CN113291494A - High-expansion-ratio flexible solar wing unfolding mechanism - Google Patents
High-expansion-ratio flexible solar wing unfolding mechanism Download PDFInfo
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- CN113291494A CN113291494A CN202110783411.2A CN202110783411A CN113291494A CN 113291494 A CN113291494 A CN 113291494A CN 202110783411 A CN202110783411 A CN 202110783411A CN 113291494 A CN113291494 A CN 113291494A
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- 238000007906 compression Methods 0.000 claims description 25
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- 238000003825 pressing Methods 0.000 claims description 18
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 12
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- 238000010008 shearing Methods 0.000 claims description 5
- 230000000903 blocking effect Effects 0.000 claims description 4
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- 239000000463 material Substances 0.000 abstract description 5
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
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Abstract
The invention discloses a high-expansion-contraction-ratio flexible solar wing spreading mechanism which comprises a bottom plate, a scissor rod assembly, a top plate and a solar carpet assembly, wherein the bottom plate is provided with a plurality of through holes; the unfolding mechanism also comprises a driving component integrated on the bottom plate; the driving assembly is provided with a driving motor and a transmission gear, and the transmission gear extends to the upper part of the bottom plate; the driving assembly is in transmission connection with the scissor rod assembly through the transmission gear and drives the scissor rod assembly to unfold so as to drive the solar blanket assembly to unfold. The unfolding mechanism has the advantages of simple structure, high reliability and small mass; most structural members in the mechanism are made of aerospace-grade hard aluminum alloy and carbon fiber composite materials, the mechanical structure is simple and not numerous, and lightweight design improvement is made on each structural member on the premise of ensuring the strength and vibration requirements; the unfolding mechanism has the advantages of low manufacturing cost, low material price, simple structure and convenient manufacture, and the scissor rod assembly drives the solar blanket assembly to move, so that the folding mechanism has the advantages of light weight, small folding volume, large unfolding span and high unfolding and folding ratio.
Description
Technical Field
The invention relates to the technical field of spaceflight, in particular to a high-expansion-ratio flexible solar wing unfolding mechanism suitable for a folding flexible solar wing.
Background
The solar wing spreading mechanism is an important component of the solar wing and is mainly used for bundling, spreading and supporting the solar carpet. The unfolding mechanism has the functions of bundling the solar blanket to meet the rigidity requirement and the emission envelope in the satellite emission stage, ensuring that the solar blanket or other single machines on the satellite are not damaged due to severe shaking, realizing smooth unfolding and locking of the solar blanket after the solar blanket enters the orbit, providing support for the solar blanket in the unfolded state, ensuring that the solar blanket and each part of the satellite are not hooked and interfered in the unfolding process, and meeting the requirements of the modal fundamental frequency and the precision after the solar blanket is unfolded and locked.
The flexible solar wing has the characteristics of furling envelope and obvious nonlinearity of weight and unfolding area thereof, and is particularly suitable for ultra-high power spacecrafts. Due to the limitation of solar cell arrays and material technologies, the flexible solar wing designed and manufactured in the early stage has complex configuration, higher cost and larger weight. With the innovative development of the new solar cell array and the material technology, the specific power of the solar wing is significantly improved, so if the area of the solar wing is reduced under the condition of unchanged power requirement, the unfolding mechanism needs to be developed in the direction of reducing weight and cost, simplifying structure and improving the reliability of the mechanism.
In the prior art, the publication numbers are: chinese patent application CN105501468A entitled "flexible solar wing spreading mechanism for space station" discloses a flexible solar wing spreading mechanism for space station. Referring to fig. 1 and 2, the unfolding mechanism is a folding hinge column type mechanism, and comprises a bottom storage box 1, a storage cylinder 2-1, a storage copper cover 2-2, an extending arm unfolding mechanism 5, a top storage box 4 and an airfoil 6. The longitudinal beam and the transverse frame of the folding hinged column type unfolding mechanism are rigid structures and cannot store elastic potential energy, so that the power for unfolding and folding the hinged columns comes from the motor. The folding and hinging column can be regarded as being formed by overlapping a plurality of same units, a unit section is formed between two adjacent transverse frames 5-1, the transverse frames are connected with the longitudinal beam 5-2 through hinges, an elbow-shaped folding hinge A is designed in the middle of the longitudinal beam, and each side surface of the folding and hinging column is provided with a diagonal member 5-3 for keeping the unfolding mechanism stable and providing extra rigidity. The unfolding of the hinge-folding columns is carried out in sequence according to the unit sections, the motor drives the upper transverse frame 5-1 to move upwards, the upper transverse frame drives the longitudinal beam 5-2 to move through the hinge hinges, so that the elbow-shaped hinge A is opened, and when the elbow-shaped hinge A is completely opened, the longitudinal beam 5-2 is completely unfolded, so that the unit sections are unfolded.
Through careful study, the unfolding mechanism disclosed in the prior art has a complex mechanical structure, is easy to damage, occupies a large volume when the unfolding mechanism is in a folded state, and has poor reliability due to excessive parts.
Finally, based on the above technical problems, those skilled in the art need to develop a novel solar span opening mechanism with high expansion ratio, large expansion size, light weight, and small furling size, which is suitable for very large power spacecraft and has complicated structure, large mass, and high cost, and most of the flexible solar span opening mechanisms in the prior art.
Disclosure of Invention
The invention aims to provide a flexible solar wing spreading mechanism with small mass, large spreading and folding volume ratio, simple structure, high reliability and low cost and high spreading and folding ratio.
In order to achieve the above purpose, the invention provides the following technical scheme:
the invention relates to a high-expansion-ratio flexible solar wing unfolding mechanism, which comprises:
a base plate;
a scissor lever assembly integrated with the base plate; and
a solar carpet assembly connected to the scissor bar assembly;
the deployment mechanism further comprises:
a drive assembly integrated with the base plate;
the driving assembly is provided with a driving motor and a transmission gear which is in transmission with the driving motor, and the transmission gear extends to the upper part of the bottom plate;
the driving assembly is in transmission connection with the scissor rod assembly through the transmission gear and drives the scissor rod assembly to unfold so as to drive the solar carpet assembly to unfold.
Further, the driving assembly includes:
the driving motor is integrated at the bottom of the bottom plate through a motor mounting seat;
a driving torque output gear connected to an output end of the driving motor;
the driving torque output gear is meshed with the transmission gear and drives the transmission gear to rotate.
Further, the scissors assembly comprises:
a bottom scissor lever disposed proximate the bottom plate;
a middle scissor lever hinged to the bottom scissor lever; and
a top scissor lever hinged to the upper end of the middle scissor lever;
the two bottom scissor rods are symmetrically arranged on two sides of the bottom plate;
the bottom scissor lever on one side is connected with the transmission gear to be driven to rotate through the transmission gear, and the bottom scissor lever on the other side is driven to rotate through a bottom synchronizing device which is driven to rotate through the transmission gear;
the two bottom shearing fork rods synchronously rotate;
the deployment mechanism further comprises:
a top plate located at the top;
the top scissor rods are arranged close to the top plate, the number of the top scissor rods is two, and the two top scissor rods are symmetrically arranged;
the number of the middle scissor rods is multiple, the middle scissor rods are arranged in a crossed manner, and the crossed positions of the middle scissor rods are hinged;
the middle scissor rods close to the bottom scissor rods are hinged with the bottom scissor rods on two sides respectively;
the middle scissor rods close to the top scissor rods are hinged with the top scissor rods on two sides respectively.
Further, the transmission gear is integrated on the bottom plate through a gear seat;
the bottom synchronization device includes:
the bottom synchronizing wheel is meshed with the transmission gear, and the number of teeth and the modulus of the bottom synchronizing wheel are the same as those of the transmission gear;
the bottom driving belt wheel is coaxially arranged with the bottom synchronizing wheel and synchronously rotates with the bottom synchronizing wheel; and
the bottom driven belt wheel is assembled on the bottom plate through a gear seat;
the bottom driving belt wheel and the bottom driven belt wheel are in transmission through a bottom transmission belt;
the bottom scissor rod close to one side of the bottom driven belt wheel is coaxial with the bottom driven belt wheel and is driven to rotate through the bottom driven belt wheel.
Furthermore, the two top scissor rods are driven to rotate by a top synchronizing device;
the top synchronization device includes:
the top driving synchronous gear is integrated on the top plate, and the top shearing fork rod on one side is coaxially and fixedly connected with the top driving synchronous gear and drives the top driving synchronous gear to rotate;
a top driven synchronizing gear meshed with the top driving synchronizing gear;
the top driving belt wheel is coaxially arranged with the top driven synchronous gear and synchronously rotates with the top driven synchronous gear; and
a top driven pulley disposed on an opposite side of the top plate;
the top driving belt wheel and the top driven belt wheel are in transmission through a top transmission belt;
the top scissor rod on the other side is coaxially and fixedly connected with the top driven belt wheel and is driven to rotate through the top driven belt wheel.
Further, a bottom locking assembly is integrated between the bottom scissor rod and the bottom plate;
a top locking assembly is integrated between the top scissor rod and the top plate;
the bottom locking assembly comprises:
a bottom compression spring and a bottom locking pin embedded in the bottom plate;
the end part of the bottom scissor lever is provided with a bottom scissor lever locking hole matched with the bottom locking pin;
the top locking assembly comprises:
a top compression spring and a top locking pin embedded in the top scissor lever;
a top shear fork rod locking hole matched with the top locking pin is formed in the top plate;
a stop plate is arranged at the position, close to the end part, of the top scissor rod;
when the scissor lever assembly is in the accommodating state, the bottom compression spring and the bottom locking pin are compressed into the bottom plate by the bottom scissor lever, and the top compression spring and the top locking pin are compressed into the top scissor lever by the blocking plate;
when the scissor lever assembly is in an unfolded state, the bottom scissor lever locking hole of the bottom scissor lever rotates to face the bottom locking pin, and the bottom locking pin is pushed into the bottom scissor lever locking hole through the bottom compression spring and locks the bottom scissor lever; the top locking pin of the top scissor lever rotates to face the top scissor lever locking hole of the top plate, and the top locking pin is pushed into the top scissor lever locking hole through the top compression spring and locks the top scissor lever.
Further, the solar carpet assembly comprises:
a bus bar disposed proximate to the base plate;
a solar blanket platen disposed adjacent to the top plate; and
a flexible solar panel integrated between the bus plate and the solar carpet pressure plate;
when the solar blanket component is in a storage state, the flexible solar panel is folded between the bus board and the solar blanket pressing board;
the solar blanket pressing plate is connected with the top plate through a solar blanket connecting rod;
a solar blanket tensioning device is integrated between the solar blanket connecting rod and the solar blanket pressing plate, and when the solar blanket assembly is in an unfolded state, the flexible solar panel keeps the unfolded degree through the solar blanket tensioning device.
Furthermore, one end of the solar blanket tensioning device is connected with the solar blanket connecting rod, and the other end of the solar blanket tensioning device is connected with the solar blanket pressing plate through a solar blanket connecting joint.
Further, the unfolding mechanism also comprises a pressing device;
when the unfolding mechanism is in a storage state, the storage degree is kept through the pressing device;
the pressing device comprises:
a titanium rod assembly located on the top plate; and
a cutter located on the base plate;
the titanium rod assembly is in threaded connection with the cutter through a titanium rod, and the cutter can be cut off after being electrified so as to release the constraint on the unfolding mechanism.
Further, the backplane is configured as a satellite star.
In the technical scheme, the flexible solar wing spreading mechanism with the high spreading ratio provided by the invention has the following beneficial effects:
the unfolding mechanism has the advantages of simple structure, high reliability and small mass; most structural members in the mechanism are made of aerospace-grade hard aluminum alloy and carbon fiber composite materials, the mechanical structure is simple and not numerous, and lightweight design improvement is made on each structural member on the premise of ensuring the strength and vibration requirements; the unfolding mechanism has the advantages of low manufacturing cost, low material price, simple structure and convenient manufacture, and the scissor rod assembly drives the solar carpet assembly to move, so that the folding mechanism has the advantages of small folding volume, long unfolding distance and high unfolding and folding ratio.
The unfolding mechanism has small mass, and can effectively reduce the mass ratio of the whole mechanism of the flexible solar wing; the expansion ratio is large, so that the envelope size of the folded state of the flexible solar blanket can be greatly reduced, and the envelope size of the folded state of the whole satellite can be further reduced; the whole structure is simple, the assembly is convenient, the launching period can be effectively shortened, and a large amount of launching cost is saved.
Drawings
In order to more clearly illustrate the embodiments of the present application or technical solutions in the prior art, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments described in the present invention, and other drawings can be obtained by those skilled in the art according to the drawings.
Fig. 1 is a first schematic structural view of a solar wing spreading mechanism in the prior art;
fig. 2 is a second schematic structural view of a solar wing spreading mechanism in the prior art;
FIG. 3 is an isometric view of a high aspect ratio flexible solar wing spreading mechanism provided by an embodiment of the present invention;
fig. 4 is a schematic structural diagram of a deployed state of a high-aspect ratio flexible solar wing unfolding mechanism according to an embodiment of the present invention;
fig. 5 is a schematic structural diagram of a driving assembly of a high-aspect ratio flexible solar wing unfolding mechanism according to an embodiment of the present invention;
fig. 6 is a schematic structural diagram of a synchronization device of a high-aspect ratio flexible solar wing spreading mechanism according to an embodiment of the present invention;
FIG. 7 is a cross-sectional view of a bottom locking assembly of a high aspect ratio flexible solar wing opening mechanism provided in accordance with an embodiment of the present invention;
FIG. 8 is a cross-sectional view of a top locking assembly of a high aspect ratio flexible solar wing opening mechanism provided in accordance with an embodiment of the present invention;
fig. 9 is a schematic structural diagram of a pressing device of a high-aspect ratio flexible solar wing spreading mechanism provided by an embodiment of the invention;
fig. 10 is an enlarged view of the solar carpet tensioning device of the high-aspect ratio flexible solar span unfolding mechanism according to the embodiment of the invention.
Description of reference numerals:
1. a base plate; 2. a top plate; 3. a solar blanket connecting rod; 4. a scissor lever assembly; 5. a drive assembly; 6. a synchronization device; 7. a bottom locking assembly; 8. a top locking assembly; 9. a pressing device; 10. a solar blanket tensioning device; 11. a solar carpet component;
201. a top scissor lever locking hole;
401. a bottom scissor lever; 402. a middle scissor lever; 403. a top scissor lever;
501. a drive motor; 502. a drive torque output gear; 503. a transmission gear;
601. a bottom synchronizing gear; 602. a bottom drive pulley; 603. a bottom drive belt; 604. a bottom driven pulley; 605. a top driven pulley; 606. a top drive belt; 607. a top drive pulley; 608. a top driven synchronizing gear; 609. a top active synchronizing gear; 610. a gear seat;
701. a bottom locking pin; 702. a bottom compression spring;
801. a top locking pin; 802. a top compression spring;
901. a titanium rod assembly; 902. a cutter;
1001. a constant force spring; 1002. the solar blanket is connected with the joint;
1101. a solar blanket press plate; 1102. a flexible solar panel; 1103. a bus bar;
40101. bottom scissor lever locking holes.
Detailed Description
In order to make the technical solutions of the present invention better understood, those skilled in the art will now describe the present invention in further detail with reference to the accompanying drawings.
See fig. 3-10;
the invention relates to a high-expansion-ratio flexible solar wing unfolding mechanism, which comprises:
a base plate 1;
a scissor rod assembly 4 integrated with the base plate 1; and
a solar carpet assembly 11 connected with the scissor bar assembly 4;
the deployment mechanism further comprises:
a drive assembly 5 integrated in the base plate 1;
the driving assembly 5 is provided with a driving motor 501 and a transmission gear 503 which is in transmission with the driving motor 501, and the transmission gear 503 extends to the upper part of the bottom plate 1;
the driving assembly 5 is in transmission connection with the scissors assembly 4 through the transmission gear 503 and drives the scissors assembly 4 to unfold so as to drive the solar carpet assembly 11 to unfold.
Specifically, the embodiment discloses a novel unfolding mechanism, which comprises a bottom plate 1, a scissor rod assembly 4, a solar carpet assembly 11 and a driving assembly 5 for driving the scissor rod assembly 4 to move; the driving motor 501 of the driving assembly 5 is used for providing power to drive the scissor lever assembly 4 to perform unfolding motion, and the solar carpet assembly 11 is unfolded along with the unfolding of the scissor lever assembly 4 because the solar carpet assembly 11 is connected with the scissor lever assembly 4.
Preferably, the driving assembly 5 of the present embodiment includes:
a driving motor 501 integrated at the bottom of the bottom plate 1 through a motor mounting seat;
a drive torque output gear 502 connected to an output end of the drive motor 501;
the driving torque output gear 502 meshes with the transmission gear 503 and drives the transmission gear 503 to rotate.
First, the composition of the driving assembly 5 is introduced, and the driving motor 501 is a power output part for unfolding motion; the driving motor 501 of the present embodiment is integrated at the bottom of the base plate 1 through a motor mounting seat, and in addition, a driving torque output gear 502 is connected to an output end of the driving motor 501, the driving torque output gear 502 rotates along with an output shaft of the driving motor 501, and at the same time, the driving module 5 has a transmission gear 503, the transmission gear 503 is engaged with the driving torque output gear 502 and rotates along with the driving torque output gear 502.
Preferably, the scissors assembly 4 of the present embodiment comprises:
a bottom scissor bar 401 disposed proximate to the bottom plate 1;
a middle scissor bar 402 hinged to the bottom scissor bar 401; and
a top scissor lever 403 hingedly connected to the upper end of the middle scissor lever 402;
the number of the bottom scissor rods 401 is two, and the two bottom scissor rods 401 are symmetrically arranged on two sides of the bottom plate 1;
the bottom scissor lever 401 on one side is connected with the transmission gear 503 so as to be driven to rotate through the transmission gear 503, and the bottom scissor lever 401 on the other side is driven to rotate through a bottom synchronization device which is driven to rotate through the transmission gear 503;
the two bottom scissor levers 401 rotate synchronously;
the deployment mechanism further comprises:
a top plate 2 at the top;
the top scissor rods 403 are arranged close to the top plate 2, two top scissor rods 403 are provided, and the two top scissor rods 403 are symmetrically arranged;
the number of the middle scissor rods 402 is multiple, the multiple middle scissor rods 402 are arranged in a crossed manner, and the crossed positions of the middle scissor rods 402 are hinged;
the middle scissor rods 402 close to the bottom scissor rods 401 are hinged with the bottom scissor rods 401 at the two sides respectively;
the middle scissor bar 402 adjacent to the top scissor bar 403 is hinged to the top scissor bars 403 on both sides, respectively.
The transmission gear 503 is integrated with the bottom plate 1 through a gear seat 610;
the bottom synchronization device includes:
the bottom synchronizing wheel 601 is meshed with the transmission gear 503, and the number of teeth and the modulus of the bottom synchronizing wheel 601 are the same as those of the transmission gear 503;
a bottom driving pulley 602 disposed coaxially with the bottom synchronizing wheel 601 and rotating synchronously with the bottom synchronizing wheel 601; and
a bottom driven pulley 605 fitted to the base plate 1 through a gear holder 610;
the bottom driving pulley 602 and the bottom driven pulley 605 are driven by a bottom driving belt 603;
the bottom scissor lever 401 on the side near the bottom driven pulley 605 is coaxial with the bottom driven pulley 605 and is driven to rotate by the bottom driven pulley 605.
The two top scissor rods 403 are driven to rotate by a top synchronizer;
the top synchronizer includes:
the top driving synchronizing gear 609 is integrated on the top plate 2, and the top shearing fork rod 403 on one side is coaxially and fixedly connected with the top driving synchronizing gear 609 and drives the top driving synchronizing gear 609 to rotate;
a top driven synchronizing gear 608 meshing with a top driving synchronizing gear 609;
a top driving pulley 607 coaxially arranged with the top driven synchronizing gear 608 and rotating in synchronization with the top driven synchronizing gear 608; and
a top driven pulley 605 disposed on the opposite side of the top plate 2;
the top driving pulley 607 and the top driven pulley 605 are driven by a top transmission belt 606;
the top scissor rod 403 on the other side is fixedly connected with the top driven pulley 605 coaxially and is driven to rotate by the top driven pulley 605.
The scissor lever assembly 4 and the specific construction of the assembly as a power transmission for the drive assembly 5 and the scissor lever assembly 4 are described in detail herein. First, the fork bar assembly 4 of the present embodiment is specifically divided into a bottom fork bar 401, a middle fork bar 402 and a top fork bar 403. The drive assembly 5 of this embodiment drives the bottom scissor lever 401 to move, and the bottom scissor lever 401 drives the top scissor lever 403 above to move through the middle scissor lever 402. Firstly, a driving motor 501 drives a transmission gear 503 to rotate through a driving torque output gear 502, and the transmission gear 503 and a bottom synchronous gear 601 have the same tooth number and modulus, so that an equal-ratio transmission gear set is formed. The bottom driving pulley 602 and the bottom synchronizing gear 601 of this embodiment are coaxially connected, so that the bottom synchronizing gear 601 drives the bottom driving pulley 602 to rotate together, and along with the rotation of the bottom driving pulley 602, the bottom driving pulley 604 on the other side is driven to rotate together through the bottom transmission belt 603, so that the bottom scissor levers 401 on both sides can synchronously rotate to realize the unfolding motion.
As the bottom scissor lever 401 rotates upward, it will drive the middle scissor lever 402 to rotate and assume an upward-spreading motion state, and finally the middle scissor lever 402 will also drive the top scissor lever 403 on the upper portion to rotate together, and the structure that ensures the top scissor levers 403 on both sides to rotate together is the top synchronizer.
Preferably, when the scissor levers are unfolded to a certain extent, the corresponding scissor levers need to be locked by using the locking assemblies, so as to maintain the state and position of the unfolded scissor lever assembly 4, and therefore, a bottom locking assembly 7 is integrated between the bottom scissor lever 401 and the bottom plate 1 in this embodiment;
a top locking assembly 8 is integrated between the top scissor rod 403 and the top plate 2;
the bottom lock assembly 7 includes:
a bottom compression spring 702 and a bottom locking pin 701 embedded in the bottom plate 1;
a bottom scissor lever locking hole 40101 matched with the bottom locking pin 701 is formed in the end of the bottom scissor lever 401;
the top lock assembly 8 includes:
a top compression spring 802 and a top locking pin 801 embedded within top scissor bar 403;
a top shear fork rod locking hole 201 matched with the top locking pin 801 is formed in the top plate 2;
the top scissor rod 403 is provided with a stop plate near the end;
when the scissor lever assembly 4 is in the storage state, the bottom compression spring 702 and the bottom locking pin 701 are compressed into the bottom plate 1 by the bottom scissor lever 401, and the top compression spring 802 and the top locking pin 801 are compressed into the top scissor lever 403 by the blocking plate;
when the scissor lever assembly 4 is in the unfolded state, the bottom scissor lever locking hole 40101 of the bottom scissor lever 401 rotates to face the bottom locking pin 701, and the bottom locking pin 701 is pushed into the bottom scissor lever locking hole 40101 through the bottom compression spring 702 and locks the bottom scissor lever 401; top locking pin 801 of top scissor lever 403 is rotated towards top scissor lever locking hole 201 of top plate 2 and top locking pin 801 is pushed into top scissor lever locking hole 201 by top compression spring 802 and locks top scissor lever 403.
In order to lock the scissor lever assembly 4, corresponding locking assemblies, namely the bottom locking assembly 7 and the top locking assembly 8, are designed for both the bottom scissor lever 401 and the top scissor lever 403; firstly, the locking structure of the bottom scissor lever 401, because in the storage state, the bottom scissor lever 401 is basically arranged in parallel with the bottom plate 1, and along with the unfolding motion, the bottom scissor lever 401 can be gradually arranged at a certain angle with the bottom plate 1, therefore, in order to enable the bottom scissor lever 401 to press and hold the bottom compression spring 702 and the bottom locking pin 701 in the storage state, a groove for accommodating the bottom compression spring 702 and the bottom locking pin 701 is designed on the bottom plate 1 in the embodiment, meanwhile, a bottom scissor lever locking hole 40101 corresponding to the end of the bottom scissor lever 401 is formed, when the bottom scissor lever locking hole 40101 is unfolded to the designed degree, the bottom scissor lever locking hole 40101 is matched with the bottom locking pin 701, and at this time, under the action of the bottom compression spring 702, the bottom locking pin 701 is driven to be embedded into the bottom scissor lever locking hole 40101, so as to realize the locking of the bottom scissor lever 401.
Similar to the locking principle of bottom scissor lever 401, top scissor lever 403 is locked by top locking assembly 8, the only difference being the mounting positions of top compression spring 802 and top locking pin 801, and the opening positions of top scissor lever locking hole 201, because the opening positions are different, a part is required to be able to hold top compression spring 802 and top locking pin 801 when in the storage state. Therefore, the above-described blocking plate is designed.
Preferably, the solar carpet module 11 of the present embodiment includes:
a bus plate 1103 disposed adjacent to the chassis base 1;
a solar carpet press plate 1101 arranged adjacent to the top plate 2; and
flexible solar panel 1102 integrated between bus plate 1103 and solar carpet press 1101;
when the solar carpet module 11 is in the storage state, the flexible solar panel 1102 is folded between the bus plate 1103 and the solar carpet pressing plate 1101;
the solar carpet press plate 1101 is connected with the top plate 2 through a solar carpet connecting rod 3;
a solar blanket tensioning device 10 is integrated between solar blanket coupler shaft 3 and solar blanket press plate 1101, and when solar blanket assembly 11 is in the unfolded state, flexible solar panels 1102 are maintained in the unfolded state by solar blanket tensioning device 10.
Wherein, the constant force spring 1001 is connected with the solar carpet connecting rod 3 at one end of the solar carpet tensioning device 10 and connected with the solar carpet pressing plate 1101 through the solar carpet connecting joint 1002 at the other end.
After the solar carpet assembly 11 is unfolded by the scissor lever assembly 4, the constant force spring 1001 is needed to maintain the unfolding degree of the flexible solar panel 1102.
The deployment mechanism further comprises a pressing device 9;
when the unfolding mechanism is in a storage state, the storage degree is kept through the pressing device 9;
the pressing device 9 includes:
a titanium rod assembly 901 on the top plate 2; and
a cutter 902 located at the base plate 2;
the titanium rod assembly 901 is threaded to the cutter 902 through a titanium rod, and the cutter 902 can be energized to sever the titanium rod to release the restraint of the deployment mechanism.
Preferably, the backplane 1 of the present embodiment is configured as a satellite star.
In the to-be-launched stage and the launched stage of the satellite, the flexible solar wing is always in a storage state, the compressing device 9 tightly fixes the unfolding mechanism on the satellite body, all the scissor rods are tightly contacted, after the satellite enters the orbit, the compressing device 9 adds points according to a program control instruction, the compressed titanium rod is cut off by the cutter 902, and the unfolding mechanism loses constraint to obtain the degree of freedom. The scissor rod assembly 4 extends outwards under the action of the driving assembly 5, the solar blanket connecting rod 3 is driven to move towards the direction far away from the star body along the direction perpendicular to the star body, the solar blanket is unfolded along with the sun blanket, the synchronization device ensures that the solar blanket is unfolded along a specified path in the unfolding process, when the solar span unfolding mechanism reaches a specified height, namely the solar blanket is unfolded, the top locking assembly 8 and the bottom locking assembly 7 are triggered, and the solar span unfolding mechanism is locked to ensure that the solar blanket is in a tensioning and unfolding state during the orbit of the satellite.
In the technical scheme, the flexible solar wing spreading mechanism with the high spreading ratio provided by the invention has the following beneficial effects:
the unfolding mechanism has the advantages of simple structure, high reliability and small mass; most structural members in the mechanism are made of aerospace-grade hard aluminum alloy and carbon fiber composite materials, the mechanical structure is simple and not numerous, and lightweight design improvement is made on each structural member on the premise of ensuring the strength and vibration requirements; the unfolding mechanism has the advantages of low manufacturing cost, low material price, simple structure and convenient manufacture, and the scissor rod assembly drives the solar carpet assembly 11 to move, so that the folding mechanism has the advantages of small folding volume, long unfolding distance and high unfolding and folding ratio.
The unfolding mechanism has small mass, and can effectively reduce the mass ratio of the whole mechanism of the flexible solar wing; the expansion ratio is large, so that the envelope size of the folded state of the flexible solar blanket can be greatly reduced, and the envelope size of the folded state of the whole satellite can be further reduced; the whole structure is simple, the assembly is convenient, the launching period can be effectively shortened, and a large amount of launching cost is saved.
While certain exemplary embodiments of the present invention have been described above by way of illustration only, it will be apparent to those of ordinary skill in the art that the described embodiments may be modified in various different ways without departing from the spirit and scope of the invention. Accordingly, the drawings and description are illustrative in nature and should not be construed as limiting the scope of the invention.
Claims (10)
1. A high aspect ratio flexible solar wing deployment mechanism, the deployment mechanism comprising:
a base plate (1);
a scissor lever assembly (4) integrated to the base plate (1); and
a solar carpet assembly (11) connected to the scissor bar assembly (4);
the deployment mechanism further comprises:
a drive assembly (5) integrated in the base plate (1);
the driving assembly (5) is provided with a driving motor (501) and a transmission gear (503) which is in transmission with the driving motor (501), and the transmission gear (503) extends to the upper part of the bottom plate (1);
the driving assembly (5) is in transmission connection with the scissor rod assembly (4) through the transmission gear (503) and drives the scissor rod assembly (4) to be unfolded so as to drive the solar carpet assembly (11) to be unfolded.
2. A high aspect ratio flexible solar wing spreading mechanism according to claim 1, wherein the drive assembly (5) comprises:
the driving motor (501) is integrated at the bottom of the bottom plate (1) through a motor mounting seat;
a drive torque output gear (502) connected to an output end of the drive motor (501);
the driving torque output gear (502) is meshed with the transmission gear (503) and drives the transmission gear (503) to rotate.
3. A high aspect ratio flexible solar wing spreading mechanism according to claim 2, wherein the scissor bar assembly (4) comprises:
a bottom scissor lever (401) arranged adjacent to the bottom plate (1);
a middle scissor lever (402) hinged to the bottom scissor lever (401); and
a top scissor lever (403) hinged to the upper end of the middle scissor lever (402);
the number of the bottom scissor rods (401) is two, and the two bottom scissor rods (401) are symmetrically arranged on two sides of the bottom plate (1);
the bottom scissor lever (401) on one side is connected with the transmission gear (503) to be driven to rotate through the transmission gear (503), and the bottom scissor lever (401) on the other side is driven to rotate through a bottom synchronization device which is driven to rotate through the transmission gear (503);
the two bottom shearing fork rods (401) synchronously rotate in different directions;
the deployment mechanism further comprises:
a top plate (2) at the top;
the top scissor rods (403) are arranged close to the top plate (2), the number of the top scissor rods (403) is two, and the two top scissor rods (403) are symmetrically arranged;
the number of the middle scissor rods (402) is multiple, the middle scissor rods (402) are arranged in a crossed manner, and the crossed positions of the middle scissor rods (402) are hinged;
the middle scissor rod (402) close to the bottom scissor rod (401) is hinged with the bottom scissor rods (401) at two sides respectively;
the middle scissor rods (402) close to the top scissor rods (403) are hinged to the top scissor rods (403) on both sides.
4. A high aspect ratio flexible solar wing opening mechanism according to claim 3, characterized in that the transmission gear (503) is integrated to the base plate (1) through a gear seat (610);
the bottom synchronization device includes:
a bottom synchronous wheel (601) meshed with the transmission gear (503), wherein the number of teeth and the modulus of the bottom synchronous wheel (601) are the same as those of the transmission gear (503);
a bottom driving pulley (602) coaxially arranged with the bottom synchronizing wheel (601) and synchronously rotating with the bottom synchronizing wheel (601); and
a bottom driven pulley (604) fitted to the base plate (1) through a gear seat (610);
the bottom driving pulley (603) and the bottom driven pulley (604) are driven by a bottom driving belt (603);
the bottom scissor rod (401) close to one side of the bottom driven pulley (604) is coaxial with the bottom driven pulley (604) and is driven to rotate by the bottom driven pulley (604).
5. A high aspect ratio flexible solar wing spreading mechanism according to claim 4 wherein the two top scissor levers (403) are connected by a top synchronization device to maintain the same amplitude of rotation in opposite directions;
the top synchronization device includes:
the top driving synchronous gear (609) is integrated on the top plate (2), and the top shearing fork rod (403) on one side is coaxially and fixedly connected with the top driving synchronous gear (609) and drives the top driving synchronous gear (609) to rotate;
a top driven synchronizing gear (608) in mesh with the top driving synchronizing gear (609);
a top drive pulley (609) arranged coaxially with the top driven synchronizing gear (608) and rotating synchronously with the top driven synchronizing gear (608); and
a top driven pulley (605) arranged on the opposite side of the top plate (2);
the top driving pulley (607) and the top driven pulley (605) are in transmission through a top transmission belt;
the top scissor rod (403) on the other side is coaxially and fixedly connected with the top driven pulley (605) and is driven to rotate by the top driven pulley (605).
6. A high aspect ratio flexible solar wing spreading mechanism according to claim 5, wherein a bottom locking assembly (7) is integrated between the bottom scissor bar (604) and the bottom plate (1);
a top locking assembly (8) is integrated between the top scissor rod (403) and the top plate (2);
the bottom locking assembly (7) comprises:
a bottom compression spring (702) and a bottom locking pin (701) embedded within the bottom plate (2);
a bottom scissor lever locking hole (40101) matched with the bottom locking pin (701) is formed in the end part of the bottom scissor lever (401);
the top locking assembly (8) comprises:
a top compression spring (802) and a top locking pin (801) embedded within the top scissor lever (403);
a top shear fork rod locking hole (201) matched with the top locking pin (801) is formed in the top plate (2);
the top scissor rod (403) is provided with a stop plate at the position close to the end;
when the scissor lever assembly (4) is in the storage state, the bottom compression spring (702) and the bottom locking pin (701) are compressed into the bottom plate (1) by the bottom scissor lever (401), and the top compression spring (802) and the top locking pin (801) are compressed into the top scissor lever (403) by the blocking plate;
when the scissor lever assembly (4) is in an unfolded state, the bottom scissor lever locking hole (40101) of the bottom scissor lever (401) rotates to face the bottom locking pin (701), and the bottom locking pin (701) is pushed into the bottom scissor lever locking hole (40101) through the bottom compression spring (702) and locks the bottom scissor lever (401); the top locking pin (801) of the top scissor lever (403) rotates to face towards the top scissor lever locking hole (201) of the top plate (2), and the top locking pin (801) is pushed into the top scissor lever locking hole (201) through the top compression spring (802) and locks the top scissor lever (403).
7. A high aspect ratio flexible solar wing spreading mechanism according to claim 5, wherein the solar carpet assembly (11) comprises:
a bus bar (1103) disposed adjacent to the chassis (1);
a solar carpet press plate (1101) arranged adjacent to the top plate (2); and
a flexible solar panel (1102) integrated between the bus plate (1103) and the solar carpet platen (1101);
when the solar carpet assembly (11) is in a storage state, the flexible solar panel (1102) is folded between the bus board (1103) and the solar carpet pressing board (1101);
the solar carpet pressure plate (1101) is connected with the top plate (2) through a solar carpet connecting rod (3);
a solar blanket tensioning device (10) is integrated between the solar blanket connecting rod (3) and the solar blanket pressing plate (1101), and when the solar blanket assembly (11) is in an unfolded state, the flexible solar plate (1102) is kept unfolded through the solar blanket tensioning device (10).
8. The high aspect ratio flexible sun wing spreading mechanism according to claim 7, wherein the sun carpet tensioning device (10) is a constant force spring with one end connected to the sun carpet connecting rod (3) and the other end connected to the sun carpet pressure plate (1102) through a sun carpet connecting joint (1002).
9. A high aspect ratio flexible solar wing deployment mechanism according to claim 3, characterized in that it further comprises a hold-down device (9);
when the unfolding mechanism is in a storage state, the storage degree is kept through the pressing device (9);
the pressing device (9) comprises:
a titanium rod assembly (901) located on the top plate (2); and
a cutter (902) located at the base plate (1);
the titanium rod assembly (901) is in threaded connection with the cutter (902) through a titanium rod, and the cutter (902) can be cut off after being electrified so as to release the constraint on the deployment mechanism.
10. A high aspect ratio flexible solar wing opening mechanism according to any of the claims 1-9, characterized in that the base plate (1) is configured as a satellite star.
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| CN202110783411.2A CN113291494A (en) | 2021-07-12 | 2021-07-12 | High-expansion-ratio flexible solar wing unfolding mechanism |
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| CN202110783411.2A CN113291494A (en) | 2021-07-12 | 2021-07-12 | High-expansion-ratio flexible solar wing unfolding mechanism |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113772125A (en) * | 2021-11-12 | 2021-12-10 | 北京最终前沿深空科技有限公司 | Sun wing unfolding device |
| CN113895659A (en) * | 2021-11-25 | 2022-01-07 | 苏州馥昶空间技术有限公司 | Sun wing unfolding device |
| CN114104337A (en) * | 2021-12-16 | 2022-03-01 | 上海交通大学 | Double-layer deployable unit |
| CN115196053A (en) * | 2022-07-18 | 2022-10-18 | 南京航空航天大学 | Secondary aircraft lifting-raising device |
| CN115367150A (en) * | 2022-08-03 | 2022-11-22 | 银河航天(北京)网络技术有限公司 | Scissor-fork type solar wing system |
| CN116605422A (en) * | 2023-07-21 | 2023-08-18 | 银河航天(北京)网络技术有限公司 | Lifting device for satellite solar wing and satellite |
| CN116692038A (en) * | 2023-07-07 | 2023-09-05 | 重庆开拓卫星科技有限公司 | Solar wing span opening mechanism capable of adjusting angle |
| US11958638B1 (en) * | 2020-05-14 | 2024-04-16 | Space Exploration Technologies Corp. | Spacecraft solar array biasing and tensioning system |
Citations (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0669251A2 (en) * | 1994-02-04 | 1995-08-30 | Orbital Sciences Corporation | Satellite having a stackable configuration |
| CN105347246A (en) * | 2015-12-03 | 2016-02-24 | 电子科技大学 | Shear-fork type lifting platform with wheel train transmission |
| CN105909714A (en) * | 2016-04-19 | 2016-08-31 | 长光卫星技术有限公司 | Impact damping device suitable for unfolding of solar panel substrate |
| CN106314826A (en) * | 2016-08-31 | 2017-01-11 | 燕山大学 | Torsional spring driven shear fork extending arm |
| 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 |
| CN109327183A (en) * | 2018-11-12 | 2019-02-12 | 张建华 | Device of solar generating |
| CN109525185A (en) * | 2018-12-24 | 2019-03-26 | 西南交通大学 | A kind of solar energy film spool |
| CN110254750A (en) * | 2019-05-29 | 2019-09-20 | 北京航空航天大学 | A kind of rope driving Zhan Shou mechanism being fitted parabolic cylinder |
| CN209789300U (en) * | 2019-01-25 | 2019-12-17 | 江苏省徐州技师学院 | Planar design works show protective structure |
| CN110722992A (en) * | 2019-11-25 | 2020-01-24 | 哈尔滨市恩光川川科技有限责任公司 | Telescopic on-vehicle solar charging device of parallel four-bar |
| CN210113719U (en) * | 2019-07-26 | 2020-02-25 | 江苏明耀光伏科技有限公司 | Solar photovoltaic panel with rain shielding function |
| CN111152939A (en) * | 2020-01-21 | 2020-05-15 | 上海宇航系统工程研究所 | Flexible solar cell array |
| US20200228057A1 (en) * | 2019-01-16 | 2020-07-16 | CubeX Solar, LLC | Foldable solar power system |
| US10773833B1 (en) * | 2011-08-30 | 2020-09-15 | MMA Design, LLC | Panel for use in a deployable and cantilevered solar array structure |
| CN211981817U (en) * | 2020-06-09 | 2020-11-20 | 国网冀北综合能源服务有限公司 | Scissor-fork type solar panel mounting rack |
| CN111977030A (en) * | 2020-08-13 | 2020-11-24 | 哈尔滨工业大学 | Solar wing with large folding-unfolding ratio |
| CN112027118A (en) * | 2020-09-14 | 2020-12-04 | 中国科学院微小卫星创新研究院 | Solar cell array structure and unfolding method |
| KR102264913B1 (en) * | 2020-04-03 | 2021-06-15 | 한국과학기술원 | Deployable Truss Boom Structure foldable into Planar Form |
| 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 |
-
2021
- 2021-07-12 CN CN202110783411.2A patent/CN113291494A/en active Pending
Patent Citations (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0669251A2 (en) * | 1994-02-04 | 1995-08-30 | Orbital Sciences Corporation | Satellite having a stackable configuration |
| US10773833B1 (en) * | 2011-08-30 | 2020-09-15 | MMA Design, LLC | Panel for use in a deployable and cantilevered solar array structure |
| CN105347246A (en) * | 2015-12-03 | 2016-02-24 | 电子科技大学 | Shear-fork type lifting platform with wheel train transmission |
| 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 |
| CN105909714A (en) * | 2016-04-19 | 2016-08-31 | 长光卫星技术有限公司 | Impact damping device suitable for unfolding of solar panel substrate |
| CN106314826A (en) * | 2016-08-31 | 2017-01-11 | 燕山大学 | Torsional spring driven shear fork extending arm |
| CN109327183A (en) * | 2018-11-12 | 2019-02-12 | 张建华 | Device of solar generating |
| CN109525185A (en) * | 2018-12-24 | 2019-03-26 | 西南交通大学 | A kind of solar energy film spool |
| US20200228057A1 (en) * | 2019-01-16 | 2020-07-16 | CubeX Solar, LLC | Foldable solar power system |
| CN209789300U (en) * | 2019-01-25 | 2019-12-17 | 江苏省徐州技师学院 | Planar design works show protective structure |
| CN110254750A (en) * | 2019-05-29 | 2019-09-20 | 北京航空航天大学 | A kind of rope driving Zhan Shou mechanism being fitted parabolic cylinder |
| CN210113719U (en) * | 2019-07-26 | 2020-02-25 | 江苏明耀光伏科技有限公司 | Solar photovoltaic panel with rain shielding function |
| CN110722992A (en) * | 2019-11-25 | 2020-01-24 | 哈尔滨市恩光川川科技有限责任公司 | Telescopic on-vehicle solar charging device of parallel four-bar |
| CN111152939A (en) * | 2020-01-21 | 2020-05-15 | 上海宇航系统工程研究所 | Flexible solar cell array |
| KR102264913B1 (en) * | 2020-04-03 | 2021-06-15 | 한국과학기술원 | Deployable Truss Boom Structure foldable into Planar Form |
| CN211981817U (en) * | 2020-06-09 | 2020-11-20 | 国网冀北综合能源服务有限公司 | Scissor-fork type solar panel mounting rack |
| CN111977030A (en) * | 2020-08-13 | 2020-11-24 | 哈尔滨工业大学 | Solar wing with large folding-unfolding ratio |
| CN112027118A (en) * | 2020-09-14 | 2020-12-04 | 中国科学院微小卫星创新研究院 | Solar cell array structure and unfolding method |
| 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 |
Non-Patent Citations (1)
| Title |
|---|
| 孔菲: "重复折展锁解式太阳翼机构设计及其性能测试", 《优秀硕士学位论文全文库工程科技Ⅱ辑》 * |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11958638B1 (en) * | 2020-05-14 | 2024-04-16 | Space Exploration Technologies Corp. | Spacecraft solar array biasing and tensioning system |
| CN113772125A (en) * | 2021-11-12 | 2021-12-10 | 北京最终前沿深空科技有限公司 | Sun wing unfolding device |
| CN113895659A (en) * | 2021-11-25 | 2022-01-07 | 苏州馥昶空间技术有限公司 | Sun wing unfolding device |
| CN113895659B (en) * | 2021-11-25 | 2023-09-19 | 苏州馥昶空间技术有限公司 | Solar wing opening device |
| CN114104337B (en) * | 2021-12-16 | 2023-08-25 | 上海交通大学 | Double-layer expandable unit |
| CN114104337A (en) * | 2021-12-16 | 2022-03-01 | 上海交通大学 | Double-layer deployable unit |
| CN115196053A (en) * | 2022-07-18 | 2022-10-18 | 南京航空航天大学 | Secondary aircraft lifting-raising device |
| CN115196053B (en) * | 2022-07-18 | 2024-03-29 | 南京航空航天大学 | Lifting-head-lifting device for secondary aircraft |
| CN115367150A (en) * | 2022-08-03 | 2022-11-22 | 银河航天(北京)网络技术有限公司 | Scissor-fork type solar wing system |
| CN115367150B (en) * | 2022-08-03 | 2024-05-17 | 银河航天(北京)网络技术有限公司 | Scissor type solar wing system |
| CN116692038A (en) * | 2023-07-07 | 2023-09-05 | 重庆开拓卫星科技有限公司 | Solar wing span opening mechanism capable of adjusting angle |
| CN116692038B (en) * | 2023-07-07 | 2024-01-30 | 重庆开拓卫星科技有限公司 | Solar wing span opening mechanism capable of adjusting angle |
| CN116605422A (en) * | 2023-07-21 | 2023-08-18 | 银河航天(北京)网络技术有限公司 | Lifting device for satellite solar wing and satellite |
| CN116605422B (en) * | 2023-07-21 | 2023-10-20 | 银河航天(北京)网络技术有限公司 | Lifting device for satellite solar wing and satellite |
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