CN110979742B - High-expansion-ratio unfolding mechanism suitable for space environment - Google Patents
High-expansion-ratio unfolding mechanism suitable for space environment Download PDFInfo
- Publication number
- CN110979742B CN110979742B CN201911204254.4A CN201911204254A CN110979742B CN 110979742 B CN110979742 B CN 110979742B CN 201911204254 A CN201911204254 A CN 201911204254A CN 110979742 B CN110979742 B CN 110979742B
- Authority
- CN
- China
- Prior art keywords
- groups
- mounting plate
- load mounting
- strip
- structural plate
- 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.)
- Active
Links
- 230000007246 mechanism Effects 0.000 title claims abstract description 45
- 238000004804 winding Methods 0.000 claims abstract description 22
- 239000007787 solid Substances 0.000 claims description 3
- 239000000126 substance Substances 0.000 claims description 3
- 230000001050 lubricating effect Effects 0.000 claims description 2
- 238000005070 sampling Methods 0.000 description 6
- 230000005540 biological transmission Effects 0.000 description 4
- 230000009471 action Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 241000282414 Homo sapiens Species 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 239000000969 carrier Substances 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000000314 lubricant Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- CWQXQMHSOZUFJS-UHFFFAOYSA-N molybdenum disulfide Chemical compound S=[Mo]=S CWQXQMHSOZUFJS-UHFFFAOYSA-N 0.000 description 1
- 229910052982 molybdenum disulfide Inorganic materials 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000007480 spreading Effects 0.000 description 1
Images
Classifications
-
- 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
Abstract
The invention provides a high-expansion-ratio unfolding mechanism suitable for a space environment, which comprises an upper structural plate, two groups of limiting sleeves, two groups of winding drums, two groups of strip springs and a load mounting plate, wherein the upper structural plate is fixedly connected with the upper structural plate; wherein, the upper structure plate is fixed on the detector, and the whole unfolding mechanism is fixedly connected with the detector; the two groups of winding drums are respectively positioned in the two limiting sleeves, and are driven by the motor to rotate in a linkage manner so as to synchronously drive the two groups of strip-shaped springs to wind and release; one end of each of the two groups of strip springs is fixed on the winding drum, and the extending end of each of the two groups of strip springs is connected with the load mounting plate to drive the load mounting plate to ascend and descend; the load mounting plate is used for executing units of load tasks. According to the unfolding mechanism, the ribbon spring with the arc-shaped section is used as a core part, so that the flexible folding and rigid unfolding of the unfolding mechanism are realized; the volume and the length in the furled state are small, the supporting structure with certain rigidity can be obtained after the unfolding, and the technical problems that the traditional unfolding mechanism cannot realize large expansion-contraction ratio and light weight are solved.
Description
Technical Field
The invention belongs to the technical field of deep space exploration, relates to an unfolding mechanism, and particularly relates to an unfolding mechanism with a large expansion-contraction ratio, which is suitable for a space environment.
Background
Extraterrestrial bodies are important carriers for human beings to understand the origin evolution of universe and solar system, and bear abundant scientific information, so that the extraterrestrial bodies are sampled and returned to have important significance.
Before sampling the extraterrestrial object, the sampler needs to be stretched from the detector to the surface of the extraterrestrial object through the unfolding mechanism, and the sampler is tightly pressed on the surface of the extraterrestrial object under certain pressure, so that the sampling task can be started. However, the task of sampling and returning extraterrestrial objects is difficult, resources on a detector are limited, the requirement on the volume and weight of the sampling device is high, and particularly the volume and the length of an unfolding mechanism of the sampling device in an initial pressing and folding state are required to be small, so that the volume and the length of the sampling device in the folding state cannot be met by the common stretching forms of a lead screw, a gear rack and the like in the traditional mechanism, and a mature design product can not be used for reference.
In summary, new high-aspect-ratio deployment mechanisms are designed to meet the task requirements.
Disclosure of Invention
In order to overcome the defects of the prior art, the inventor of the invention carries out intensive research and provides a unfolding mechanism with a large spreading ratio, which is suitable for a space environment, and the unfolding mechanism is flexibly folded and rigidly unfolded by adopting a ribbon spring with an arc-shaped section as a core part; the volume and the length in the furled state are small, a supporting structure with certain rigidity can be obtained after the unfolding, and the technical problems that the traditional unfolding mechanism cannot realize large expansion-contraction ratio, light weight and the like are solved, so that the invention is completed.
The invention aims to provide the following technical scheme: a high-expansion-ratio unfolding mechanism suitable for a space environment comprises an upper structural plate, two groups of limiting sleeves, two groups of winding drums, two groups of strip springs and a load mounting plate; wherein the content of the first and second substances,
the upper structural plate is fixed on the detector, and the whole unfolding mechanism is fixedly connected with the detector;
the limiting sleeve is fixed below the upper structural plate and is a round sleeve with an opening at one side, a cylindrical circumferential structure on the limiting sleeve plays a limiting role, the tail end of the cylindrical circumferential structure is connected with a drooping straight baffle, and the two straight baffles are both positioned at the outer side end of the limiting sleeve;
the two groups of winding drums are respectively positioned in the two limiting sleeves, and are driven by the motor to rotate in a linkage manner so as to synchronously drive the two groups of strip-shaped springs to wind and release;
one end of each of the two groups of strip springs is fixed on the winding drum, and the extending end of each of the two groups of strip springs is connected with the load mounting plate to drive the load mounting plate to ascend and descend;
the load mounting plate is used for executing units of load tasks.
Furthermore, the cross section of the ribbon spring is arc-shaped, can be wound into a cylindrical reel, is accommodated in the limiting sleeve, can be completely unfolded into a rod shape, and bears the axial load.
Further, two sets of ribbon springs are mounted symmetrically with the load mounting plate.
Further, the unfolding mechanism further comprises a lower structural plate below the limiting sleeve, the lower structural plate and the upper structural plate are rigidly fixed, the lower structural plate is provided with a non-closed annular longitudinal through hole, the width of the longitudinal through hole is smaller than the inherent height of the cambered surface of the ribbon spring, and the extending end of the ribbon spring is longitudinally connected onto the load mounting plate through a connection.
Furthermore, a cylindrical guide sleeve is arranged below the lower structural plate around the longitudinal through hole, and the inner diameter of the guide sleeve is the outer diameter of the annular through hole.
Further, the tail end of the guide sleeve is processed with a conical surface, and the conical surface is narrow at the top and wide at the bottom; the load mounting plate is provided with a frustum corresponding to the guide sleeve, and the conical surface of the frustum is matched with the tail end of the guide sleeve to form a frustum-conical seat.
Furthermore, a solid lubricating film is arranged on the conical surfaces of the frustum and the guide sleeve.
The unfolding mechanism with the large expansion ratio, which is suitable for the space environment, provided by the invention brings beneficial technical effects:
(1) the innovative design scheme of unfolding and folding is as follows: the unfolding and folding actions of the mechanism are realized through the winding and releasing of the two groups of strip springs, so that the characteristics of small folding volume, light weight and the like which cannot be realized by the traditional transmission modes such as a lead screw, a gear rack and the like are realized; the internal transmission form of the unfolding mechanism is simple, the electric control difficulty is small, and the reliability is high;
(2) the length ratio of the unfolding state to the folding state is large, the mechanism has small volume and light weight: the length of the mechanism in the unfolding state is more than 4 times of that in the folding state, and the traditional transmission modes such as a lead screw, a gear rack and the like cannot be realized; in a furled state, the strip-shaped spring is wound on the winding drum to be cylindrical, so that the occupied volume is small, and the whole weight of the mechanism is light because the mechanism does not contain metal parts with larger weight, such as a lead screw and the like;
(3) can be unfolded and folded repeatedly: the mechanism can be repeatedly unfolded and folded by forward and reverse rotation of the winding drum, and consumables and wearing parts are not used in the repeated unfolding and folding process, so that the service life is long, and the cost is low;
(4) the mechanism is simple, and the reliability is high: the mechanism has few types of parts, reduces transmission links, only drives the band-shaped spring to wind and release through the rotation of the winding drum, and has low failure rate and high reliability during the operation of the mechanism;
(5) the space adaptability is strong: the structure is compact in a furled state, the rigidity is high, and the test bed can adapt to a large-scale vibration test; the main parts of the scheme are metal parts, the radiation resistance is good, the high and low temperature resistance is good, and no thermal control measure is required; therefore, the scheme has better space adaptability and reliability.
Drawings
FIG. 1 is a schematic diagram of a high aspect ratio deployment mechanism, in a collapsed state, suitable for use in a space environment, according to a preferred embodiment of the present invention;
FIG. 2 is a schematic diagram of a high aspect ratio deployment mechanism suitable for use in a space environment, in accordance with a preferred embodiment of the present invention, shown in a deployed state;
FIG. 3 shows a schematic view of a coiled state of a ribbon spring;
fig. 4 shows a schematic view of a fully expanded state of the ribbon spring.
The reference numbers illustrate:
1-upper structural plate, 2-limiting sleeve, 3-winding drum, 4-ribbon spring, 5-lower structural plate, 51-guide sleeve, 6-load mounting plate and 61-frustum.
Detailed Description
The invention is explained in more detail below with reference to the figures and examples. The features and advantages of the present invention will become more apparent from the description.
As shown in fig. 1 and 2, the present invention provides a high-expansion-ratio deployment mechanism suitable for space environment, which comprises an upper structural plate 1, two sets of stop collars 2, two sets of winding drums 3, two sets of ribbon springs 4, and a load mounting plate 6; wherein the content of the first and second substances,
the upper structural plate 1 is fixed on the detector, so that the whole unfolding mechanism is fixedly connected with the detector;
the limiting sleeve 2 is fixed below the upper structural plate 1 and is a circular sleeve with an opening on one side, a cylindrical circumferential structure on the limiting sleeve plays a limiting role, the tail end of the cylindrical circumferential structure is connected with a drooping straight baffle, and the two straight baffles are both positioned at the outer side end of the limiting sleeve 2;
the two groups of winding drums 3 are respectively positioned in the two limiting sleeves 2, and the two groups of winding drums 3 are driven by a motor to rotate in a linkage manner to synchronously drive the two groups of strip-shaped springs 4 to wind and release;
two sets of band spring 4 one end are fixed on reel 3, and the end that stretches out is connected with load mounting panel 6, drives load mounting panel 6 and rises and descend: when the winding drum 3 winds the strip-shaped spring 4, the load mounting plate 6 moves linearly in the closing direction; when the reel 3 releases the band spring 4, the load mounting plate 6 moves linearly in the unwinding direction; when the reel is unfolded in place, the position of the mechanism is locked by the positioning moment of the driving motor of the reel 3;
the load mounting plate 6 is used for the execution unit of the load task such as a sampler.
In the present invention, as shown in fig. 3 and 4, the large expansion ratio deployment mechanism suitable for space environment has two strip springs 4 as core components, and the strip springs are open cylindrical thin shells with certain length, and can realize bending and flattening movements under the action of elastic force generated by self deformation. The cross section of the strip-shaped spring 4 is arc-shaped, and the diameter and the arc length of the arc can be designed according to specific bearing characteristics; it can be wound into a cylinder shape and accommodated in a small space; can be completely unfolded into a rod shape and can bear axial load.
Because the cross section of the strip-shaped spring 4 is arc-shaped and is not a complete circle, the torsional rigidity of the single strip-shaped spring 4 along the center line of the single strip-shaped spring is weak, and the torsional capacity is poor. The two groups of the strip springs 4 and the load mounting plate 6 are symmetrically mounted, and when the load mounting plate 6 bears torsional load, the strip springs 4 are prevented from rotating along the center line of the strip springs, so that the torsional capacity of the mechanism at the load mounting plate 6 is greatly improved.
In the invention, the cylindrical circumferential structure is arranged on the limiting sleeve 2, and the limiting cylindrical surface of the limiting sleeve 2 and the winding drum 3 are coaxially arranged during assembly. When the band spring 4 wound on the reel 3 moves in the radial direction of the reel 3, the stop collar 2 restrains the reel 3 within a fixed diameter range. When the band spring 4 is unfolded and bears the axial load, the stop sleeve 2 limits the expansion of the band spring 4 along the radial direction of the winding drum 3, so that the axial bearing capacity of the band spring 4 is improved.
The straight baffle on the stop collar 2 is less with the terminal opening that forms of cylindrical circumference structure, and through the guide effect of opening and straight baffle when banded spring 4 expandes, it is perpendicular with the installation face of last structural slab 1 when guaranteeing banded spring 4 to expand, avoids banded spring 4 to follow self central line gyration simultaneously, has improved the torsional rigidity of deployment mechanism.
In the invention, the unfolding mechanism also comprises a lower structural plate 5 below the limiting sleeve 2, the lower structural plate 5 and the upper structural plate 1 are rigidly fixed, a non-closed annular longitudinal through hole is formed in the lower structural plate 5, the ribbon spring 4 can freely slide up and down in the longitudinal through hole, and the extending end of the ribbon spring 4 is connected to the load mounting plate 6 through the longitudinal through hole.
From the above, the longitudinal through hole on the lower structural plate 5 provides support for the side surface of the ribbon spring 4, so that the stability of the ribbon spring 4 is enhanced, the torsional rigidity of the unfolding mechanism is also improved, and the development of the work of the execution unit on the load mounting plate 6 is facilitated.
Further, a cylindrical guide sleeve 51 is arranged below the lower structural plate 5 around the longitudinal through hole, the inner diameter of the guide sleeve is the outer diameter of the annular through hole, the guide sleeve 51 plays a role in guiding and limiting the band-shaped spring 4, the shaking degree of the band-shaped spring 4 during unfolding is reduced, and the unfolding stability is improved.
Furthermore, the end of the guide sleeve 51 is processed with a conical surface, which is narrow at the top and wide at the bottom;
a frustum 61 is arranged on the load mounting plate 6 corresponding to the guide sleeve 51, and the conical surface of the frustum 61 and the tail end of the guide sleeve 51 form frustum-conical seat matching; six degrees of freedom between the lower structural plate 5 and the load mounting plate 6 are restrained, and the high-rigidity characteristic in the furled state is realized. Due to the conical surface fit, when the band-shaped spring 4 is unlocked and unfolded, the load mounting plate 6 is easily separated from the lower structural plate 5, and the problem of blocking cannot occur.
Furthermore, a solid lubricant film (such as a molybdenum disulfide film) is disposed on the tapered surfaces of the frustum 61 and the guide sleeve 51 to prevent the frustum 61 and the guide sleeve 51 from being bonded.
The present invention has been described above in connection with preferred embodiments, but these embodiments are merely exemplary and merely illustrative. On the basis of the above, the invention can be subjected to various substitutions and modifications, and the substitutions and the modifications are all within the protection scope of the invention.
Claims (4)
1. A high-expansion-ratio unfolding mechanism suitable for a space environment is characterized by comprising an upper structural plate (1), two groups of limiting sleeves (2), two groups of winding drums (3), two groups of strip springs (4), a lower structural plate (5) below the limiting sleeves (2) and a load mounting plate (6); wherein the content of the first and second substances,
the upper structural plate (1) is fixed on the detector, and the whole unfolding mechanism is fixedly connected with the detector;
the limiting sleeve (2) is fixed below the upper structural plate (1) and is a circular sleeve with an opening on one side, a cylindrical circumferential structure on the limiting sleeve plays a limiting role, the tail end of the cylindrical circumferential structure is connected with a drooping straight baffle, and the two straight baffles are both positioned at the outer side end of the limiting sleeve (2);
the two groups of winding drums (3) are respectively positioned in the two limiting sleeves (2), and the two groups of winding drums (3) are driven by a motor to rotate in a linkage manner to synchronously drive the two groups of strip-shaped springs (4) to wind and release;
one end of each group of the band-shaped springs (4) is fixed on the winding drum (3), and the extending end of each group of the band-shaped springs is connected with the load mounting plate (6) to drive the load mounting plate (6) to ascend and descend; the cross section of the strip-shaped spring (4) is arc-shaped, the strip-shaped spring can be wound around the winding drum (3) to form a cylinder, is stored in the limiting sleeve (2), can be completely unfolded to form a rod shape and bears axial load; the two groups of strip springs (4) are symmetrically arranged with the load mounting plate (6);
the lower structural plate (5) and the upper structural plate (1) are rigidly fixed, the lower structural plate (5) is provided with a non-closed annular longitudinal through hole, the width of the longitudinal through hole is less than the inherent cambered surface height of the ribbon spring (4), and the extending end of the ribbon spring (4) is connected to the load mounting plate (6) through the longitudinal through hole;
the load mounting plate (6) is used for executing units of load tasks.
2. The unfolding mechanism with high expansion ratio applicable to the space environment as claimed in claim 1, wherein a cylindrical guide sleeve (51) is installed around the longitudinal through hole below the lower structural plate (5), and the inner diameter of the guide sleeve is the outer diameter of the annular longitudinal through hole.
3. The deployment mechanism with high expansion ratio applicable to the space environment as claimed in claim 2, wherein a conical surface is machined at the end of the guide sleeve (51), and the conical surface is narrow at the top and wide at the bottom;
the load mounting plate (6) is provided with a frustum (61) corresponding to the guide sleeve (51), and the conical surface of the frustum (61) is matched with the tail end of the guide sleeve (51) to form a frustum-conical seat.
4. The deployment mechanism with high expansion ratio applicable to space environment as claimed in claim 3, wherein the conical surfaces of the frustum (61) and the guide sleeve (51) are provided with solid lubricating films.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911204254.4A CN110979742B (en) | 2019-11-29 | 2019-11-29 | High-expansion-ratio unfolding mechanism suitable for space environment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911204254.4A CN110979742B (en) | 2019-11-29 | 2019-11-29 | High-expansion-ratio unfolding mechanism suitable for space environment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110979742A CN110979742A (en) | 2020-04-10 |
| CN110979742B true CN110979742B (en) | 2021-12-07 |
Family
ID=70088565
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911204254.4A Active CN110979742B (en) | 2019-11-29 | 2019-11-29 | High-expansion-ratio unfolding mechanism suitable for space environment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110979742B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113291495B (en) * | 2021-06-25 | 2023-05-09 | 安徽应流集团霍山铸造有限公司 | Space mechanical arm based on flexible belt winding and unwinding and rigid-flexible conversion mechanism |
| CN114132528B (en) * | 2021-11-30 | 2023-12-19 | 北京卫星制造厂有限公司 | Flexible sail unfolding device |
| CN114435628A (en) * | 2022-01-12 | 2022-05-06 | 航天科工空间工程发展有限公司 | Space unfolding mechanism |
Family Cites Families (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5885367A (en) * | 1997-03-07 | 1999-03-23 | The United States Of America As Represented By The Secretary Of The Navy | Retractable thin film solar concentrator for spacecraft |
| FR2890454B1 (en) * | 2005-09-05 | 2007-10-12 | Alcatel Sa | DEPLOYABLE REFLECTIVE SHAPE OF TRIANGLE OF RELEAUX FOR A SPACE OBSERVATION INSTRUMENT |
| FR2933771B1 (en) * | 2008-07-11 | 2010-08-13 | Thales Sa | THERMALLY DEPLOYABLE TAPE METER AND DEPLOYABLE STRUCTURE COMPRISING SAID METER TAPE |
| CN105474780B (en) * | 2008-11-28 | 2012-10-31 | 上海宇航系统工程研究所 | The gathering of space film facility launches support tube |
| CN101607603B (en) * | 2009-07-13 | 2012-05-16 | 北京航空航天大学 | Thin-wall sleeve-type space development mechanism |
| US8770522B1 (en) * | 2010-12-01 | 2014-07-08 | The United States Of America As Represented By The Secretary Of The Air Force | Deployable space boom using bi-stable tape spring mechanism |
| GB2491822B (en) * | 2011-06-09 | 2015-12-02 | Rtl Materials Ltd | Coilable extendible member and methods |
| CN102501988B (en) * | 2011-09-26 | 2014-05-07 | 北京航空航天大学 | Telescopic space boom mechanism for supporting detection load |
| FR2998876B1 (en) * | 2012-12-05 | 2015-07-17 | Thales Sa | DEVICE FOR DEPLOYING AND REPLOYING A FLEXIBLE STRUCTURE, FLEXIBLE DEPLOYABLE STRUCTURE AND SATELLITE PROVIDED WITH SUCH A DEVICE |
| CN103482084B (en) * | 2013-08-29 | 2016-01-13 | 中国科学院长春光学精密机械与物理研究所 | A kind of novel Stretching of solar wings based on banded spring and supporting mechanism |
| US10071823B2 (en) * | 2013-11-27 | 2018-09-11 | Composite Technology Department, Inc. | Extendible boom |
| CN103693217A (en) * | 2013-12-06 | 2014-04-02 | 上海卫星工程研究所 | Retractable spatial stretching arm for satellite |
| US9580190B1 (en) * | 2014-06-16 | 2017-02-28 | Deployable Space Systems | Deployable root stiffness mechanism for tubular slit booms and method for increasing the bending and torsional stiffness of a tubular slit boom |
| FR3025498B1 (en) * | 2014-09-05 | 2017-12-08 | Thales Sa | DEPLOYABLE MAT WITH AUTONOMOUS SPONTANEOUS AND SATELLITE DEPLOYMENT COMPRISING AT LEAST ONE SUCH MAT |
| US10160555B2 (en) * | 2015-04-22 | 2018-12-25 | Composite Technology Development, Inc. | Multiple boom deployment |
| CN105370713A (en) * | 2015-11-20 | 2016-03-02 | 北京卫星制造厂 | Microsatellite unfolding mechanism |
| US10196817B2 (en) * | 2016-04-15 | 2019-02-05 | Composite Technology Development, Inc. | Locking mechanism for deployable booms |
| CN106005479B (en) * | 2016-06-07 | 2018-05-04 | 北京空间飞行器总体设计部 | Expanding unit is compared in a kind of big storage available for large deformation rod piece |
| CN106159409B (en) * | 2016-07-19 | 2019-01-22 | 中国科学院国家空间科学中心 | A kind of space thin-walled tubular extending arm expanding unit |
| CN106564621B (en) * | 2016-11-03 | 2018-10-02 | 中国科学院国家空间科学中心 | It is a kind of to realize the X-type section boom for collapsing expansion function |
| CN106584438B (en) * | 2017-01-24 | 2022-11-15 | 重庆大学 | Spacecraft prestress conical thin-wall three-rod parallel space unfolding mechanism |
| CN106864772B (en) * | 2017-01-24 | 2021-06-01 | 航天东方红卫星有限公司 | Spacecraft prestress thin-wall conical multi-rod parallel type space unfolding mechanism |
| CN109760855B (en) * | 2019-03-01 | 2020-10-20 | 哈尔滨工业大学 | Flexible space solar sailboard |
-
2019
- 2019-11-29 CN CN201911204254.4A patent/CN110979742B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN110979742A (en) | 2020-04-10 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110979742B (en) | High-expansion-ratio unfolding mechanism suitable for space environment | |
| CN205061052U (en) | Reel clamping device | |
| CN106602204B (en) | Sleeve type satellite antenna | |
| CN110405024A (en) | A kind of conformal device of metal tube section support | |
| CN108327932B (en) | A kind of human-like bar unilateral side driving mechanism with radial tightening | |
| CN102278439A (en) | Telescopic mechanical structure | |
| CN106864772B (en) | Spacecraft prestress thin-wall conical multi-rod parallel type space unfolding mechanism | |
| US2903901A (en) | Transmission | |
| CN201705878U (en) | Telescopic mechanical structure | |
| CN109638470A (en) | A kind of novel netted annular deployable antenna truss structure | |
| CN113895662B (en) | Failure satellite capturing docking device and method | |
| CN113650813B (en) | Active driving type large-scale film unfolding sail device | |
| CN113864403A (en) | Cover plate driving device of automobile | |
| CN111284685B (en) | Space retractable undercarriage emergency lowering device and method | |
| CN109625341A (en) | A kind of space articulation positioning device | |
| CN108767421B (en) | Space deployable antenna supporting mechanism | |
| CN108146576A (en) | The actuating device of the control drag-line of bicycle speed-varying unit | |
| CN210619689U (en) | Device for rolling strip rubber | |
| CN107035266A (en) | Electric pole structure | |
| CN109638404B (en) | Novel three-layer net-shaped deployable antenna truss structure with beam forming function | |
| CN113715042B (en) | Spiral coiling type multi-section flexible robot | |
| CN214879260U (en) | Manual rolling machine of adjustable reel size | |
| CN112875434A (en) | Drawing rolling machine | |
| CN107720591A (en) | A kind of wind spring drive-type steel wire rope winding mechanism based on assembly pulley row's rope | |
| CN207548502U (en) | A kind of rotation tensioning floating chuck |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |