CN113772125B - Sun wing unfolding device - Google Patents
Sun wing unfolding device Download PDFInfo
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- CN113772125B CN113772125B CN202111340188.0A CN202111340188A CN113772125B CN 113772125 B CN113772125 B CN 113772125B CN 202111340188 A CN202111340188 A CN 202111340188A CN 113772125 B CN113772125 B CN 113772125B
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- 239000000758 substrate Substances 0.000 claims abstract description 107
- 238000003825 pressing Methods 0.000 claims abstract description 14
- 239000002360 explosive Substances 0.000 claims description 7
- 238000003780 insertion Methods 0.000 claims description 6
- 230000037431 insertion Effects 0.000 claims description 6
- 230000009471 action Effects 0.000 claims description 5
- 230000006835 compression Effects 0.000 claims description 5
- 238000007906 compression Methods 0.000 claims description 5
- 238000005056 compaction Methods 0.000 claims description 4
- 230000007480 spreading Effects 0.000 claims description 3
- 238000004804 winding Methods 0.000 claims description 3
- 238000003756 stirring Methods 0.000 claims description 2
- 238000009434 installation Methods 0.000 claims 1
- 230000005484 gravity Effects 0.000 description 3
- 230000007246 mechanism Effects 0.000 description 3
- 229910000831 Steel Inorganic materials 0.000 description 2
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000004880 explosion Methods 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 238000004891 communication Methods 0.000 description 1
- 230000000994 depressogenic effect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000005489 elastic deformation Effects 0.000 description 1
- 238000005286 illumination Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
- 238000005381 potential energy Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
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- 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
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Abstract
The application provides a solar wing opening device, includes: the solar wing locking device comprises a tensioning rope, an unfolding rod component, an unfolding power component, a solar wing base plate component, a locking structure and a pressing structure; the unfolding rod assembly is connected with the solar wing base plate assembly and comprises two short rods and a plurality of long rods; the two short rods are respectively connected with the uppermost substrate and the lowermost substrate; one end of the locking structure is connected with the lower short rod, and the other end of the locking structure is abutted against the satellite body; the unfolding power assembly is arranged on the satellite body and used for generating power for releasing the tensioning rope when the solar wing substrate assembly is unfolded; one end of the tensioning rope is fixed on the upper short rod, and the other end of the tensioning rope is fixed on the unfolding power component; one end of the compressing structure is fixedly connected with the Mth solar wing substrate, and the other end of the compressing structure is connected with the satellite body and used for keeping the solar wing substrate assembly in a folded state before being unfolded. The expansion mode of this application strikes for a short time, and structure weight is little, and is small.
Description
Technical Field
The application relates to a unfolding device, in particular to a solar wing unfolding device.
Background
The solar wing is a component for receiving solar illumination to generate energy when the spacecraft runs on orbit. Due to the large size of the solar wing, the solar wing is usually folded and compressed when being launched and released and unfolded when being in orbit. Therefore, the solar wing needs to have a folding mechanism and is installed between two solar wing substrates. The current common unfolding scheme is to adopt a hinge mode for unfolding. The torsion spring is arranged in the hinge, after the solar wing enters the track, the solar wing pressing point is unlocked, and the torsion spring in the hinge drives the solar wing substrate to unfold. Such a development of a hinge by a torsion spring has the following problems: (1) the torsion spring drives the base plate to unfold, and a great impact effect can be generated, because the space has no air resistance and gravity, and all energy is consumed at the moment of final stop. This impact requires that the structural strength must be high, which results in a high volume and weight. (2) The hinge with the torsion spring needs a certain design size, when the multi-fold solar wing is provided, the thickness formed by the plurality of torsion spring hinges can enable the thickness of the whole solar wing to be too large in a compression state, and for a flat satellite, the thickness can greatly exceed the size budget.
Disclosure of Invention
In view of the above technical problems, the embodiment of the present application provides a solar wing unfolding apparatus, which unfolds a solar wing mechanism by tensioning a line, and the unfolding mode has small impact, small structural weight, small volume, low cost and no mechanical unfolding hinge.
The technical scheme adopted by the application is as follows:
the embodiment of the application provides a solar wing opening device, includes: the solar wing locking device comprises a tensioning rope, an unfolding rod component, an unfolding power component, a solar wing base plate component, a locking structure and a pressing structure; the solar wing substrate assembly comprises a first solar wing substrate, an Mth solar wing substrate, wherein the first solar wing substrate and the Mth solar wing substrate are sequentially connected through a hinge structure from bottom to top, M is an even number, the first solar wing substrate is connected with the satellite body through the hinge structure, a rotating shaft is arranged on the hinge structure between the first solar wing substrate and the satellite body, a rotating shaft is arranged between the hinge structures between the ith solar wing substrate and the (i + 1) th solar wing substrate, and the value of i is 2, 4. The unfolding rod assembly comprises two short rods and a plurality of long rods sequentially arranged between the two short rods, when the solar wing substrate is in an unfolded state, each short rod spans one solar wing substrate, and each long rod spans two solar wing substrates; the short rods comprise an upper short rod and a lower short rod, the upper end of the upper short rod is rotatably connected with the Mth solar wing substrate through an upper connecting rod, and the lower end of the lower short rod is connected with a rotating shaft on the first solar wing substrate through a lower connecting rod; the long rods are rotatably connected with the short rods and the adjacent two long rods through unfolding shafts, and each long rod is also connected with the corresponding rotating shaft through a long rod connecting rod; sliding wheels are arranged on the upper connecting rod, the lower connecting rod and the unfolding shaft; one end of the locking structure is connected with the lower short rod, and the other end of the locking structure is abutted with the satellite body; the satellite body is provided with a locking part matched with the locking structure; during deployment of the deployment rod assembly, the locking structure moves with the deployment rod assembly to the locking portion and cooperates with the locking portion to lock the deployment rod assembly to the satellite body; the unfolding power component is arranged on the satellite body and comprises a power part and an accommodating part, the accommodating part is provided with an accommodating space for accommodating the tensioning rope, and the power part is used for generating power for releasing the tensioning rope when the solar wing substrate component is unfolded; one end of the tensioning rope is fixedly connected with the sliding wheel positioned on the upper connecting rod, and the other end of the tensioning rope sequentially bypasses the sliding wheel on the unfolding shaft and the sliding wheel on the lower connecting rod and is fixed in the accommodating space; when the solar wing substrate assembly is in an unfolded state, the tensioning rope is in a tensioned state, and when the solar wing substrate is in a folded state, the tensioning rope is in a relaxed state; one end of the compaction structure is fixedly connected with the Mth solar wing substrate, and the other end of the compaction structure is connected with the satellite body, so that the solar wing substrate assembly is kept in a folded state before being unfolded; when the solar wing substrate needs to be unfolded, the pressing force of the pressing structure is released so that the solar wing substrate is unfolded.
The embodiment of the application has at least the following technical effects:
(1) the folding thickness of the solar wing is mainly determined by the thickness of the unfolding rod by adopting a mode that the unfolding rod is pulled by the pull wire, and the unfolding rod can be made very thin due to the fact that the space has no gravity and air resistance, so that the thickness of the solar wing during folding can be reduced, and the size of the solar wing is small.
(2) As the simple connecting hinge is only used between every two solar wing substrates and no other redundant structure is provided, namely the torsion spring and the structure caused by the torsion spring are reduced on each solar wing substrate, the weight of the solar wing is reduced on the whole.
(3) When the solar wing is unfolded in place, due to the fact that the pulling force is in the solar wing panel, impact force is evenly distributed along the solar wing panel, and compared with a torsional spring hinge unfolding mode, all impact force is concentrated on the hinge, and when the solar wing is unfolded, the local impact force is very small.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments or related technologies of the present application, the drawings needed to be used in the description of the embodiments or related technologies are briefly introduced below, it is obvious that the drawings in the following description are only some embodiments of the present application, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic view of a solar wing deployment apparatus provided in accordance with an embodiment of the present application in a folded state;
FIG. 2 is a schematic view of a solar wing deployment apparatus provided in accordance with another embodiment of the present application in a collapsed state;
fig. 3 is an exploded schematic view of a solar wing deployment device provided in an embodiment of the present application in a deployed state;
FIG. 4 is a schematic view of a solar wing substrate coupled to a rotation shaft by a hinge structure in an embodiment of the present application;
FIG. 5 is a schematic view of a hinge structure in an embodiment of the present application;
FIG. 6 is a schematic view of a support structure in an embodiment of the present application;
FIGS. 7 and 8 are schematic views of a deployment rod assembly in an embodiment of the present application;
FIG. 9 is a schematic view of a fastener in an embodiment of the present application;
FIG. 10 is a schematic view of a locking mechanism in an embodiment of the present application;
FIG. 11 is a schematic view of a deploy power assembly in an embodiment of the present application.
(description of reference numerals)
1-solar wing substrate assembly; 101-solar wing substrate; 102-a bump;
2-a deployment rod assembly; 201-upper short bar; 202-lower short bar; 203-long rod; 204-upper connecting rod;
205-a lower connecting rod; 206-long rod connecting rod; 207-a sliding wheel; 208-fixed block; 209-mounting shaft;
210-a connection hole;
3-a locking structure; 301-locking the end cap; 302-a locking pin; 303-locking spring; 304-a stop;
4-unfolding the power assembly; 401-fixing plate; 402-a housing; 403-a baffle; 404-a toggle piece;
405-rotating rods; 406-torsion spring; 407-a recess; 408-a first bolt; 409-stud;
410-a second bolt; 5, tensioning the rope; 6-hinge structure; 601-male hinge; 602-a female hinge;
603-a retainer ring; 7-a satellite body; 8-a rotating shaft; 9-a support structure; 901-a first connection;
902-a second connection; 10-a guide bracket; 11-exploding the bolt.
Detailed Description
In order to make the technical problems, technical solutions and advantages to be solved by the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application.
As shown in fig. 1 to 3, an embodiment of the present application provides a solar wing spreading device, including: the solar wing comprises a solar wing base plate assembly 1, an unfolding rod assembly 2, a locking structure 3, an unfolding power assembly 4, a tensioning rope 5 and a compression structure.
Further, in the embodiment of the present application, as shown in fig. 3, the solar wing substrate assembly 1 may include M solar wing substrates 101 sequentially connected by the hinge structure 6, from bottom to top, wherein M is an even number. Preferably, M is an even number equal to or greater than 6. The embodiment of the application shows 6 solar wing substrates.
The first solar wing substrate is connected with the satellite body 7 through a hinge structure, a rotating shaft 8 is arranged on the hinge structure between the first solar wing substrate and the satellite body, the rotating shaft 8 is arranged between the hinge structures between the ith solar wing substrate and the (i + 1) th solar wing substrate, and the value of i is 2, 4. That is, the solar wing substrate located between the first solar wing substrate and the last solar wing substrate is provided with the rotation axis at the position spaced apart by two substrates.
In the embodiment of the present application, the satellite body 7 may be a flat plate as a whole, such as a communication satellite.
As shown in fig. 4, in the embodiment of the present application, the number of the hinge structures 6 at the connection position may be 2, and both ends of the rotation shaft are rotatably disposed in the two hinge structures, respectively. As shown in fig. 5, in the present embodiment, the hinge structure 6 may include a male hinge 601 and a female hinge 602. The female hinge 602 and the male hinge 601 are rotatably coupled and cooperatively formed with a through hole into which the rotating shaft 8 is inserted. The male hinge 601 and the female hinge 602 are respectively formed with fixing holes for fixing to the corresponding solar wing substrate, and can be fixed to the solar wing substrate by screws, for example. After the rotating shaft 8 is inserted into the through hole, it can be fixed on both sides of the male hinge 601 by the retainer rings 603, and the retainer rings 603 can have an opening. As the simple connecting hinge is only used between every two solar wing substrates and no other redundant structure is provided, namely the torsion spring and the structure caused by the torsion spring are reduced on each solar wing substrate, the weight of the solar wing is reduced on the whole.
Further, in this embodiment of the application, each solar wing substrate is provided with a plurality of protrusions 202, when the solar wing substrate is in a folded state, the protrusions of two adjacent solar wing substrates abut against each other, so that it can be ensured that the solar cell pieces adhered to the solar wing substrate are not crushed when the solar wing is in the folded state.
Further, in the present embodiment, the first solar wing substrate may be rotatably connected to the satellite body through the supporting structure 9. As shown in fig. 6, the support structure 9 may include a first connection portion 901 and a second connection portion 902, the first connection portion 901 is formed with a fixing hole connected with the satellite body, the second connection portion 902 is formed with two fixing holes connected with the male hinge, and a through hole connected with the unfolding shaft.
In addition, in the embodiment of the present application, a sleeve is disposed on the rotating shaft on the first solar wing substrate. The sleeve is used for preventing the supporting structure from rubbing with the solar wing substrate assembly.
Further, as shown in fig. 7 and 8, the deployment rod assembly 2 may include two short rods 201 and 202 and a plurality of long rods 203 sequentially disposed between the two short rods. When the solar wing substrates are in the unfolded state, each short rod spans one solar wing substrate, and each long rod spans two solar wing substrates, namely, in the case of setting M solar wing substrates, the number of the long rods is (M-2)/2.
The short rods comprise an upper short rod 201 and a lower short rod 202, the upper end of the upper short rod 201 is rotatably connected with the Mth solar wing substrate through an upper connecting rod 204, and the lower end of the lower short rod 202 is connected with a rotating shaft on the first solar wing substrate through a lower connecting rod 205. The long rods are rotatably connected with the short rods and the adjacent two long rods through unfolding shafts, and each long rod is also connected with a corresponding rotating shaft through a long rod connecting rod 206; the upper connecting rod, the lower connecting rod and the unfolding shaft are all provided with a sliding wheel 207.
In the embodiment of the present application, both ends of the short and long rods have through holes. The unfolding shaft passes through the corresponding through hole and realizes the rotary connection between the short rod and the long rod as well as between the long rods through the check rings. The movable pulley cover is fixed through retaining ring realization at the expansion axle, and the expansion axle passes through-hole, movable pulley in proper order promptly and fixes through the retaining ring.
Further, the upper connecting rod 204 may be connected to the mth solar wing substrate through a fixing member. As shown in fig. 9, the fixing member may include a fixing block 208, one end of the fixing block 208 is connected to the mth solar wing substrate, the other end of the fixing block is provided with a mounting shaft 209, and the mounting shaft 209 is provided with a connecting hole 210 connected to the upper connecting rod 204. In this way, one end of the upper connecting rod 204 is inserted into the through hole of the upper short rod 201, and the other end is inserted into the connecting hole 210, so that the upper short rod is connected with the uppermost solar wing substrate. The upper connecting rod 204 may be secured in the connecting bore 210 by a retaining ring.
In this application embodiment, a plurality of stock is owing to connect through the expansion axle at the tip, and consequently, two adjacent stock, the stock that is located the top is because far away from the sun wing base plate, and consequently, the stock connecting rod of the stock connecting rod that uses can be longer than the stock connecting rod of the stock that is located the below. In the embodiment of the present application, the rotating shaft 8 is provided with a connecting hole, and the connecting hole is provided at a middle position of the rotating shaft 8. The lower connecting rod and the long rod connecting rod can be connected with the rotating shaft through the connecting hole. The lower connecting rod and the long rod connecting rod can be fixed through the check ring. Thus, when the deployment rod assembly is deployed, the solar wing substrate assembly follows the deployment.
Further, in the present embodiment, one end of the locking structure 3 is connected to the lower short rod 202, and the other end is abutted against the satellite body 7. The satellite body 7 is provided with a locking part (not shown) adapted to the locking structure, and during the unfolding process of the unfolding rod assembly 2, the locking structure 3 moves to the locking part along with the unfolding rod assembly and is matched with the locking part to lock the unfolding rod assembly on the satellite body 7.
Specifically, as shown in fig. 10, the locking structure 3 in the embodiment of the present application may include a locking pin cover 301, a locking pin 302, and a locking spring 303. One end of the locking pin cover 301 is connected with the end of the lower short rod 202, and the other end is movably connected with the satellite body 7, and an insertion hole is formed by the mutual matching of the end through hole of the lower short rod and the locking pin cover. The locking pin 302 is inserted into the insertion hole, and a stopper portion 304 is formed. The locking spring 303 is disposed outside the locking pin 302 and above the stopping portion 304, i.e. the locking spring is limited by the stopping portion 304. One end of the locking spring pushes the locking pin to be abutted against the locking pin cover, and the other end of the locking spring is abutted against the lower short rod.
The locking portion may be a locking hole adapted to the locking pin. In the embodiment of the present application, the position of the locking hole is set so that the deployment lever assembly just corresponds to the insertion hole from the folded state to the fully unfolded state. Specifically, when the unfolding rod assembly is unfolded, the locking structure moves along with the unfolding rod assembly, when the unfolding rod assembly is in a fully unfolded state, namely is unfolded to a proper position, the locking structure just moves to the position of the locking hole, at the moment, the locking pin just faces to the locking hole, and at the moment, the locking pin is pushed out of the insertion hole under the action of the elastic force of the locking spring and is inserted into the locking hole, so that the unfolding rod assembly is locked on the satellite body.
Further, in the embodiment of the present invention, the unfolding power module 4 is provided on the satellite body 7, and includes a power unit for generating power for releasing the tension rope 5 when the solar wing panel assembly is unfolded, and a housing portion in which a housing space for housing the tension rope is formed.
Specifically, as shown in fig. 11, the unfolding power assembly 4 further includes a fixing plate 401, and the fixing plate 401 is fixedly connected to the satellite body 7. The receiving portion includes a housing 402, the housing 402 has a receiving space formed therein, a baffle 403 protruding outward is formed at the bottom of the side portion of the housing, and a toggle member 404 is disposed on the baffle, and in one example, the toggle member 404 may include a first bolt 408 and a stud 409.
The power section may include a rotating lever 405 and a torsion spring 406. The upper end of the rotating rod 405 penetrates through the accommodating space to be rotatably connected with the shell, and the lower end of the rotating rod 405 penetrates through the torsion spring 406 and is rotatably connected with the fixing plate 401. The upper end of the rotation rod 405 may be fixed by a second bolt 410, and the lower end may also be fixed by a bolt. The upper end of the rotating rod 405 is used for the tightening rope 5 to wind; the end of the torsion spring 406 is formed with a recess 407, and the toggle member 404 is inserted into the recess 407.
It should be noted that the torsion spring in the embodiment of the present application may be changed to a stepping motor.
Further, in the present embodiment, the tension cord 5 is used to deploy the deployment rod assembly. As shown in fig. 3, one end of the tightening rope 5 is fixedly connected to the sliding wheel on the upper connecting rod 201, and the other end of the tightening rope sequentially passes around the sliding wheel on the unfolding shaft and the sliding wheel on the lower connecting rod and is fixed in the accommodating space. In order to release and accommodate the tension rope 5 smoothly, as shown in fig. 2, a plurality of guide brackets 10 are further provided on the satellite body for guiding the tension rope to the accommodating space. In this embodiment, two guide brackets with different heights are provided, wherein the height of the guide bracket close to the unfolding power assembly is higher than that of the other guide bracket, so that a height difference is formed, and the tensioning rope can be better released and accommodated. In one example, the tensioning line may be a 0.5mm steel wire rope. In the present embodiment, the tension rope 5 is in a tensioned state when the solar wing substrate assembly is in the unfolded state, and the tension rope 5 is in a relaxed state when the solar wing substrate assembly is in the folded state.
In the embodiment of the application, the working principle of unfolding the solar wing substrate through the tensioning rope is as follows: under the sun wing base plate is in the expanded state, 5 one end windings of stay rope are on casing 402, 10 rings are no less than to the number of winding turns, and stay rope 5 is in taut state this moment, receive external force (like the packing force that the staff applyed) and when folding when the sun wing base plate, stay rope 5 receives the pulling force, and progressively will twine the partial rope of casing 402 and pull open, casing 402 produces the rotation along with pulling open of rope this moment, this rotation can drive to dial the piece and stir the depressed part, thereby drive torsional spring 406 and produce elastic deformation, will expand potential energy storage this moment in torsional spring 406. When the external force is relieved, the poking piece is pushed under the action of the elastic force of the torsion spring, so that the shell is driven to rotate, the tensioning rope is released, and the unfolding rod component is unfolded.
Further, in the present embodiment, the pressing structure is used to press the solar wing substrate assembly before the solar wing substrate assembly is unfolded, so that the solar wing substrate is in a folded and pressed state. When the solar wing substrate needs to be unfolded, the pressing force of the pressing structure is released so that the solar wing substrate is unfolded.
In one exemplary embodiment, the compression structure may be a locking cord (not shown). One end of the locking rope is fixedly connected with the sliding wheel on the upper connecting rod, and the other end of the locking rope is fixed on the satellite body; when the solar wing substrate needs to be unfolded, the locking ropes are burnt out to unfold the solar wing substrate. In one example, the locking rope may be a 0.5mm steel wire rope.
In the embodiment of the present application, the locking cord may be blown by an ignition device. The ignition device can be connected with the controller, and after the solar wing substrate rises to a preset position, the controller can send an ignition instruction to the ignition device to blow the locking rope. After the locking rope is blown, the tensioning rope is released under the action of the torsion spring, the released tensioning rope can generate tension on the unfolding rod assembly, as shown in fig. 7, each corner point in the unfolding rod assembly can be subjected to the resultant force of F1 and F2, and when the force of F3 is formed, two rods at the corner are stressed to unfold.
In another exemplary embodiment, as shown in fig. 2, the compression structure may be an explosive bolt 11. The explosive bolts 11 sequentially penetrate through the M solar wing base plates from top to bottom and are fixed on the satellite body, so that the solar wing base plate assembly is in a folded and compressed state. A plurality of explosive bolts can be provided as required to ensure that the solar wing substrate assembly can be in a folded and compacted state before being unfolded. The explosion bolt 11 may be an existing product provided with an explosive charge at a position between the lowermost base plate and the satellite body, and the pressing force on the solar wing base plate is released by controlling the explosive charge to explode. To avoid redundancy, the present invention omits specific description of the explosion bolt. After the pressing force is released, the tensioning rope is released under the action of the torsion spring, the released tensioning rope can generate tension on the unfolding rod assemblies, and as shown in fig. 7, when each corner point in the unfolding rod assemblies is subjected to the resultant force of F1 and F2 to form a force of F3, the two rods at the corner points are stressed and unfolded.
The solar wing unfolding device provided by the embodiment of the application adopts a mode that the stay wire pulls the unfolding rod, the folding thickness of the solar wing mainly depends on the thickness of the unfolding rod, and the unfolding rod can be made very thin due to the fact that the space does not have gravity and air resistance, so that the thickness of the solar wing during folding can be reduced, and the size of the solar wing unfolding device can be small. In addition, when the solar wing is unfolded in place, due to the fact that the pulling force is in the solar wing panel, impact force is evenly distributed along the solar wing panel, compared with the unfolding mode of the torsion spring hinge, all impact force is concentrated on the hinge, and when the device is unfolded, the local impact force is very small.
Although some specific embodiments of the present application have been described in detail by way of illustration, it should be understood by those skilled in the art that the above illustration is only for purposes of illustration and is not intended to limit the scope of the present application. It will also be appreciated by those skilled in the art that various modifications may be made to the embodiments without departing from the scope and spirit of the present application. The scope of the present application is defined by the appended claims.
Claims (10)
1. A solar wing spreading device, comprising: the solar wing locking device comprises a tensioning rope, an unfolding rod component, an unfolding power component, a solar wing base plate component, a locking structure and a pressing structure; the solar wing substrate assembly comprises a first solar wing substrate, a second solar wing substrate, a third solar wing substrate, a fourth solar wing substrate, a fifth solar wing substrate, a sixth solar wing substrate, a fifth solar wing substrate and a sixth solar wing substrate, wherein the first solar wing substrate is connected with the satellite body through a hinge structure from bottom to top in sequence, M is an even number, the first solar wing substrate is connected with the satellite body through the hinge structure, a rotating shaft is arranged in the hinge structure between the first solar wing substrate and the satellite body, a rotating shaft is arranged between the hinge structures between the ith solar wing substrate and the (i + 1) th solar wing substrate, and the value of i is 2, 4,. and M-2; the unfolding rod assembly comprises two short rods and a plurality of long rods sequentially arranged between the two short rods, when the solar wing substrate is in an unfolded state, each short rod spans one solar wing substrate, and each long rod spans two solar wing substrates; the short rods comprise an upper short rod and a lower short rod, the upper end of the upper short rod is rotatably connected with the Mth solar wing substrate through an upper connecting rod, and the lower end of the lower short rod is connected with a rotating shaft on the first solar wing substrate through a lower connecting rod; the long rods are rotatably connected with the short rods and the adjacent two long rods through unfolding shafts, and each long rod is also connected with the corresponding rotating shaft through a long rod connecting rod; sliding wheels are arranged on the upper connecting rod, the lower connecting rod and the unfolding shaft;
the hinge structure comprises a male hinge and a female hinge, the male hinge and the female hinge are rotatably connected and matched to form a through hole for inserting a rotating shaft, fixing holes fixed with corresponding solar wing substrates are respectively formed in the male hinge and the female hinge, and the male hinge and the female hinge are fixed on two sides of the male hinge through retaining rings after the rotating shaft is inserted into the through hole;
one end of the locking structure is connected with the lower short rod, and the other end of the locking structure is abutted with the satellite body; the satellite body is provided with a locking part matched with the locking structure; during deployment of the deployment rod assembly, the locking structure moves with the deployment rod assembly to the locking portion and cooperates with the locking portion to lock the deployment rod assembly to the satellite body;
the unfolding power component is arranged on the satellite body and comprises a power part and an accommodating part, the accommodating part is provided with an accommodating space for accommodating the tensioning rope, and the power part is used for generating power for releasing the tensioning rope when the solar wing substrate component is unfolded;
one end of the tensioning rope is fixedly connected with the sliding wheel positioned on the upper connecting rod, and the other end of the tensioning rope sequentially bypasses the sliding wheel on the unfolding shaft and the sliding wheel on the lower connecting rod and is fixed in the accommodating space; when the solar wing substrate assembly is in an unfolded state, the tensioning rope is in a tensioned state, and when the solar wing substrate is in a folded state, the tensioning rope is in a relaxed state;
one end of the compaction structure is fixedly connected with the Mth solar wing substrate, and the other end of the compaction structure is connected with the satellite body, so that the solar wing substrate assembly is kept in a folded state before being unfolded;
when the solar wing substrate needs to be unfolded, the pressing force of the pressing structure is released so that the solar wing substrate is unfolded.
2. The solar wing spreading device according to claim 1, wherein the solar wing base plate is provided with a plurality of protrusions, and when the solar wing base plate is in a folded state, the protrusions of two adjacent solar wing base plates abut against each other.
3. The solar wing deployment device of claim 1, wherein a sleeve is disposed on the rotational axis of the first solar wing substrate.
4. The solar wing deployment device of claim 1, wherein the locking structure comprises a locking pin cover, a locking pin, and a locking spring;
one end of the locking pin cover is connected with the lower short rod, the other end of the locking pin cover is movably connected with the satellite body, and the lower short rod and the locking pin cover are matched with each other to form an insertion hole; the locking pin is inserted into the insertion hole and is provided with a stopping part; the locking spring is arranged outside the locking pin and above the stopping part;
the locking part is a locking hole;
when the unfolding rod assembly is in a fully unfolded state, the locking pin is inserted into the locking hole under the action of the elastic force of the locking spring so as to lock the unfolding rod assembly on the satellite body.
5. The solar wing deployment device of claim 1, wherein the deployment power assembly further comprises a stationary plate fixedly connected to the satellite body;
the accommodating part comprises a shell, the accommodating space is formed in the shell, a baffle protruding outwards is formed on the side part of the shell, and a stirring part is arranged on the baffle;
the power part comprises a rotating rod and a torsion spring; the upper end of the rotating rod penetrates through the accommodating space to be rotatably connected with the shell, and the lower end of the rotating rod penetrates through the torsion spring and is rotatably connected with the fixed plate; the upper end of the rotating rod is used for winding the tensioning rope; the end of the torsion spring is provided with a concave part, and the poking piece is inserted into the concave part.
6. The solar wing deployment device of claim 1, further comprising a plurality of guide brackets disposed on the satellite body for guiding the tension line to the receptacle.
7. The solar wing deployment device of claim 1, said tensioning line being a wire rope.
8. The solar wing deployment device of claim 1, wherein the upper connection bar is connected to the mth solar wing substrate by a fastener;
the mounting includes the fixed block, the one end of fixed block with the Mth solar wing base plate is connected, and the other end is provided with the installation axle, install epaxial be provided with the connecting hole that the upper junction pole is connected.
9. The solar wing unfolding apparatus according to claim 1, wherein the pressing structure is a locking rope, one end of the locking rope is fixedly connected with the sliding wheel of the upper connecting rod, and the other end of the locking rope is connected with the satellite body.
10. The solar wing unfolding apparatus according to claim 1, wherein the compression structure is an explosive bolt, and the explosive bolt sequentially penetrates through the M solar wing substrates from top to bottom and is fixed on the satellite body.
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| CN202111340188.0A CN113772125B (en) | 2021-11-12 | 2021-11-12 | Sun wing unfolding device |
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| CN115009541B (en) * | 2021-04-12 | 2023-12-26 | 北京邮电大学 | Hinge formula expansion mechanism that turns over of rope linkage |
| CN115009546B (en) * | 2022-08-08 | 2022-11-04 | 银河航天(北京)网络技术有限公司 | Pressing force adjusting mechanism, system and method for stacking satellite solar wings |
| CN116552811A (en) * | 2023-07-11 | 2023-08-08 | 北京大学 | Folding and unfolding device |
| 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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| JP2902652B2 (en) * | 1988-10-06 | 1999-06-07 | 株式会社東芝 | Disturbance torque control device |
| DE19819955C2 (en) * | 1998-05-05 | 2000-06-29 | Eurocopter Deutschland | Rope connection for solar panel deployment on satellites |
| CN106240845B (en) * | 2016-08-04 | 2019-10-18 | 北京空间飞行器总体设计部 | A kind of passive type flexibility sun span spasm leads mechanism |
| CN108412987B (en) * | 2018-03-14 | 2020-10-30 | 北京航空航天大学 | Direction-changeable pulley device for rope-driven deployable mechanism |
| CN209080191U (en) * | 2018-11-16 | 2019-07-09 | 北京微分航宇科技有限公司 | A kind of solar wing unlock unfolding mechanism |
| CN112238952B (en) * | 2020-10-27 | 2022-02-15 | 东方红卫星移动通信有限公司 | Satellite solar cell sailboard |
| CN112278337A (en) * | 2020-11-20 | 2021-01-29 | 天津航天机电设备研究所 | Unfolding test device of super-large-area high-storage-ratio light 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 |
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