CN106081165A - A kind of space development lazy-tongs of self adaptation thermal deformation - Google Patents
A kind of space development lazy-tongs of self adaptation thermal deformation Download PDFInfo
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- CN106081165A CN106081165A CN201610480528.2A CN201610480528A CN106081165A CN 106081165 A CN106081165 A CN 106081165A CN 201610480528 A CN201610480528 A CN 201610480528A CN 106081165 A CN106081165 A CN 106081165A
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- 230000006978 adaptation Effects 0.000 title claims abstract description 17
- 238000011161 development Methods 0.000 title claims abstract description 16
- 230000036316 preload Effects 0.000 claims description 16
- 229910000831 Steel Inorganic materials 0.000 claims description 14
- 239000010959 steel Substances 0.000 claims description 14
- 238000009434 installation Methods 0.000 claims description 5
- 230000002265 prevention Effects 0.000 claims description 3
- 238000013519 translation Methods 0.000 abstract description 4
- 230000006835 compression Effects 0.000 abstract description 3
- 238000007906 compression Methods 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 4
- 239000000203 mixture Substances 0.000 description 3
- 230000001360 synchronised effect Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- 239000011800 void material Substances 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 239000011825 aerospace material Substances 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000005056 compaction Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
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Abstract
The present invention proposes the space development lazy-tongs of a kind of self adaptation thermal deformation, including two fairleads, a set of linkage rope, two set self-adapting adjusting apparatus and two cable wire pressure strips.When the rope that links extends because of high temperature deformation, the adjustment spring elongation of self-adapting adjusting apparatus drives adjusting lever translation distich running rope rope to carry out tensioning；When the rope that links shortens because of low-temperature deformation, the big adjusting lever translation compression adjustment spring distich running rope rope driving self-adapting adjusting apparatus of linkage rope tension change discharges, it is ensured that linkage rope tension is maintained at and does not affects in the range of mechanism deploying reliability.The present invention efficiently solves at low temperature or high temperature limit operating mode second line of a couplet running rope rope because of the flexible caused tension force drastically variation issue of thermal deformation, improves the synchronicity of mechanism deploying and launches reliability, expanding the expansion temperature adaptation scope of solar array.
Description
Technical field
The invention belongs to spacecraft adnexa synchronous expansion and control technical field, the space of a kind of self adaptation thermal deformation
Launch lazy-tongs, be that a kind of solar array with steel wire rope pre-tightening tension self-adaptative adjustment function launches synchrodrive
Structure.
Background technology
Generally with large-sized solar cell array on modern spacecraft, it is contemplated that the restriction in vehicle space and launching
During bear bigger overload, be typically in rounding state at launching phase spacecraft solar array, until spacecraft
After separating with vehicle, solar array can unlock expansion.For ensureing that each piece of solar panel can press desired trajectory fortune
Dynamic also synchronous expansion, solar battery array is typically fitted with launch lazy-tongs, and most common of which is rope link gear
(CCL).CCL is made up of the fairlead fixed with development mechanism hinge and linkage rope, is similar to a tape handler.?
During solar array launches, the tension force travelling with the exhibits on an exhibition tour open procedure of linkage rope can occur respective change, the least meeting that tension force becomes
Affecting the synchronicity that solar array launches, what tension force became then can increase mounted resistance square too greatly.Traditional solution
It is for launching the lazy-tongs linkage rope suitable pretightning force of setting.This solution can make expansion lazy-tongs less
There is under temperature difference condition higher reliability, but when spatial environments difference variation is violent, the most under cryogenic, because heat becomes
The additional tension that shape causes is increased dramatically, and can reach the strength degree even beyond cord material.
The expansion lazy-tongs that the present invention proposes use adjusting apparatus to make linkage rope pre-tightening tension in condition of different temperatures
Lower self-adaptative adjustment, effectively reduces the tension variation scope of linkage rope, improves the temperature environment adaptability of mechanism.
Summary of the invention
Solve the technical problem that
Present invention is mainly used for the tension force solving to launch lazy-tongs linkage rope during solar array launches
The problem that excursion is excessive, especially solves in low temperature or high temperature limit operating mode second line of a couplet running rope rope tensility problem jumpy,
Make the change of linkage rope tension be maintained in safe scope, improve the reliability of mechanism deploying.
Technical scheme
In one aspect of the invention, the present invention proposes the space development lazy-tongs of a kind of self adaptation thermal deformation, including
Two fairleads, a set of linkage ropes；Fairlead is provided with the mounting interface being connected with solar array shaft hinge；Two
Fairlead is separately fixed on adjacent two shaft hinges of solar array；Linkage rope is closed ring, with certain
Clamp force is wound on two fairleads；
It is characterized in that:
Described space development lazy-tongs also include some set self-adapting adjusting apparatus；
Often set self-adapting adjusting apparatus includes an adjustment bearing, two directive wheels, two directive wheel bearing pins, adjustment
Bar, an adjustment spring, an adjustment swivel nut and a cable wire limiting plate；Adjust to be provided with on bearing and be connected with cell panel side
Mounting interface；
Two directive wheels are arranged on adjustment bearing by directive wheel bearing pin respectively, the guiding of the most corresponding first directive wheel
Being also equipped with cable wire limiting plate on wheel bearing pin, the directive wheel bearing pin of corresponding second directive wheel is length at the installing hole adjusted on bearing
Cylindrical void；
Described adjusting lever is through the installed surface of adjustment bearing, and described installed surface is perpendicular to the length direction of described strip hole；
The adjusting lever being in installed surface side is U-shaped shelf structure, with the directive wheel bearing pin secure fit of corresponding second directive wheel；It is in peace
The adjusting lever of dress face opposite side is column structure, top fixed adjustment swivel nut, column structure is cased be in the tune of pressured state
Whole spring, adjusts both ends of the spring and is retrained by installed surface and adjustment swivel nut；
Self-adapting adjusting apparatus is fixedly mounted on the solar panel side between two fairleads；It is positioned at fairlead two
The linkage rope of side is each passed through two directive wheels, and wherein linkage rope coordinates with the first directive wheel outside the first directive wheel,
Coordinate with the second directive wheel inside the second directive wheel.
Further preferred version, the space development lazy-tongs of described a kind of self adaptation thermal deformation, it is characterised in that: from
The tricks adapting to adjusting apparatus is even number set, half self-adapting adjusting apparatus and the installation direction of second half self-adapting adjusting apparatus
On the contrary.
Further preferred version, the space development lazy-tongs of described a kind of self adaptation thermal deformation, it is characterised in that: institute
Stating fairlead and radially ring week be provided with V-groove, axially local is provided with linkage rope escape prevention groove；Described linkage rope is divided into two sections,
Anticreep limited block and the anticreep slot fit of setting on fairlead it is equipped with on each section of linkage rope；Two sections of linkage ropes pass through steel
Rope slocket connects into a closed-loop；Described cable connector has length regulation function.
Further preferred version, the space development lazy-tongs of described a kind of self adaptation thermal deformation, it is characterised in that: steel
Rope slocket includes steel wire pressure ring, left-handed screw, right-handed screw, left-handed pre-load nut, dextrorotation pre-load nut, adjusting nut；Left side
Cable wire passes left-handed screw one end installing hole, and is fixed by steel wire pressure ring；The left-handed screw other end passes through left-handed pre-load nut
It is connected on the left of adjusting nut；Right side cable wire is through right-handed screw one end installing hole, and is fixed by steel wire pressure ring；Right-handed screw
The other end is connected on the right side of adjusting nut by dextrorotation pre-load nut.
Beneficial effect
The present invention effectively reduces the change difference of fairlead both sides linkage rope tension in lazy-tongs motion, improves
The synchronicity that solar array launches.
The present invention use can the adjusting lever of Automatic adjusument, efficiently solve at low temperature or high temperature limit operating mode second line of a couplet running rope
Rope, because of the flexible caused tension force drastically variation issue of thermal deformation, improves the reliability of mechanism deploying, expands solaode
The expansion temperature adaptation scope of battle array.
Present configuration scheme interface compatibility is good, can expansive approach in other similar spacecraft exhibitions needing synchronous expansion
In opening mechanism.
The additional aspect of the present invention and advantage will part be given in the following description, and part will become from the following description
Obtain substantially, or recognized by the practice of the present invention.
Accompanying drawing explanation
Above-mentioned and/or the additional aspect of the present invention and advantage are from combining the accompanying drawings below description to embodiment and will become
Substantially with easy to understand, wherein:
Fig. 1 is the lazy-tongs population structure schematic diagram of the present invention；
Fig. 2 is the fairlead structural representation of the present invention；
Fig. 3 is the linkage rope composition schematic diagram of the present invention；
Fig. 4 is the cable connector composition schematic diagram of the present invention；
Fig. 5 is the self-adapting adjusting apparatus structure composition schematic diagram of the present invention.
Wherein: fairlead 1, link rope 2, self-adapting adjusting apparatus 3, cable wire pressure strip 4, bowden cable 5, anticreep limited block
6, cable connector 7；Steel wire pressure ring 11, left-handed screw 12, right-handed screw 13, left-handed pre-load nut 14, dextrorotation pre-load nut 15, adjust
Whole nut 16；Adjust bearing 21, directive wheel 22, directive wheel bearing pin 23, adjusting lever 24, adjust spring 25, adjust swivel nut 26, cable wire
Limiting plate 27.
Detailed description of the invention
Embodiments of the invention are described below in detail, and the example of described embodiment is shown in the drawings, the most from start to finish
Same or similar label represents same or similar element or has the element of same or like function.Below with reference to attached
The embodiment that figure describes is exemplary, it is intended to is used for explaining the present invention, and is not considered as limiting the invention.
In describing the invention, it is to be understood that term " " center ", " longitudinally ", " laterally ", " length ", " width ",
" thickness ", " on ", D score, "front", "rear", "left", "right", " vertically ", " level ", " top ", " end ", " interior ", " outward ", " up time
Pin ", the orientation of the instruction such as " counterclockwise " or position relationship be based on orientation shown in the drawings or position relationship, be for only for ease of
Describe the present invention and simplification description rather than instruction or the device of hint indication or element must have specific orientation, Yi Te
Fixed azimuth configuration and operation, be therefore not considered as limiting the invention.
In addition, term " first ", " second " are only used for describing purpose, and it is not intended that instruction or hint relative importance
Or the implicit quantity indicating indicated technical characteristic.Therefore, define " first ", the feature of " second " can express or
Implicitly include one or more this feature.In describing the invention, " multiple " are meant that two or more,
Unless otherwise expressly limited specifically.
The invention aims to solve to launch lazy-tongs linkage rope opening during solar array launches
The problem that power excursion is excessive, especially solves at low temperature or high temperature limit operating mode second line of a couplet running rope rope tensility is jumpy asks
Topic.
Propose the space development lazy-tongs of a kind of self adaptation thermal deformation for this present invention, including two fairleads, one
Associating running rope rope；Also include some set self-adapting adjusting apparatus.
Fairlead is provided with the mounting interface being connected with solar array shaft hinge；Two fairleads are separately fixed at
On adjacent two shaft hinges of solar array；Linkage rope is closed ring, is wound on two draglines with certain tensioning
On ring.
Often set self-adapting adjusting apparatus includes an adjustment bearing, two directive wheels, two directive wheel bearing pins, adjustment
Bar, an adjustment spring, an adjustment swivel nut and a cable wire limiting plate；Adjust to be provided with on bearing and be connected with cell panel side
Mounting interface.
Two directive wheels are arranged on adjustment bearing by directive wheel bearing pin respectively, the guiding of the most corresponding first directive wheel
Being also equipped with cable wire limiting plate on wheel bearing pin, the directive wheel bearing pin of corresponding second directive wheel is length at the installing hole adjusted on bearing
Cylindrical void.
Described adjusting lever is through the installed surface of adjustment bearing, and described installed surface is perpendicular to the length direction of described strip hole；
The adjusting lever being in installed surface side is U-shaped shelf structure, with the directive wheel bearing pin secure fit of corresponding second directive wheel；It is in peace
The adjusting lever of dress face opposite side is column structure, top fixed adjustment swivel nut, column structure is cased be in the tune of pressured state
Whole spring, adjusts both ends of the spring and is retrained by installed surface and adjustment swivel nut.
Self-adapting adjusting apparatus is fixedly mounted on the solar panel side between two fairleads；It is positioned at fairlead two
The linkage rope of side is each passed through two directive wheels, and wherein linkage rope coordinates with the first directive wheel outside the first directive wheel,
Coordinate with the second directive wheel inside the second directive wheel.
The operation principle of the present invention is: linkage rope passes the directive wheel of self-adapting adjusting apparatus, and with certain tensioning
It is wound on two fairleads, when the rope that links extends because of high temperature deformation, adjusts spring elongation and drive adjusting lever to translate linkage
Rope carries out tensioning；When the rope that links shortens because of low-temperature deformation, linkage rope tension becomes big and drives adjusting lever translation compression to adjust
Whole spring distich running rope rope discharges, it is ensured that linkage rope tension is maintained at and does not affects in the range of mechanism deploying reliability.
Based on above-mentioned principle, the specific embodiment of the present invention it is given below:
Embodiment 1:
As it is shown in figure 1, the space development lazy-tongs of the present embodiment a kind of self adaptation thermal deformation include two fairleads 1,
A set of linkage rope 2, two set self-adapting adjusting apparatus 3 and two cable wire pressure strips 4.Two fairleads 1 are separately fixed at the sun
On adjacent two shaft hinges of energy cell array.Two set self-adapting adjusting apparatus 3 are arranged on the solar energy between two fairleads
Cell panel side, and the installation direction of two set self-adapting adjusting apparatus 3 is contrary, linkage rope 2 is through two set self-adaptative adjustment dresses
Put and be wound on two fairleads with certain tensioning, can move along with the rotation of fairlead.Cable wire pressure strip 4 is fixed on leads
Prevent from slipping by cable wire and fairlead local compaction on grommet.
As in figure 2 it is shown, radially ring week be provided with V-groove on fairlead, axially local is provided with linkage rope escape prevention groove.Dragline
It is additionally provided with on ring and the mounting interface of solar array shaft hinge.
As it is shown on figure 3, linkage rope includes bowden cable 5, anticreep limited block 6 and cable connector 7.Linkage rope is divided into two
Section, each section is equipped with anticreep limited block 6 and the anticreep slot fit on fairlead 1, prevents from linking between rope and fairlead
Relatively slide.Two sections of linkage ropes connect one closed-loop of formation by two cable connectors 7.
As shown in Figure 4, cable connector 7 includes steel wire pressure ring 11, left-handed screw 12, right-handed screw 13, left-handed pre-load nut
14, dextrorotation pre-load nut 15, adjusting nut 16.Left side cable wire is through left-handed screw 12 one end installing hole, and passes through steel wire pressure ring
11 fix；Left-handed screw 12 other end is connected on the left of adjusting nut 16 by left-handed pre-load nut 14；Right side cable wire is through the right side
Rotation screw 13 one end installing hole, and fixed by steel wire pressure ring；Right-handed screw 13 other end is connected by dextrorotation pre-load nut 15
On the right side of adjusting nut 16.By rotating the adjusting nut 16 adjustable linkage initial installation length of rope, left-handed pre-load nut 14,
It is locking that dextrorotation pre-load nut 15 is used for that adjusting nut 16 is carried out pretension.
As it is shown in figure 5, self-adapting adjusting apparatus 3 includes adjusting bearing 21, directive wheel 22, directive wheel bearing pin 23, adjusting lever
24, adjust spring 25, adjust swivel nut 26 and cable wire limiting plate 27.It is provided with the installation with cell panel side on adjustment bearing to connect
Mouthful.
Two directive wheels 22 are arranged on adjustment bearing 21 by directive wheel bearing pin 23 respectively, the most corresponding first directive wheel
Directive wheel bearing pin on be also equipped with cable wire limiting plate 27, the directive wheel bearing pin of corresponding second directive wheel is in the peace adjusted on bearing
Dress hole is strip hole.
Described adjusting lever 24 is through the installed surface of adjustment bearing, and described installed surface is perpendicular to the length side of described strip hole
To；The adjusting lever being in installed surface side is U-shaped shelf structure, with the directive wheel bearing pin secure fit of corresponding second directive wheel；Place
Adjusting lever in installed surface opposite side is column structure, top fixed adjustment swivel nut 26, column structure is cased be in pressurized shape
The adjustment spring 25 of state, adjusts spring 25 two ends and is retrained by installed surface and adjustment swivel nut 26.
Self-adapting adjusting apparatus 3 is fixedly mounted on the solar panel side between two fairleads 1；It is positioned at fairlead
The linkage rope of both sides is each passed through two directive wheels, and wherein linkage rope 2 is joined with the first directive wheel outside the first directive wheel
Close, coordinate with the second directive wheel inside the second directive wheel.
Linkage rope 2, through self-adapting adjusting apparatus 3, relies on directive wheel 22 tensioning shown in Fig. 5.When linkage rope 2 because of
During high temperature deformation elongation, the adjustment spring 25 of self-adapting adjusting apparatus 3 extends, and drives adjusting lever 24 to translate and then pull to wheel 22
Distich running rope rope 2 carries out tensioning；When the rope 2 that links shortens because of low-temperature deformation, linkage rope 2 tension force becomes big and drives adjusting lever 24
Translation compression adjusts spring 25 distich running rope rope 2 and carries out release of tension, it is ensured that tension force is maintained at does not affects mechanism deploying reliability
In the range of.
Said mechanism material uses general aerospace material, such as aluminium alloy, titanium alloy, rustless steel.
Although above it has been shown and described that embodiments of the invention, it is to be understood that above-described embodiment is example
Property, it is impossible to be interpreted as limitation of the present invention, those of ordinary skill in the art is without departing from the principle of the present invention and objective
In the case of above-described embodiment can be changed within the scope of the invention, revise, replace and modification.
Claims (4)
1. space development lazy-tongs for self adaptation thermal deformation, including two fairleads, a set of linkage rope；On fairlead
It is provided with the mounting interface being connected with solar array shaft hinge；Two fairleads are separately fixed at the phase of solar array
On adjacent two shaft hinges；Linkage rope is closed ring, is wound on two fairleads with certain tensioning；
It is characterized in that:
Described space development lazy-tongs also include some set self-adapting adjusting apparatus；
Often set self-adapting adjusting apparatus include an adjustment bearing, two directive wheels, two directive wheel bearing pins, adjusting lever,
One adjusts spring, an adjustment swivel nut and a cable wire limiting plate；Adjust to be provided with on bearing and be connected with cell panel side
Mounting interface；
Two directive wheels are arranged on adjustment bearing by directive wheel bearing pin respectively, the directive wheel pin of the most corresponding first directive wheel
Being also equipped with cable wire limiting plate on axle, the directive wheel bearing pin of corresponding second directive wheel is strip at the installing hole adjusted on bearing
Hole；
Described adjusting lever is through the installed surface of adjustment bearing, and described installed surface is perpendicular to the length direction of described strip hole；It is in
The adjusting lever of installed surface side is U-shaped shelf structure, with the directive wheel bearing pin secure fit of corresponding second directive wheel；It is in installed surface
The adjusting lever of opposite side is column structure, top fixed adjustment swivel nut, column structure is cased be in the adjustment bullet of pressured state
Spring, adjusts both ends of the spring and is retrained by installed surface and adjustment swivel nut；
Self-adapting adjusting apparatus is fixedly mounted on the solar panel side between two fairleads；It is positioned at fairlead both sides
Linkage rope is each passed through two directive wheels, and wherein linkage rope coordinates with the first directive wheel outside the first directive wheel, the
Coordinate with the second directive wheel inside two directive wheels.
A kind of space development lazy-tongs of self adaptation thermal deformation, it is characterised in that: self adaptation is adjusted
The tricks of engagement positions is even number set, and half self-adapting adjusting apparatus is contrary with the installation direction of second half self-adapting adjusting apparatus.
A kind of space development lazy-tongs of self adaptation thermal deformation, it is characterised in that: described dragline
Ring is radially provided with V-groove in ring week, and axially local is provided with linkage rope escape prevention groove；Described linkage rope is divided into two sections, Mei Yiduan
Anticreep limited block and the anticreep slot fit of setting on fairlead it is equipped with on linkage rope；Two sections of linkage ropes pass through cable connector
Connect into a closed-loop；Described cable connector has length regulation function.
A kind of space development lazy-tongs of self adaptation thermal deformation, it is characterised in that: cable connector
Including steel wire pressure ring, left-handed screw, right-handed screw, left-handed pre-load nut, dextrorotation pre-load nut, adjusting nut；Left side cable wire is worn
Cross left-handed screw one end installing hole, and fixed by steel wire pressure ring；The left-handed screw other end is connected to by left-handed pre-load nut
On the left of adjusting nut；Right side cable wire is through right-handed screw one end installing hole, and is fixed by steel wire pressure ring；The right-handed screw other end
It is connected on the right side of adjusting nut by dextrorotation pre-load nut.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610480528.2A CN106081165B (en) | 2016-06-27 | 2016-06-27 | A kind of space development lazy-tongs of adaptive thermal deformation |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610480528.2A CN106081165B (en) | 2016-06-27 | 2016-06-27 | A kind of space development lazy-tongs of adaptive thermal deformation |
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| Publication Number | Publication Date |
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| CN106081165A true CN106081165A (en) | 2016-11-09 |
| CN106081165B CN106081165B (en) | 2018-01-12 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106428640A (en) * | 2016-11-30 | 2017-02-22 | 上海卫星工程研究所 | Automatic counterglow orientator of satellite solar array |
| CN107458624A (en) * | 2017-07-28 | 2017-12-12 | 中国科学院西安光学精密机械研究所 | A kind of spring retractable deployable mechanism |
| CN110576963A (en) * | 2019-09-19 | 2019-12-17 | 西北工业大学 | Solar unmanned aerial vehicle wing structure |
| CN110966350A (en) * | 2019-12-04 | 2020-04-07 | 北京卫星制造厂有限公司 | Manual adjusting device for pre-tightening locking ring tension |
| CN112429275A (en) * | 2020-12-10 | 2021-03-02 | 北京空间机电研究所 | Spacing formula space rotation locking and releasing mechanism |
| CN115009541A (en) * | 2021-04-12 | 2022-09-06 | 北京邮电大学 | Rope-linked hinge-folding type unfolding mechanism |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1234871A (en) * | 1968-01-22 | 1971-06-09 | Licentia Gmbh | Solar-cell generator for missions close to the sun |
| US20030015625A1 (en) * | 2001-07-13 | 2003-01-23 | The Boeing Company | Extendable/retractable bi-fold solar array |
| CN101383568A (en) * | 2008-10-24 | 2009-03-11 | 哈尔滨工业大学 | Synchronous expansion mechanism for foldable inflating expansion solar cell paddles |
| CN105460237A (en) * | 2014-08-20 | 2016-04-06 | 上海航天设备制造总厂 | Flexible solar wing hanging and unfolding device |
| CN205239949U (en) * | 2015-12-28 | 2016-05-18 | 中国科学院沈阳自动化研究所 | Deployable sun wing of cube |
-
2016
- 2016-06-27 CN CN201610480528.2A patent/CN106081165B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1234871A (en) * | 1968-01-22 | 1971-06-09 | Licentia Gmbh | Solar-cell generator for missions close to the sun |
| US20030015625A1 (en) * | 2001-07-13 | 2003-01-23 | The Boeing Company | Extendable/retractable bi-fold solar array |
| CN101383568A (en) * | 2008-10-24 | 2009-03-11 | 哈尔滨工业大学 | Synchronous expansion mechanism for foldable inflating expansion solar cell paddles |
| CN105460237A (en) * | 2014-08-20 | 2016-04-06 | 上海航天设备制造总厂 | Flexible solar wing hanging and unfolding device |
| CN205239949U (en) * | 2015-12-28 | 2016-05-18 | 中国科学院沈阳自动化研究所 | Deployable sun wing of cube |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106428640A (en) * | 2016-11-30 | 2017-02-22 | 上海卫星工程研究所 | Automatic counterglow orientator of satellite solar array |
| CN106428640B (en) * | 2016-11-30 | 2019-01-25 | 上海卫星工程研究所 | The automatic Direct to the sun device of satellite sun energy windsurfing |
| CN107458624A (en) * | 2017-07-28 | 2017-12-12 | 中国科学院西安光学精密机械研究所 | A kind of spring retractable deployable mechanism |
| CN107458624B (en) * | 2017-07-28 | 2023-04-11 | 中国科学院西安光学精密机械研究所 | Spring telescopic type deployable mechanism |
| CN110576963A (en) * | 2019-09-19 | 2019-12-17 | 西北工业大学 | Solar unmanned aerial vehicle wing structure |
| CN110966350A (en) * | 2019-12-04 | 2020-04-07 | 北京卫星制造厂有限公司 | Manual adjusting device for pre-tightening locking ring tension |
| CN110966350B (en) * | 2019-12-04 | 2021-10-01 | 北京卫星制造厂有限公司 | Manual adjusting device for pre-tightening locking ring tension |
| CN112429275A (en) * | 2020-12-10 | 2021-03-02 | 北京空间机电研究所 | Spacing formula space rotation locking and releasing mechanism |
| CN115009541A (en) * | 2021-04-12 | 2022-09-06 | 北京邮电大学 | Rope-linked hinge-folding type unfolding mechanism |
| CN115009541B (en) * | 2021-04-12 | 2023-12-26 | 北京邮电大学 | Hinge formula expansion mechanism that turns over of rope linkage |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106081165B (en) | 2018-01-12 |
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