CN213008814U - Zero-gravity unfolding test device for solar wing - Google Patents
Zero-gravity unfolding test device for solar wing Download PDFInfo
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- CN213008814U CN213008814U CN202021449846.0U CN202021449846U CN213008814U CN 213008814 U CN213008814 U CN 213008814U CN 202021449846 U CN202021449846 U CN 202021449846U CN 213008814 U CN213008814 U CN 213008814U
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- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 26
- 230000007246 mechanism Effects 0.000 claims abstract description 13
- 230000000712 assembly Effects 0.000 claims abstract description 12
- 238000000429 assembly Methods 0.000 claims abstract description 12
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 6
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 5
- 239000010959 steel Substances 0.000 claims abstract description 5
- 230000005484 gravity Effects 0.000 claims description 8
- 238000004088 simulation Methods 0.000 claims description 7
- 239000004411 aluminium Substances 0.000 claims description 4
- 230000003028 elevating effect Effects 0.000 claims description 4
- 238000013461 design Methods 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
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- 230000008569 process Effects 0.000 description 2
- 230000008901 benefit Effects 0.000 description 1
- 238000011981 development test Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000005486 microgravity Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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- 229910001220 stainless steel Inorganic materials 0.000 description 1
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Abstract
The utility model provides a solar wing zero-gravity unfolding test device, which comprises an unfolding frame system, a guide rail system and a hanging system, wherein the unfolding frame system comprises horizontal trusses and upright trusses, the horizontal trusses are connected with the tops of the upright trusses through reinforcing inclined ribs, and the bottom of each upright truss is provided with a movable adjusting ground foot assembly; the guide rail system comprises two pairs of longitudinal guide rails which are parallel to each other and four groups of transverse guide rail assemblies which are parallel to each other, the two pairs of longitudinal guide rails which are parallel to each other are connected with a horizontal truss through a plurality of transverse channel steel, each pair of longitudinal guide rails comprises a longitudinal guide rail I and a longitudinal guide rail II which are arranged in parallel, each group of transverse guide rail assemblies comprises a transverse guide rail and an aluminum hanging plate, the transverse guide rails and the aluminum hanging plates are connected through a plurality of fine adjustment mechanisms, two ends of each aluminum hanging plate are connected with the longitudinal guide rails on the corresponding sides through a longitudinal pulley, and the longitudinal pulleys on the same pair of. The utility model discloses bear load big, expand the space sufficient, expand frictional resistance little and the commonality is strong.
Description
Technical Field
The utility model belongs to the zero gravity of satellite sun wing expandes experimental field among the aerospace trade, especially, relates to a zero gravity of sun wing expandes test device.
Background
The zero-gravity unfolding mechanism of the satellite solar wing in the modern aerospace industry has a plurality of types, the traditional zero-gravity unfolding mechanism has a plurality of defects, some unfolding loads are small, some unfolding widths are narrow or the unfolding space is insufficient, and the like, so that a solar wing zero-gravity unfolding test device is necessary to be provided, the defect factors can be solved, and wider basic conditions and convenience are provided for the zero-gravity unfolding test of the satellite solar wing.
Disclosure of Invention
In view of this, the utility model aims at providing a zero gravity of solar wing expandes test device, bears the load big, expand that the space is sufficient, expansion frictional resistance value is little, the commonality is strong, can generally promote in the trade.
In order to achieve the above purpose, the technical scheme of the utility model is realized like this:
a solar wing zero-gravity unfolding test device comprises an unfolding frame system, a guide rail system and a hanging system, wherein the unfolding frame system comprises four groups of horizontal trusses and upright trusses, the upright trusses are uniformly arranged below the horizontal trusses, the horizontal trusses are connected with the tops of the upright trusses through reinforcing oblique ribs, and the bottom of each upright truss is provided with a movable adjusting foot assembly;
the guide rail system comprises two pairs of longitudinal guide rails which are parallel to each other and four groups of transverse guide rail assemblies which are parallel to each other, the two pairs of longitudinal guide rails which are parallel to each other are connected with a horizontal truss through a plurality of transverse channel steel, each pair of longitudinal guide rails comprises a longitudinal guide rail I and a longitudinal guide rail II which are arranged in parallel, each group of transverse guide rail assemblies comprises a transverse guide rail and an aluminum hanging plate, the transverse guide rails are arranged under the aluminum hanging plates, the transverse guide rails are connected with the aluminum hanging plates through a plurality of fine adjustment mechanisms, two ends of each aluminum hanging plate are connected with the longitudinal guide rails on the corresponding sides through a longitudinal pulley, and the longitudinal pulleys on the longitudinal guide rails I and the longitudinal guide rails II of the same pair;
the hanging system comprises an SADA (synthetic aperture radar) hanger and three inter-plate hangers, each transverse guide rail corresponds to a hanger, and the SADA hanger and the three inter-plate hangers are respectively connected with the transverse guide rails through a transverse pulley; the SADA hanging device is connected with a solar wing root hinge, and the solar wing plates are hung and connected between the plates.
Furthermore, the device also comprises a solar wing support vehicle, wherein the solar wing support vehicle is arranged on one side of the unfolding frame system, a simulation wall is arranged on the solar wing support vehicle, and the solar wing plate and the simulation wall are connected through a solar wing root hinge.
Further, vertical coaster includes vertical coaster body, four first deep groove ball bearings and linear bearing, and four two liang of a set of and install the upper portion at vertical coaster body through an axle respectively of four first deep groove ball bearings, the surface of four first deep groove ball bearings all with corresponding vertical guide surface contact, linear bearing installs the bottom at vertical coaster body, and installs the back shaft on linear bearing, respectively connects a connecting seat at the both ends of back shaft, is connected with the aluminium link plate through the connecting seat.
Furthermore, the transverse pulley comprises a transverse pulley body and four second deep groove ball bearings, the four second deep groove ball bearings are arranged on the upper portion of the transverse pulley body in a group in pairs and are respectively installed on the upper portion of the transverse pulley body through a shaft, the outer surfaces of the four second deep groove ball bearings are in surface contact with the transverse guide rail, and the bottom of the transverse pulley body is connected with a corresponding hanger.
Further, the inter-plate hanging and the SADA hanging are identical in structure and respectively comprise a hanging rod, a turn buckle, a spring scale, a universal ball joint and a connecting piece which are sequentially connected from top to bottom, the connecting piece hung between the plates is a connecting plate, a connecting hanging point is arranged on the connecting plate, and the connecting piece hung on the SADA is an SADA hanging point.
Further, fine-tuning includes screw thread post, lower screw thread post and internal thread sleeve, the internal thread sleeve sets up between last screw thread post and lower screw thread post, goes up the screw thread post from last to passing down behind the aluminium link plate with internal thread muffjoint, lower screw thread post from supreme passing behind the cross guide rail with internal thread muffjoint.
Further, but movable regulation lower margin subassembly includes a plurality of casters and two hand elevating system of universal bulb, and a plurality of casters evenly distributed is around stand truss bottom, the hand elevating system of universal bulb includes universal bulb seat, screw-nut subassembly and hand round, the bottom at the lead screw of screw-nut subassembly is installed to universal bulb seat, hand round is fixed at the top of the lead screw of screw-nut subassembly, and the bottom at the stand truss is fixed to the nut of screw-nut subassembly.
Furthermore, the expansion frame system is of a ball rod splicing type truss structure or is formed by splicing and building aluminum profiles.
Compared with the prior art, zero gravity of solar wing expandes test device have following advantage:
1. the device adopts the arrangement mode of double guide rails on each side and staggered longitudinal pulleys for the arrangement mode of the longitudinal guide rails, so that the arrangement can greatly meet the requirement of the spacing between the small solar wing furling plates; the transverse guide rail is connected with the aluminum hanging plate through the fine adjustment mechanism to form a transverse guide rail assembly, so that the bearing capacity of a hanging system is enhanced, the design value of the unfolding span is up to 1.9 m, the unfolding requirement of the solar wing plate with larger load and larger size is met, and the arrangement mode and the design provide sufficient rigidity and unfolding space for the solar wing plates with different types, loads and appearance sizes;
2. the arrangement of the longitudinal guide rail and the transverse guide rail is as follows: the hanging system is characterized by comprising two pairs of longitudinal guide rails which are parallel to each other and a plurality of groups of transverse guide rails which are parallel to each other, wherein a mounting interface with the hanging system is provided by a pulley, so that the hanging system can move transversely and longitudinally along the guide rail system in the unfolding process;
3. the pulley and the guide rail are arranged, namely the pulley adopts 4 deep groove ball bearings which are symmetrically distributed on two sides of the guide rail after polishing, the friction resistance value is extremely small, the linear bearing eliminates the problem of insufficient installation parallelism of the longitudinal guide rail, and the potential risk of possible expansion clamping stagnation is solved; the whole structure only has extremely small friction resistance value of the expansion test, so that the smooth operation of the expansion test is ensured;
4. the design of the hanging points and the hanging among the plates ensures that the height and the span of the hanging points hung among the plates can be adjusted so as to meet the hanging requirements of different solar wing models, and the universal ball can save energy to ensure that the hanging points slightly rotate, thereby ensuring the smooth operation of the development test;
5. the movable adjustable anchor assembly is arranged to realize indoor movement of the whole expansion frame, vertical deviation of column assembly can be eliminated through the universal ball head type anchor, and horizontal regularity of truss installation is guaranteed.
Drawings
The accompanying drawings, which form a part hereof, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention without undue limitation. In the drawings:
fig. 1 is a schematic structural view of a solar wing zero-gravity unfolding test device according to an embodiment of the present invention;
FIG. 2 is a schematic view of the arrangement of the rail system and the hanger system;
FIG. 3 is a schematic view of the arrangement of the longitudinal rail and the longitudinal trolley;
FIG. 4 is a schematic structural view of a cross-rail assembly;
FIG. 5 is a schematic view of the longitudinal block;
FIG. 6 is a schematic view of the lateral block;
FIG. 7 is a schematic view of the hanging structure between plates;
FIG. 8 is a schematic view of the connection of a horizontal truss, a reinforcing diagonal rib and an upright truss;
FIG. 9 is a schematic structural view of a movably adjustable anchor assembly;
FIG. 10 is a schematic structural view of another movably adjustable anchor assembly;
fig. 11 is a structural schematic diagram of an expansion frame system built by aluminum profiles.
Description of reference numerals:
1-extending frame system, 2-guide rail system, 3-hanging system, 4-horizontal truss, 5-upright truss, 6-reinforced diagonal rib, 7-movable adjusting foot component, 8-longitudinal guide rail, 9-transverse guide rail component, 10-transverse channel steel, 11-longitudinal guide rail I, 12-longitudinal guide rail II, 13-transverse guide rail, 14-aluminum hanging plate, 15-fine adjustment mechanism, 16-SADA hanging, 17-inter-plate, 18-transverse pulley, 19-solar wing root hinge, 20-solar wing plate, 21-solar wing bracket vehicle, 22-simulation wall, 23-longitudinal pulley body, 24-first deep groove ball bearing, 25-linear bearing, 26-support shaft, 27-connecting seat, 28-longitudinal pulley, 29-transverse pulley body, 30-second deep groove ball bearing, 31-universal ball head hand-operated lifting mechanism, 32-suspender, 33-basket bolt, 34-spring scale, 35-universal ball joint, 36-connecting plate, 37-connecting hoisting point, 38-SADA hoisting point, 39-universal caster and 40-Fuma wheel.
Detailed Description
It should be noted that, in the present invention, the embodiments and features of the embodiments may be combined with each other without conflict.
The present invention will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
As shown in fig. 1-11, a solar wing zero-gravity unfolding test device comprises an unfolding frame system 1, a guide rail system 2 and a hanging system 3, wherein the unfolding frame system 1 provides a rigid platform for the guide rail system 2 and the hanging system 3, in order to make the self reach force balance and keep better rigidity as much as possible, the guide rail system 2 is used for providing a low-friction track moving guide rail for a solar wing unfolding test process, and the hanging system 3 is used for connecting with a solar wing plate and a solar wing root hinge at corresponding positions and properly adjusting the length of the solar wing to meet different height requirements of the solar wing; the unfolding frame system 1 comprises four groups of horizontal trusses 4 and upright trusses 5, wherein the upright trusses 5 are uniformly arranged below the horizontal trusses 4, the horizontal trusses 4 are connected with the tops of the upright trusses 5 through reinforcing inclined ribs 6, and the bottom of each upright truss 5 is provided with a movable adjusting foot assembly 7; the arrangement of the reinforcing inclined ribs 6 enhances the bearing capacity of the truss expansion frame;
the guide rail system 2 comprises two pairs of longitudinal guide rails 8 which are parallel to each other and four groups of transverse guide rail assemblies 9 which are parallel to each other, the two pairs of longitudinal guide rails 8 which are parallel to each other are connected with the horizontal truss 4 through a plurality of transverse channel steel 10, each pair of longitudinal guide rails 8 comprises a longitudinal guide rail I11 and a longitudinal guide rail II 12 which are arranged in parallel, each group of transverse guide rail assemblies 9 comprises a transverse guide rail 13 and an aluminum hanging plate 14, the transverse guide rails 13 are arranged right below the aluminum hanging plates 14, the transverse guide rails 13 are connected with the aluminum hanging plates 14 through a plurality of fine adjustment mechanisms 15, two ends of each aluminum hanging plate 14 are connected with the longitudinal guide rail on the corresponding side through a longitudinal pulley 28, and the longitudinal pulleys 28 on the longitudinal guide rails I and the longitudinal guide rails II of the same pair;
the hanging system 3 comprises an SADA (synthetic aperture radar) hanger 16 and three inter-plate hangers 17, each transverse guide rail 13 corresponds to one hanger, and the SADA hanger 16 and the three inter-plate hangers 17 are respectively connected with the transverse guide rails 13 through a transverse pulley 18; the SADA hanger 16 is connected with a solar wing root hinge 19, and the inter-plate hanger 17 is connected with a solar wing plate 20.
The zero-gravity unfolding test device for the solar wing further comprises a solar wing support vehicle 21, wherein the solar wing support vehicle 21 is arranged on one side of the unfolding frame system 1, a simulation wall 22 is arranged on the solar wing support vehicle 21, and a solar wing plate 20 and the simulation wall 22 are connected through a solar wing root hinge 19. The test device of this application is solar wing support and solar wing root hinge, all belongs to prior art, no longer gives unnecessary details here.
The longitudinal pulley 28 comprises a longitudinal pulley body 23, four first deep groove ball bearings 24 and a linear bearing 25, wherein the four first deep groove ball bearings 24 are pairwise in a group and are respectively installed on the upper portion of the longitudinal pulley body 23 through an axle, the outer surfaces of the four first deep groove ball bearings 24 are in surface contact with corresponding longitudinal guide rails, the linear bearing 25 is installed at the bottom of the longitudinal pulley body 23, a supporting axle 26 is installed on the linear bearing 25, two ends of the supporting axle 26 are respectively connected with a connecting seat 27, and the connecting seats are connected with the aluminum hanging plate 14 through the connecting seats 27.
The transverse pulley 18 comprises a transverse pulley body 29 and four second deep groove ball bearings 30, the four second deep groove ball bearings 30 are arranged on the upper portion of the transverse pulley body 29 in a group in pairs and are respectively mounted on one shaft, the outer surfaces of the four second deep groove ball bearings 30 are in surface contact with the transverse guide rail 13, and the bottom of the transverse pulley body 29 is connected with a corresponding hanger.
The inter-plate hanger 17 and the SADA hanger 16 have the same structure, and both comprise a hanging rod 32, a turn buckle 33, a spring balance 34, a universal ball joint 35 and a connecting piece which are sequentially connected from top to bottom, the connecting piece of the inter-plate hanger 17 is a connecting plate 36, a connecting hanging point 37 is arranged on the connecting plate 36, and the connecting piece of the SADA hanger 16 is an SADA hanging point 38. The basket bolt 33 is a stainless steel closed basket, so that the vertical height of the hanger can be finely adjusted, and the adaptability of the hanger solar wing plate in height is improved; the universal ball joint 35 can enable the lifting point to slightly rotate around the ball joint, so that the smoothness of the unfolding test is ensured; wherein be equipped with two connection hoisting points on the connecting plate 36 of hanging 17 between the board, and the span of two connection hoisting points is adjustable, adapts to the solar wing panel of different specifications and expandes the test demand, and the connection hoisting point is prevented that static POM switching links to each other through black, guarantees the insulating demand of whole test device and solar wing panel.
The fine adjustment mechanism 15 comprises an upper threaded column, a lower threaded column and an internal threaded sleeve, the internal threaded sleeve is arranged between the upper threaded column and the lower threaded column, the upper threaded column penetrates through the aluminum hanging plate 14 from top to bottom and then is connected with the internal threaded sleeve, and the lower threaded column penetrates through the transverse guide rail 13 from bottom to top and then is connected with the internal threaded sleeve.
The movable adjusting anchor assembly 7 comprises a plurality of universal casters 39 and two universal ball head hand-operated lifting mechanisms 31, the plurality of universal casters 39 are uniformly distributed around the bottom of the stand truss 5, the universal ball head hand-operated lifting mechanisms 31 comprise universal ball head bases, lead screw nut assemblies and hand-operated wheels, the bottoms of the lead screws of the lead screw nut assemblies are installed on the universal ball head bases, the hand-operated wheels are fixed at the tops of the lead screws of the lead screw nut assemblies, and nuts of the lead screw nut assemblies are fixed at the bottoms of the stand truss. The arrangement enhances the transfer convenience of the truss expansion frame, the travelling universal caster is arranged at the bottom of the truss, in addition, the universal ball head hand-operated lifting mechanism 31 ensures that the truss can be finely adjusted in height, and the universal ball head type ground feet can enable the truss to stably and vertically land, so that a more complete environment is provided for the installation of the guide rail, and the reliability of the expansion test is ensured; the horseback wheels 40 can also be directly used as the running truss feet.
The expansion frame system 1 is of a ball bar splicing type truss structure or is formed by splicing and building aluminum profiles, and the ball bar splicing type truss is large in bearing load and high in stress strength.
When the device is used, the SADA hanger is connected with the B shaft part of the solar wing, the hangers between the plates are directly connected with the solar wing plates, the solar wing is hung on the expansion frame system, the gravity of the solar wing is overcome by each hanger, and the hangers between the plates and the SADA hanger are hung on the transverse guide rail and can freely move on the transverse guide rail, and the transverse guide rail can move along the longitudinal guide rail, so that each solar wing can freely move in two directions in the horizontal direction, and the solar wing can be freely expanded under the zero gravity condition.
The zero-gravity unfolding test device for the solar wing mainly bears the gravity of the suspended solar wing, provides a microgravity environment for unfolding the solar wing, and can be popularized to all industries with zero-gravity unfolding test requirements and similar industries.
The above description is only a preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. The utility model provides a zero gravity of solar wing expandes test device which characterized in that: the device comprises an expansion frame system (1), a guide rail system (2) and a hanging system (3), wherein the expansion frame system (1) comprises four groups of horizontal trusses (4) and upright trusses (5), the upright trusses (5) are uniformly arranged below the horizontal trusses (4), the horizontal trusses (4) are connected with the tops of the upright trusses (5) through reinforcing oblique ribs (6), and the bottom of each upright truss (5) is provided with a movable adjusting ground foot assembly (7);
the guide rail system (2) comprises two pairs of longitudinal guide rails (8) which are parallel to each other and four groups of transverse guide rail assemblies (9) which are parallel to each other, the two pairs of longitudinal guide rails (8) which are parallel to each other are connected with the horizontal truss (4) through a plurality of transverse channel steel (10), each pair of longitudinal guide rails (8) comprises a longitudinal guide rail I (11) and a longitudinal guide rail II (12) which are arranged in parallel, each group of transverse guide rail assemblies (9) comprises a transverse guide rail (13) and an aluminum hanging plate (14), the transverse guide rails (13) are arranged under the aluminum hanging plate (14), and the transverse guide rail (13) is connected with the aluminum hanging plate (14) through a plurality of fine adjustment mechanisms (15), two ends of the aluminum hanging plate (14) are respectively connected with the longitudinal guide rail on the corresponding side through a longitudinal pulley (28), longitudinal pulleys (28) on a first longitudinal guide rail and a second longitudinal guide rail of the same pair of longitudinal guide rails are arranged in a staggered mode;
the hanging system (3) comprises an SADA (SADA) hanger (16) and three inter-plate hangers (17), each transverse guide rail (13) corresponds to one hanger, and the SADA hanger (16) and the three inter-plate hangers (17) are respectively connected with the transverse guide rails (13) through a transverse pulley (18); the SADA hanger (16) is connected with a solar wing root hinge (19), and the inter-plate hanger (17) is connected with a solar wing plate (20).
2. The solar wing zero-gravity unfolding test device according to claim 1, characterized in that: the device also comprises a solar wing support vehicle (21), wherein the solar wing support vehicle (21) is arranged on one side of the unfolding frame system (1), a simulation wall (22) is arranged on the solar wing support vehicle (21), and a solar wing plate (20) and the simulation wall (22) are connected through a solar wing root hinge (19).
3. The solar wing zero-gravity unfolding test device according to claim 2, characterized in that: vertical coaster (28) are including vertical coaster body (23), four first deep groove ball bearings (24) and linear bearing (25), and four two liang a set of and install the upper portion at vertical coaster body (23) through an axle respectively in four first deep groove ball bearings (24), the surface of four first deep groove ball bearings (24) all with the surface contact of corresponding vertical guide rail, linear bearing (25) are installed in the bottom of vertical coaster body (23), and install back shaft (26) on linear bearing (25), respectively connect a connecting seat (27) at the both ends of back shaft (26), are connected with aluminium link plate (14) through connecting seat (27).
4. The solar wing zero-gravity unfolding test device according to claim 3, characterized in that: the transverse pulley (18) comprises a transverse pulley body (29) and four second deep groove ball bearings (30), wherein every two of the four second deep groove ball bearings (30) are in a group and are respectively installed on the upper portion of the transverse pulley body (29) through a shaft, the outer surfaces of the four second deep groove ball bearings (30) are in surface contact with the transverse guide rail (13), and the bottom of the transverse pulley body (29) is connected with a corresponding hanger.
5. The solar wing zero-gravity unfolding test device according to claim 4, wherein: the inter-plate hanger (17) and the SADA hanger (16) are identical in structure and respectively comprise a hanger rod (32), a turn buckle (33), a spring scale (34), a universal ball joint (35) and a connecting piece which are sequentially connected from top to bottom, the connecting piece of the inter-plate hanger (17) is a connecting plate (36), a connecting hanging point (37) is arranged on the connecting plate (36), and the connecting piece of the SADA hanger (16) is an SADA hanging point (38).
6. The solar wing zero-gravity unfolding test device according to claim 1, characterized in that: fine-tuning (15) are including last screw thread post, lower screw thread post and internal thread sleeve, the internal thread sleeve sets up between last screw thread post and lower screw thread post, goes up the screw thread post from last to passing down behind aluminium link plate (14) with internal thread muffjoint, lower screw thread post from supreme cross guide (13) back and internal thread muffjoint down.
7. The solar wing zero-gravity unfolding test device according to claim 1, characterized in that: but movable regulation lower margin subassembly (7) include a plurality of casters (39) and two hand elevating system of universal bulb (31), and a plurality of casters (39) evenly distributed are around stand truss (5) bottom, the hand elevating system of universal bulb (31) are including universal bulb seat, screw-nut subassembly and hand round, the bottom at the lead screw of screw-nut subassembly is installed to universal bulb seat, the top at the lead screw of screw-nut subassembly is fixed to hand round, and the bottom at the stand truss is fixed to the nut of screw-nut subassembly.
8. The solar wing zero-gravity deployment test apparatus of any one of claims 1-7, wherein: the expansion frame system (1) is of a ball bar splicing type truss structure or is formed by splicing and building aluminum profiles.
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| CN202021449846.0U CN213008814U (en) | 2020-07-21 | 2020-07-21 | Zero-gravity unfolding test device for solar wing |
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| CN202021449846.0U CN213008814U (en) | 2020-07-21 | 2020-07-21 | Zero-gravity unfolding test device for solar wing |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113470477A (en) * | 2021-08-24 | 2021-10-01 | 贵州航天乌江机电设备有限责任公司 | Unfolding device for simulating weightlessness |
| CN114056608A (en) * | 2021-11-30 | 2022-02-18 | 北京卫星制造厂有限公司 | Counter weight mechanism and zero-gravity unfolding experimental device |
| CN114590422A (en) * | 2022-05-09 | 2022-06-07 | 天津航天机电设备研究所 | A three-rocker arm test device for composite motion microgravity deployment of space mechanism |
| CN114644283A (en) * | 2022-02-17 | 2022-06-21 | 航天科工空间工程发展有限公司 | A solar wing ground deployment test stand |
| CN115636115A (en) * | 2022-10-28 | 2023-01-24 | 哈尔滨工业大学 | Solar wing secondary unfolding gravity unloading test device |
| CN115924139A (en) * | 2022-12-28 | 2023-04-07 | 贵州航天乌江机电设备有限责任公司 | Unfolding device for folding wing of aircraft |
| CN116678650A (en) * | 2023-05-05 | 2023-09-01 | 上海宇航系统工程研究所 | Horizontal unfolding test system of stretching mechanism |
| CN118270257A (en) * | 2024-06-03 | 2024-07-02 | 中国人民解放军国防科技大学 | Foldable movable zero gravity simulation support truss comprehensive test system |
| CN119527588A (en) * | 2025-01-21 | 2025-02-28 | 沈阳中科新宇空间智能装备有限公司 | A gravity unloading mechanism for ground deployment of flexible solar wing |
| CN119840871A (en) * | 2025-02-19 | 2025-04-18 | 北京卫星制造厂有限公司 | Microgravity simulation device for scroll type flexible solar wing |
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| CN113470477A (en) * | 2021-08-24 | 2021-10-01 | 贵州航天乌江机电设备有限责任公司 | Unfolding device for simulating weightlessness |
| CN114056608A (en) * | 2021-11-30 | 2022-02-18 | 北京卫星制造厂有限公司 | Counter weight mechanism and zero-gravity unfolding experimental device |
| CN114644283A (en) * | 2022-02-17 | 2022-06-21 | 航天科工空间工程发展有限公司 | A solar wing ground deployment test stand |
| CN114590422A (en) * | 2022-05-09 | 2022-06-07 | 天津航天机电设备研究所 | A three-rocker arm test device for composite motion microgravity deployment of space mechanism |
| CN114590422B (en) * | 2022-05-09 | 2022-07-29 | 天津航天机电设备研究所 | A three-rocker arm test device for composite motion microgravity deployment of space mechanism |
| CN115636115B (en) * | 2022-10-28 | 2024-04-16 | 哈尔滨工业大学 | Solar wing secondary unfolding gravity unloading test device |
| CN115636115A (en) * | 2022-10-28 | 2023-01-24 | 哈尔滨工业大学 | Solar wing secondary unfolding gravity unloading test device |
| CN115924139A (en) * | 2022-12-28 | 2023-04-07 | 贵州航天乌江机电设备有限责任公司 | Unfolding device for folding wing of aircraft |
| CN116678650A (en) * | 2023-05-05 | 2023-09-01 | 上海宇航系统工程研究所 | Horizontal unfolding test system of stretching mechanism |
| CN118270257A (en) * | 2024-06-03 | 2024-07-02 | 中国人民解放军国防科技大学 | Foldable movable zero gravity simulation support truss comprehensive test system |
| CN119527588A (en) * | 2025-01-21 | 2025-02-28 | 沈阳中科新宇空间智能装备有限公司 | A gravity unloading mechanism for ground deployment of flexible solar wing |
| CN119840871A (en) * | 2025-02-19 | 2025-04-18 | 北京卫星制造厂有限公司 | Microgravity simulation device for scroll type flexible solar wing |
| CN119840871B (en) * | 2025-02-19 | 2025-12-12 | 北京卫星制造厂有限公司 | Microgravity simulation device for scroll type flexible solar wing |
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