广州汽车集团股份有限公司 | Spreader component |
| CN103274288A (en) * | 2013-06-05 | 2013-09-04 | 北京空间飞行器总体设计部 | Suspending and releasing system used for impact test of lander |
| CN203998583U (en) * | 2014-08-08 | 2014-12-10 | 上海卫星工程研究所 | Spacecraft is light-duty suspender attaching parts for lifting |
| EP3002604A2 (en) * | 2014-10-03 | 2016-04-06 | Airbus Helicopters | A rotorcraft fitted with a radioaltimeter having plane antennas and a lens for modifying the field of view of the antennas |
| CN204873425U (en) * | 2015-08-05 | 2015-12-16 | 天津卡斯特机械有限公司 | Excavator hydro -cylinder special lifting device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107658538B (en) | 2020-12-22 |
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