CN116692038B - Solar wing span opening mechanism capable of adjusting angle - Google Patents
Solar wing span opening mechanism capable of adjusting angle Download PDFInfo
- Publication number
- CN116692038B CN116692038B CN202310831030.6A CN202310831030A CN116692038B CN 116692038 B CN116692038 B CN 116692038B CN 202310831030 A CN202310831030 A CN 202310831030A CN 116692038 B CN116692038 B CN 116692038B
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- 230000007246 mechanism Effects 0.000 title claims abstract description 56
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 8
- 238000009434 installation Methods 0.000 claims description 6
- 239000000758 substrate Substances 0.000 claims description 6
- 229910052742 iron Inorganic materials 0.000 claims description 4
- 239000013013 elastic material Substances 0.000 claims description 3
- 238000010586 diagram Methods 0.000 description 5
- 230000006835 compression Effects 0.000 description 4
- 238000007906 compression Methods 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 230000001174 ascending effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000001179 sorption measurement Methods 0.000 description 1
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
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
- B64G1/443—Photovoltaic cell arrays
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/50—Photovoltaic [PV] energy
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Photovoltaic Devices (AREA)
Abstract
The invention relates to the technical field of solar wings, in particular to a solar wing unfolding mechanism with an adjustable angle, which comprises a pressing plate, solar wings, a unfolding mechanism and a base plate, wherein the solar wings are arranged at the lower end of the pressing plate, the solar wings and the unfolding mechanism are arranged at the upper end of the base plate, the left end and the right end of the solar wings are respectively provided with the unfolding mechanism, the unfolding mechanism consists of a plurality of first unfolding plates, second unfolding plates and connecting columns, the first unfolding plates are positioned at the left end of the second unfolding plates, the two ends of the first unfolding plates are connected with the middle end of the first unfolding plates in a staggered manner through the connecting columns to form a scissor structure for unfolding the solar wings, one side of the bottom end of each first unfolding plate and one side of the top end of each second unfolding plate are respectively arranged in the base plate and the pressing plate in a sliding manner, a control column is rotatably arranged at the rear end of the first unfolding plate positioned at the lowermost end, a limiting part is fixedly arranged at the rear end of each control column, and an electromagnetic part is attached to the rear end of each limiting part; the invention can change the movement gesture of the unfolding mechanism by controlling the electromagnet and simultaneously adjust the angle of the solar wing.
Description
Technical Field
The present invention relates to a solar wing unfolding mechanism, and more particularly to a solar wing unfolding mechanism with adjustable angle.
Background
In the long-term running process of the spacecraft, the solar wing is mainly relied on to provide electric energy for the spacecraft. The solar wing utilizes the battery piece attached to the solar wing to convert light energy into electric energy for a spacecraft, and the working mode of the solar wing is as follows: when the spacecraft is launched, the solar wing is in a furled state, so that occupied volume is reduced; reliable locking is needed to bear the vibration working condition of the ascending section; after the spacecraft enters the orbit, the solar wing is in an open state to generate electricity; the deployed state requires locking to increase the deployment fundamental frequency.
At present, most of solar wingspan of domestic spacecraft adopts a scheme of one-time passive deployment in place and locking, namely, solar sailboards are deployed to a specified position by means of power of a driving spring in a hinge, and then the solar sailboards are fixed at the specified position by means of a locking device in the hinge, so that the existing solar wing still has certain defects for special application scenes of relatively small deployment area, repeated folding and deployment function requirements and high requirements on weight and folding envelope.
However, the existing solar wing opening mechanism generally only has the function of unfolding the solar wing, cannot meet the requirement of the solar wing working mode, has the special application scene of repeated folding and unfolding function requirement and very high requirement on weight and folding envelope for the spacecraft, and still has certain defects.
Disclosure of Invention
The present invention has been made in view of the above problems, and an object of the present invention is to fulfill the requirements of the solar wing for compacting, expanding, locking and collapsing functions by changing the form of the expanding mechanism, and the present invention is to achieve the above objects by the following technical solutions:
the utility model provides a but angle regulation's solar wing expansion mechanism, includes pressure strip, solar wing, expansion mechanism, base plate, and solar wing is installed to the pressure strip lower extreme, solar wing and expansion mechanism all install in the base plate upper end, both ends all are provided with expansion mechanism about the solar wing, expansion mechanism comprises a plurality of first expansion plates, the second expansion plates, the spliced pole, first expansion plates is located the left end of second expansion plates, and its both ends and well end pass through spliced pole staggered connection and form the scissors structure and be used for expanding solar wing, bottom one side of first expansion plates and top one side of second expansion plates slide respectively and set up in base plate and pressure strip, the first expansion plate rear end rotatable mounting who is located the lower extreme has the control post, the rear end fixed of control post is provided with the locating part, the rear end laminating of locating part is provided with the electromagnetic member, electromagnetic member and the locating part is absorbed mutually, the spacing shifting chute of electromagnetic member has all been seted up to the left and right sides of base plate, the front end of shifting chute all has seted up first rotation groove and second rotation groove, be used for expanding angle adjustment motor, the front end of base plate is connected with the driving lever of opening angle, the driving lever is connected with the front end of opening angle adjustment base plate, the driving lever is provided with the driving lever.
Preferably, the inner sides of the moving grooves are provided with limiting grooves matched with the control columns so that the control columns can move, and the front ends of the limiting grooves are through grooves.
Preferably, both ends all are provided with the installation department about the pressure strip, and installation department front end below outside all is provided with the installed part, and installation department lower extreme inboard all is provided with the sliding tray, and pressure strip front end evenly distributed has four connecting portions.
Preferably, the solar wing consists of a plurality of flexible solar cell blankets, and connecting plates are fixedly arranged on the left side and the right side of each flexible solar cell blanket.
Preferably, the front ends of the two uppermost connecting plates and the flexible solar cell blanket are fixedly provided with upper connecting pieces, one ends of the upper connecting pieces are fixedly connected with the lower ends of the corresponding mounting parts, and the connecting plates and the flexible solar cell blanket which are adjacent up and down are connected in a zigzag manner through middle connecting pieces.
Preferably, the front ends of the two connecting plates and the flexible solar cell blanket which are positioned at the lowest part are fixedly provided with lower connecting pieces, one ends of the lower connecting pieces are fixedly connected with the base plate, and the upper connecting pieces, the middle connecting pieces and the lower connecting pieces are all made of elastic materials and are positioned at the same vertical position.
Preferably, the limiting piece is arranged on one side of the electromagnetic piece in an arc-shaped fit mode.
Preferably, the upper end of the middle part of the first unfolding plate is fixedly provided with a first locking piece, the first locking piece extends towards the direction of the second unfolding plate, a slotted hole is formed in the rear end of the first locking piece, an electrified demagnetizing magnet is arranged in the slotted hole, the upper end of the middle part of the second unfolding plate is fixedly provided with a second locking piece, the second locking piece extends towards the direction of the first unfolding plate, the upper end of the second locking piece is provided with an iron sheet, and the first locking piece and the second locking piece are mutually adsorbed.
Preferably, the rear end of the second expansion plate at the uppermost end extends towards the first expansion plate, and the sliding piece is arranged in the sliding groove and can slide back and forth relative to the sliding groove.
Preferably, the control groove is formed in the front end of the second unfolding plate at the lowest end, and the driving rod is fixedly connected with the control grooves in the two unfolding mechanisms.
The invention has the beneficial effects that:
1. according to the invention, the expansion mechanism is used for controlling the pressing plate to press downwards, so that the problems of vibration scattering of the solar wing and the like can be prevented when the spacecraft is launched, and the solar wing is comprehensively pressed through the pressing plate, so that the pressure born by the solar wing is uniformly distributed, and the damage to the solar wing is prevented.
2. According to the invention, the unfolding mechanism is driven by the driving motor so as to fully unfold the solar wing, and after the solar wing is unfolded, two electrified demagnetizing magnets in the unfolding mechanism attract each other so as to keep the unfolding form of the unfolding mechanism, thereby improving the unfolding fundamental frequency of the solar wing.
3. According to the solar cell panel, after the solar wings are unfolded, the angle of the solar wings can be changed according to the position of the spacecraft by driving the motor, so that sunlight is always directly irradiated onto the solar cell panel, and the photoelectric conversion efficiency of the solar cell is improved.
4. According to the invention, the moving gesture of the unfolding mechanism can be changed by controlling the electromagnet, and the functions of unfolding and folding the solar wing can be simultaneously completed, so that the device can meet the requirements of special application scenes of the solar wing.
5. The solar wing compression, expansion, locking and folding function requirements can be met only by changing the form of the expansion mechanism, a complicated power system and a control system are not needed, and meanwhile, the solar wing compression, expansion, locking and folding function requirement is realized, and the solar wing compression, expansion, locking and folding device is simple in structure and compact in structure, so that the control cost and the emission cost of the solar wing are reduced.
Drawings
Fig. 1 is a schematic structural diagram of an overall mechanism provided by the present invention.
Fig. 2 is an exploded view of the overall structure provided by the present invention.
Fig. 3 is a schematic diagram of a compacting plate structure at a first view angle according to the present invention.
Fig. 4 is a schematic diagram of a compacting plate structure at a second view angle according to the present invention.
Fig. 5 is a schematic view of a solar wing structure according to the present invention.
Fig. 6 is a schematic structural diagram of a right deployment mechanism under a first view angle provided by the present invention.
Fig. 7 is a front view of the right deployment mechanism in a first view.
Fig. 8 is a schematic structural diagram of a right deployment mechanism according to the second aspect of the present invention.
Fig. 9 is a schematic view of a substrate structure in a solar spanwise state according to the present invention.
Fig. 10 is an enlarged view of the structure a in fig. 9 according to the present invention.
Fig. 11 is a top view of a substrate structure in a spanwise state of a sun provided by the present invention.
Reference numerals illustrate:
100, a compression plate; 110. a mounting part; 111. a mounting member; 112. a sliding groove; 120. a connection part; 200. a solar wing; 210. a connecting plate; 211. an upper connecting piece; 212. a middle connecting piece; 213. a lower connecting piece; 300. a deployment mechanism; 310. a first deployment panel; 311. a mounting column; 312. a control column; 313. a limiting piece; 314. an electromagnetic member; 315. a first locking member; 320. a second deployment panel; 321. a slider; 322. a control groove; 323. a second locking member; 330. a connecting column; 400. a substrate; 401. a moving groove; 402. a limit groove; 403. a first rotating groove; 404. a second rotating groove; 410. a limiting plate; 420. a driving motor; 421. and a driving rod.
Detailed Description
The preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings, but the present invention may be embodied in various forms, and thus the present invention is not limited to the embodiments described below, and in addition, components not connected to the present invention will be omitted from the drawings for the sake of more clarity of description of the present invention;
as shown in fig. 1-4, an adjustable angle solar wing deployment mechanism, comprising: the solar wing device comprises a compacting plate 100, a solar wing 200, an unfolding mechanism 300 and a base plate 400;
the compacting plate 100 is positioned at the upper end of the integral mechanism, and the lower end of the compacting plate is provided with a solar wing 200;
the left and right ends of the solar wing 200 are provided with unfolding mechanisms 300;
the solar wing 200 and the unfolding mechanism 300 are both installed at the upper end of the base plate 400;
mounting parts 110 are arranged at the left end and the right end of the compacting plate 100;
mounting pieces 111 are arranged on the outer sides below the front ends of the two mounting parts 110;
sliding grooves 112 are formed in the inner sides of the lower ends of the two mounting parts 110;
four connecting parts 120 are uniformly distributed at the front end of the compacting plate 100;
as shown in fig. 1, 4 and 5, the solar wing 200 is composed of a plurality of flexible solar cell blankets, and connection plates 210 are fixedly arranged on the left and right sides of each flexible solar cell blanket;
the upper connecting pieces 211 are fixedly arranged at the front ends of the two connecting plates 210 and the flexible solar cell blanket which are positioned at the uppermost part;
one end of the upper connector 211 is fixedly connected with the lower end of the corresponding mounting part 110;
the connecting plates 210 and the flexible solar cell blankets which are adjacent to each other up and down are connected in a zigzag manner through the middle connecting piece 212;
the front ends of the two connecting plates 210 and the flexible solar cell blanket positioned at the lowest part are fixedly provided with lower connecting pieces 213, and one end of each lower connecting piece 213 is fixedly connected with the substrate 400;
the upper connecting piece 211, the middle connecting piece 212 and the lower connecting piece 213 are all made of elastic materials and are positioned at the same vertical position, and when the solar wing 200 is pressed tightly, the upper connecting piece 211, the middle connecting piece 212 and the lower connecting piece 213 are in a normal state;
as shown in fig. 4 and 6-8, the deployment mechanism 300 is composed of a plurality of first deployment plates 310, second deployment plates 320, and connection posts 330;
the first expansion plate 310 is located at the left end of the second expansion plate 320, and two ends and the middle end thereof are connected in a staggered manner through a connecting column 330 to form a scissor structure;
the front end of the first unfolding plate 310 at the uppermost end is provided with a mounting column 311 extending towards the direction of the second unfolding plate 320;
the mounting post 311 is rotatably mounted on the mounting member 111;
the rear end of the first unfolding plate 310 at the lowest end is rotatably provided with a control column 312;
a circular-arc-shaped limiting piece 313 is fixedly arranged at the rear end of the control column 312, and an iron sheet is arranged on the rear end surface of the limiting piece 313;
the rear end of the limiting piece 313 is provided with an electromagnetic piece 314 in an attaching mode, namely when the electromagnetic piece 314 is electrified, the electromagnetic piece 314 can adsorb the limiting piece 313;
a first locking member 315 is fixedly arranged at the upper end of the middle part of the first expansion plate 310 at the front part, and the first locking member 315 extends towards the direction of the second expansion plate 320;
a slot is formed at the rear end of the first locking member 315, and an electrified demagnetizing magnet is arranged inside the slot;
the rear end of the second unfolding plate 320 at the uppermost end is provided with a sliding piece 321 extending towards the direction of the first unfolding plate 310;
the sliding piece 321 is installed inside the sliding groove 112 and can slide back and forth relative to the sliding groove;
a control groove 322 is formed in the front end of the second unfolding plate 320 at the lowest end;
a second locking member 323 is fixedly arranged at the upper end of the middle part of the second unfolding plate 320 at the rear part, and the second locking member 323 extends towards the direction of the first unfolding plate 310;
the upper end of the second locking piece 323 is provided with an iron sheet, that is, when the solar wing 200 is unfolded, the first locking piece 315 and the second locking piece 323 are mutually adsorbed;
as shown in fig. 6 and fig. 9-11, the left and right sides of the substrate 400 are provided with moving grooves 401 for moving the limiting member 313 and the electromagnetic member 314;
the inner sides of the two moving grooves 401 are provided with limiting grooves 402 for the control column 312 to move, and the front ends of the limiting grooves 402 are through grooves;
the front ends of the two moving grooves 401 are respectively provided with a first rotating groove 403 and a second rotating groove 404, and the limiting groove 402 is disconnected in the first rotating groove 403 so as to allow the unfolding mechanism 300 to rotate;
the upper ends of the two moving grooves 401 are respectively provided with a limiting plate 410 for limiting the vertical movement of the limiting piece 313 and the electromagnetic piece 314;
the limiting plates 410 are fixedly arranged at the upper end of the base plate 400 and positioned at two sides of the moving groove 401, and are disconnected at the first rotating groove 403;
a driving motor 420 is fixedly arranged at the right side of the front end of the base plate 400;
the output end of the driving motor 420 is connected with a driving rod 421, and the driving rod 421 is fixedly connected with the control grooves 322 in the two unfolding mechanisms 300;
working principle:
when the solar wing is in the folded state: the limiting piece 313, the electromagnetic piece 314 and the sliding piece 321 are respectively positioned at the rear ends of the moving groove 401 and the sliding groove 112, the compressing plate 100 compresses the solar wing 200, and the locking shaft of the driving motor 420 is controlled to ensure the compressing effect on the solar wing 200.
When the solar wing needs to be unfolded: the electromagnetic member 314 is electrified and drives the driving rod 421 to reversely rotate through the driving motor 420, so that the first unfolding plate 310 and the second unfolding plate 320 are driven to unfold, the pressing plate 100 is driven to upwards lift up to unfold the solar wing 200, and the limiting member 313, the electromagnetic member 314 and the sliding member 321 respectively move towards the front ends of the moving groove 401 and the sliding groove 112 when the solar wing 200 unfolds until the solar wing 200 is completely unfolded, at the moment, the limiting member 313 leaves the moving groove 401 and is positioned at the upper end of the first rotating groove 403, the electromagnetic member 314 is still positioned in the moving groove 401, and the first locking member 315 adsorbs the second locking member 323 to keep the unfolded posture of the solar wing 200.
When the solar wing needs to rotate in angle: the electromagnetic member 314 is stopped to be energized, and the whole unfolding mechanism 300 is controlled to rotate by the driving motor 420, so that the solar wing 200 is driven to rotate by the compacting plate 100, and sunlight is directly irradiated onto the solar wing 200, thereby increasing the photoelectric conversion efficiency.
When the solar wing needs to be folded: the driving motor 420 drives the unfolding mechanism 300 to return, the limiting piece 313 is attached to the electromagnetic piece 314, the electromagnetic piece 314 is electrified with the first locking piece 315, the electromagnetic piece 314 adsorbs the limiting piece 313, the first locking piece 315 releases the adsorption to the second locking piece 323, and then the driving motor 420 rotates positively, so that the driving rod 421 drives the first unfolding plate 310, the second unfolding plate 320, the limiting piece 313, the electromagnetic piece 314 and the sliding piece 321 to return, and meanwhile, the upper connecting piece 211, the middle connecting piece 212 and the lower connecting piece 213 control the connecting plate 210 to return so as to drive the solar wing 200 to fold, and the solar wing 200 is compressed through the compressing plate 100.
Claims (10)
1. The utility model provides a solar wing expansion mechanism of adjustable angle, includes pinch plate (100), solar wing (200), expansion mechanism (300), base plate (400), solar wing (200) are installed to pinch plate (100) lower extreme, solar wing (200) and expansion mechanism (300) all install in base plate (400) upper end, its characterized in that: the solar wing (200) is provided with unfolding mechanisms (300) at the left and right ends, the unfolding mechanisms (300) are composed of a plurality of first unfolding plates (310), second unfolding plates (320) and connecting columns (330), the first unfolding plates (310) are positioned at the left ends of the second unfolding plates (320), two ends and the middle ends of the first unfolding plates are connected in a staggered manner through the connecting columns (330) to form a scissor structure for unfolding the solar wing (200), one side of the bottom end of each first unfolding plate (310) and one side of the top end of each second unfolding plate (320) are respectively arranged in a base plate (400) and a compressing plate (100) in a sliding manner, the rear end of each first unfolding plate (310) positioned at the bottommost end is rotatably provided with a control column (312), the rear end of each control column (312) is fixedly provided with a limiting piece (313), the rear end of each limiting piece (313) is provided with an electromagnetic piece (314), after the electromagnetic piece (314) is electrified, the electromagnetic piece (314) is attracted with the limiting piece (313), the left and right sides of the base plate (400) are respectively provided with a moving groove (401) for limiting the electromagnetic piece (314), the front end (401) is provided with a first rotating groove (400) for rotating the front end (400), the front end (400) of the front end (400) is provided with a rotating mechanism (400), the output end of the driving motor (420) is connected with a driving rod (421), and the driving rod (421) is connected with the two unfolding mechanisms (300).
2. The adjustable angle solar wing deployment mechanism of claim 1, wherein: limiting grooves (402) matched with the control columns (312) are formed in the inner sides of the moving grooves (401) for the control columns (312) to move, and the front ends of the limiting grooves (402) are through grooves.
3. The adjustable angle solar wing deployment mechanism of claim 1, wherein: both ends all are provided with installation department (110) about clamp plate (100), and installation department (110) front end below outside all is provided with installed part (111), and installation department (110) lower extreme inboard all is provided with sliding tray (112), and clamp plate (100) front end evenly distributed has four connecting portion (120).
4. An adjustable angle solar wing deployment mechanism according to claim 3, wherein: the solar wing (200) is composed of a plurality of flexible solar cell blankets, and connecting plates (210) are fixedly arranged on the left side and the right side of each flexible solar cell blanket.
5. The adjustable angle solar wing deployment mechanism of claim 4, wherein: the front ends of the two connecting plates (210) and the flexible solar cell blanket which are positioned at the uppermost part are fixedly provided with upper connecting pieces (211), one end of each upper connecting piece (211) is fixedly connected with the lower end of the corresponding mounting part (110), and the connecting plates (210) and the flexible solar cell blanket which are adjacent up and down are connected in a zigzag manner through middle connecting pieces (212).
6. The adjustable angle solar wing deployment mechanism of claim 5, wherein: the front ends of the two connecting plates (210) and the flexible solar cell blanket which are positioned at the lowest part are fixedly provided with lower connecting pieces (213), one ends of the lower connecting pieces (213) are fixedly connected with the substrate (400), and the upper connecting pieces (211), the middle connecting pieces (212) and the lower connecting pieces (213) are made of elastic materials and are positioned at the same vertical position.
7. The adjustable angle solar wing deployment mechanism of claim 1, wherein: the limiting piece (313) is arranged on one side of the electromagnetic piece (314) in an arc-shaped joint mode.
8. The adjustable angle solar wing deployment mechanism of claim 1, wherein: the upper end of the middle part of the first unfolding plate (310) is fixedly provided with a first locking piece (315), the first locking piece (315) extends towards the second unfolding plate (320), a slotted hole is formed in the rear end of the first locking piece (315), an electrified demagnetizing magnet is arranged in the slotted hole, the upper end of the middle part of the second unfolding plate (320) is fixedly provided with a second locking piece (323), the second locking piece (323) extends towards the first unfolding plate (310), the upper end of the second locking piece (323) is provided with an iron sheet, and the first locking piece (315) and the second locking piece (323) are mutually adsorbed.
9. An adjustable angle solar wing deployment mechanism according to claim 3, wherein: the rear end of the second unfolding plate (320) positioned at the uppermost end is provided with a sliding piece (321) extending towards the direction of the first unfolding plate (310), and the sliding piece (321) is arranged in the sliding groove (112) and can slide back and forth relative to the sliding groove.
10. The adjustable angle solar wing deployment mechanism of claim 1, wherein: the front end of the second unfolding plate (320) at the lowest end is provided with a control groove (322), and the driving rod (421) is fixedly connected with the control grooves (322) in the two unfolding mechanisms (300).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310831030.6A CN116692038B (en) | 2023-07-07 | 2023-07-07 | Solar wing span opening mechanism capable of adjusting angle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310831030.6A CN116692038B (en) | 2023-07-07 | 2023-07-07 | Solar wing span opening mechanism capable of adjusting angle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116692038A CN116692038A (en) | 2023-09-05 |
| CN116692038B true CN116692038B (en) | 2024-01-30 |
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ID=87825801
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310831030.6A Active CN116692038B (en) | 2023-07-07 | 2023-07-07 | Solar wing span opening mechanism capable of adjusting angle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116692038B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH01127498A (en) * | 1987-11-12 | 1989-05-19 | Space Commun Res Corp | Expansion truss structure |
| CN106915479A (en) * | 2015-12-28 | 2017-07-04 | 中国科学院沈阳自动化研究所 | A kind of deployable solar wing of cube |
| CN113086248A (en) * | 2021-03-26 | 2021-07-09 | 中国空间技术研究院 | Flexible solar wing with scissor type unfolding mechanism |
| CN113291494A (en) * | 2021-07-12 | 2021-08-24 | 长光卫星技术有限公司 | High-expansion-ratio flexible solar wing unfolding mechanism |
| CN114030657A (en) * | 2021-10-28 | 2022-02-11 | 上海宇航系统工程研究所 | Solar wing device capable of being repeatedly folded and unfolded and using method |
| CN218703980U (en) * | 2022-11-15 | 2023-03-24 | 重庆开拓卫星科技有限公司 | Solar wing capable of being unfolded in two-way sliding mode |
-
2023
- 2023-07-07 CN CN202310831030.6A patent/CN116692038B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH01127498A (en) * | 1987-11-12 | 1989-05-19 | Space Commun Res Corp | Expansion truss structure |
| CN106915479A (en) * | 2015-12-28 | 2017-07-04 | 中国科学院沈阳自动化研究所 | A kind of deployable solar wing of cube |
| CN113086248A (en) * | 2021-03-26 | 2021-07-09 | 中国空间技术研究院 | Flexible solar wing with scissor type unfolding mechanism |
| CN113291494A (en) * | 2021-07-12 | 2021-08-24 | 长光卫星技术有限公司 | High-expansion-ratio flexible solar wing unfolding mechanism |
| CN114030657A (en) * | 2021-10-28 | 2022-02-11 | 上海宇航系统工程研究所 | Solar wing device capable of being repeatedly folded and unfolded and using method |
| CN218703980U (en) * | 2022-11-15 | 2023-03-24 | 重庆开拓卫星科技有限公司 | Solar wing capable of being unfolded in two-way sliding mode |
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| Publication number | Publication date |
|---|---|
| CN116692038A (en) | 2023-09-05 |
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