Scissor-fork type solar wing unfolding device based on planar four-bar mechanism

Abstract

The invention belongs to the technical field of solar wing unfolding machinery, and particularly relates to a shears-fork type solar wing unfolding device based on a planar four-bar mechanism, which comprises an unfolding base assembly, a countersunk head assembly, a guide mechanism, a positioning assembly, a connecting assembly and a top plate arranged on the side wall of the connecting assembly, the shear fork type solar wing unfolding device based on the plane four-bar mechanism is composed of the rigid unfolding mechanism and the flexible solar wing film, and the flexible solar wing film is supported and tensioned after the shear fork type solar wing unfolding device is completely unfolded; the anti-bending section coefficient of the rod piece is high, and meanwhile, the rod piece is positioned in the axial direction in the form of an end cover and a set screw; the connecting pieces at the two ends of the shear fork rod facilitate complete positioning of pressing, the guide assembly is arranged, the folding condition of the solar wing is conveniently maintained, a guide rope keeps certain compactness and rigidity in the unfolding process of the whole mechanism, and when the flexible solar wing adopts a four-point tensioning mode, the system has higher fundamental frequency, and the stability of the system is improved. And the stability and the reliability are improved.

Description

Technical Field

[0001] The invention relates to the technical field of solar wing unfolding machinery, and in particular to a scissor-type solar wing unfolding device based on a planar four-bar mechanism. Background Art

[0002] Flexible solar wings have the characteristics of small envelope, light weight, and modularity. They can perfectly meet the envelope requirements of flat-panel satellite layered stacking, making it possible to launch large-scale satellite stacking. Solar wings are the main source of satellite energy. Depending on the substrate that carries the battery cells, solar wings are divided into rigid, semi-rigid and flexible solar wings. Traditional rigid solar wings have a relatively thick substrate and a large gap between the boards, resulting in a relatively large overall "block", which occupies a lot of the spacecraft's outer envelope. Semi-rigid solar wings are similar.

[0003] However, in actual use, the frame-type deployment mechanism used in super-large flexible solar wings such as the International Space Station is not applicable. The basic mass of the frame-type deployment mechanism is heavy, and its advantages can only be reflected when the number of deployment sections or the length is very long and the size of the solar wing is very large. After the folded state is opened, the flexible solar wing film is difficult to provide support and tensioning effects. In addition, the hinged or rope-driven deployment mechanism is only applicable to rigid solar wings. Both the inflatable deployment and centrifugal deployment have obvious defects, such as the overall weight of the accessories is heavy, the friction between each other is large, and it is difficult to position adjacent connectors under compression, which reduces the ability to withstand impact loads. There is a lack of guidance during the deployment of the solar wing, and it is difficult to maintain compactness and rigidity during the deployment process. Finally, during the deployment of the flexible solar wing, there is a lack of tensioning cooperation for four-point positioning, poor stability and low reliability. These are all actual problems that need to be solved urgently. Summary of the invention

[0004] The purpose of the present invention is to provide a scissor-type solar wing deployment device based on a planar four-bar mechanism, so as to solve the problem that the frame-type deployment mechanism used in super-large flexible solar wings such as the International Space Station proposed in the above-mentioned background technology is not applicable. The basic mass of the frame-type deployment mechanism is heavy, and its advantages can only be reflected when the number of deployment sections or the length is very long and the size of the solar wing is very large. Moreover, after the folded state is opened, the flexible solar wing film is difficult to provide support and tensioning effects. In addition, the hinge-type or rope-driven deployment mechanism is only applicable to rigid solar wings, and the inflation deployment and centrifugal force deployment have obvious defects, such as the overall mass of the accessories is heavy, the friction between each other is large, and in the case of compression, it is difficult to position the adjacent connecting parts, which reduces the ability to withstand impact loads, lacks guidance during the solar wing deployment process, and it is difficult to maintain compactness and rigidity during the deployment process. Finally, during the deployment of the flexible solar wing, there is a lack of tensioning cooperation for four-point positioning, poor stability and low reliability.

[0005] To achieve the above-mentioned purpose, the present invention provides the following technical solution: comprising an unfolding base assembly, a countersunk assembly, a guide mechanism, a positioning assembly, a connecting assembly and a top plate arranged on the side wall of the connecting assembly;

[0006] in:

[0007] An unfolding base assembly, the unfolding base assembly includes a bottom plate, a ramp plate integrally connected to the top of the bottom plate, and a motor seat arranged on the top of the ramp plate, a motor is arranged on the top of the motor seat, and a motor rod connected to the countersunk assembly is arranged at the output end of the motor;

[0008] A countersunk head assembly, wherein a cross bar 1 is arranged at the other end of the countersunk head assembly, a plurality of groups of carbon fiber scissor rods in a vertically cross-shaped manner are hingedly connected to the side wall of the countersunk head assembly, constant force springs are arranged at both ends of the cross bar 1, and a flexible solar wing film is arranged at the top of the cross bar 1;

[0009] A guide assembly, the guide assembly comprising a transverse plate arranged on a side wall of the ramp plate;

[0010] A positioning assembly, the positioning assembly comprising a connecting block disposed on a side wall of the countersunk assembly;

[0011] A connecting assembly, the connecting assembly comprising a connecting buckle arranged on the top of the carbon fiber scissor rod, a plurality of connecting plates are arranged on the top of the connecting buckle, and a second cross bar is connected to the side wall of the connecting plate by snap-fitting;

[0012] A top plate includes a transverse frame arranged on two side walls of the cross bar.

[0013] Preferably, the countersunk assembly includes a countersunk, a pin shaft hole arranged on the side wall of the countersunk, a conical countersunk hole and a square hole arranged on the top of the countersunk, and an empty groove arranged on the side wall of the countersunk, and a threaded hole is reserved at the bottom of the inner cavity of the empty groove.

[0014] Preferably, a pin is passed through the circumferential inner wall of the plurality of pin holes, an L-shaped sleeve is sleeved on the circumferential outer wall of the pin, an end cover is snap-connected to the side wall of the pin, and a fastening screw is passed through the side wall of the end cover.

[0015] Preferably, a transverse plate hole is reserved at the top of the transverse plate, a triangular plate and a bracket are integrally connected at the bottom of the transverse plate, ear plates are oppositely arranged at the bottom of the bracket, a winding wheel is penetrated through the side wall of the ear plate, and a plate cover is penetrated through the winding wheel.

[0016] Preferably, triangle plates 2 are arranged opposite to each other on the top of the plate cover, and the side walls of the triangle plates 2 are provided with torsion spring rods, the circumferential outer walls of the torsion spring rods are sleeved with torsion springs, and one end of the torsion spring is provided with a clamping plate that fits with the side wall of the plate cover.

[0017] Preferably, the top of the connecting block is integrally formed with a reserved V-shaped groove, and the bottom of the connecting block is integrally formed with a reserved spherical surface that matches the position and size of the V-shaped groove.

[0018] Preferably, the transverse frame comprises T-shaped combination buckles arranged at equal intervals, the side walls of the plurality of T-shaped combination buckles are provided with vertical frames, and the ends of the plurality of groups of vertical frames are sleeved with cross-shaped combination buckles.

[0019] Preferably, a wire wheel corresponding to the guide assembly is provided at the bottom of the second crossbar, and a guide rope is wound between the guide assembly and the wire wheel.

[0020] Preferably, the flexible solar wing film is stored in an accordion-shaped folding manner, and the length of the flexible solar wing film is consistent with the unfolded height of the multiple groups of carbon fiber scissor rods.

[0021] Preferably, rotatable constant force springs are provided on both sides of the cross bar 1 and the cross bar 2, and the four constant force springs are respectively connected to the four corners of the flexible solar wing film.

[0022] Compared with the prior art, the present invention has the following beneficial effects:

[0023] 1. This scissor-type solar wing deployment device based on a planar four-bar mechanism is composed of a rigid deployment mechanism and a flexible solar wing film. The main body of the rigid deployment mechanism is composed of multiple pairs of scissor-type rods, the root of which is connected to the bottom frame and the top of which is connected to the top frame. At the same time, the top frame is also connected to the top plate, and the bottom frame is also connected to the bottom plate. The two plates are used to compress and protect the solar wing in the folded state when the mechanism is folded. When deploying, multiple pairs of scissor-type rods open synchronously, driving the top frame to move away from the bottom frame, thereby pulling the solar wing to open from the folded state, and providing support and tension for the flexible solar wing film after it is fully deployed.

[0024] 2. This scissor-type solar wing deployment device based on a planar four-bar mechanism uses carbon fiber hollow bars and aluminum alloy connectors as the rods. The carbon fiber bars have a square outer and round inner cross-section. Compared with the concentric circle cross-section, it has a higher bending section coefficient, better strength and stiffness, and is easier to position and assemble. Compared with the hollow rectangular cross-section, it does not have the problem of stress concentration at the four corners, and has a light overall mass and high stability. At the same time, the two rods are connected by a pin shaft, and a wear-resistant and self-lubricating L-shaped Teflon sleeve is added between the pin shaft and the rod. The axial positioning uses an end cover and a set screw to facilitate assembly, minimize the clearance between the rotating pairs, and reduce friction.

[0025] 3. This scissor-type solar wing deployment device based on a planar four-bar mechanism has a fully positioned design for compression on the two end connectors of the scissor rods. Two V-shaped grooves are processed on the upper surface of each connector, and a spherical surface is processed at the corresponding position on the lower surface. When the scissor mechanism is partially subjected to compression force, the adjacent scissor rods contact each other to ensure that each adjacent connector is fully positioned. Under the action of the compression force, the ability of the entire mechanism to withstand impact loads is greatly improved;

[0026] 4. This scissor-type solar wing deployment device based on a planar four-bar mechanism is provided with a guide assembly. One end of the guide rope is wound around the wire wheel at the bottom, and the other end is fixed to the top frame. During the deployment process, the wire wheel rotates continuously, and the guide rope is gradually stretched. A small hole is punched at the corresponding position of each solar wing, and the guide rope passes through it, so that the folding state of the solar wing is maintained, and the guide rope maintains a certain degree of compactness and rigidity during the deployment process of the entire mechanism, playing a role in supporting the flexible solar wing;

[0027] 5. This scissor-type solar wing deployment device based on a planar four-bar mechanism has a higher fundamental frequency when the flexible solar wing adopts a four-point tensioning method. Therefore, the solar wing is tensioned by a four-point tensioning method, that is, tensioning force is applied to the four corners of the flexible film, and its rotation can passively adapt to the lateral displacement of the upper and lower plates, thereby improving stability and reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the present invention will be described in detail below in combination with the accompanying drawings and detailed embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative labor. Among them:

[0029] Figure 1 It is a schematic diagram of the overall structure of the scissor-type solar wing deployment device based on a planar four-bar mechanism of the present invention;

[0030] Figure 2 It is a schematic diagram of the countersunk head assembly of the scissor-type solar wing deployment device based on the planar four-bar mechanism of the present invention;

[0031] Figure 3 It is a schematic diagram of the rotating subassembly of the scissor-type solar wing deployment device based on the planar four-bar mechanism of the present invention;

[0032] Figure 4 It is a schematic diagram of the countersunk head assembly and the rod body of the scissor-type solar wing deployment device based on the planar four-bar mechanism of the present invention;

[0033] Figure 5 It is a schematic diagram of a guide assembly of a scissor-type solar wing deployment device based on a planar four-bar mechanism of the present invention;

[0034] Figure 6 It is a schematic diagram of the unfolding process of the scissor-type solar wing unfolding device based on the planar four-bar mechanism of the present invention;

[0035] Figure 7 It is a schematic diagram of an unfolding base assembly of a scissor-type solar wing unfolding device based on a planar four-bar mechanism of the present invention;

[0036] Figure 8 It is a schematic diagram of the positioning assembly of the scissor-type solar wing deployment device based on the planar four-bar mechanism of the present invention;

[0037] Fig. 9 It is a schematic diagram of the complete deployment of the scissor-type solar wing deployment device based on the planar four-bar mechanism of the present invention.

[0038] In the figure: 100, unfolded base assembly; 110, bottom plate; 120, ramp plate; 130, motor seat; 140, motor; 150, motor rod; 160, cross bar 1; 170, carbon fiber scissor rod; 180, flexible solar wing film; 190, constant force spring; 200, countersunk assembly; 210, countersunk; 220, pin hole; 221, pin; 222, L-shaped bushing; 223, end cover; 224, fastening screw; 230, tapered countersunk hole; 240, square hole; 250, empty slot; 260, threaded hole; 300, guide assembly; 310 , horizontal plate; 311, horizontal plate hole; 312, triangle plate one; 320, bracket; 330, ear plate; 331, winding wheel; 340, plate cover; 341, triangle plate two; 342, torsion spring rod; 343, torsion spring; 350, clamping plate; 400, positioning assembly; 410, connecting block; 411, V-shaped groove; 412, spherical surface; 500, connecting assembly; 510, connecting buckle; 520, connecting plate; 530, horizontal bar two; 600, top plate; 610, horizontal frame; 620, T-shaped combination buckle; 630, vertical frame; 640, cross-shaped combination buckle. DETAILED DESCRIPTION

[0039] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0040] In the description of the present invention, “plurality” means two or more than two, unless otherwise clearly and specifically defined.

[0041] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "provided with", "mounted / connected", "connected", etc. should be understood in a broad sense. For example, "connected" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0042] The present invention provides a scissor-type solar wing deployment device based on a planar four-bar mechanism, which is composed of a rigid deployment mechanism and a flexible solar wing film. The main body of the rigid deployment mechanism is composed of multiple pairs of scissor-type rods, the root of which is connected to the bottom frame, and the top of which is connected to the top frame; at the same time, the top frame is also connected to the top plate, and the bottom frame is also connected to the bottom plate. The two plates are used to compress and protect the solar wing in a folded state when the mechanism is folded. When unfolding, multiple pairs of scissor-type rods are opened synchronously, driving the top frame to move away from the bottom frame, thereby pulling the solar wing to open from the folded state, and providing support and tension for the flexible solar wing film after fully unfolding. The rod member is in the form of a carbon fiber hollow rod and an aluminum alloy connector, and the carbon fiber rod has a cross-sectional shape of an outer square and an inner circle. Compared with the concentric circle section, it has a higher bending section coefficient, better strength and rigidity, and is easier to position and assemble; compared with the hollow rectangular section, it does not have the problem of stress concentration at the four corners, the overall weight is light, and the stability is high. At the same time, the two rods are connected by a pin, and a wear-resistant and self-lubricating L-shaped Teflon sleeve is added between the pin and the rod; the axial positioning adopts the form of end covers and set screws, which is easy to assemble and minimizes the clearance of the rotating pair as much as possible, while also reducing friction. A full positioning design for clamping is added to the connecting parts at both ends of the scissor rod. Two V-shaped grooves are machined on the upper surface of each connecting part, and a spherical surface is machined at the corresponding position on the lower surface. When the scissor mechanism is partially subjected to compression force, adjacent scissor rods contact each other to ensure that each adjacent connecting piece is fully positioned. Under the action of compression force, the ability of the entire mechanism to withstand impact loads is greatly improved. A guide assembly is provided, one end of the guide rope is wound around the bottom wire wheel, and the other end is fixed to the top frame. During the unfolding process, the wire wheel rotates continuously, and the guide rope gradually stretches. Small holes are punched at the corresponding positions of each solar wing, through which the guide rope passes. This maintains the folding state of the solar wing, and also enables the guide rope to maintain a certain degree of compactness and rigidity during the unfolding process of the entire mechanism, playing a role in supporting the flexible solar wing. When the flexible solar wing adopts a four-point tensioning method, the system has a higher fundamental frequency, so the four-point tensioning method is used to tension the solar wing, that is, tension is applied to the four corners of the flexible film, and its rotation can passively adapt to the lateral displacement of the upper and lower plates, thereby improving stability and reliability. Please refer to Figures 1 to 9 , including an unfolding base assembly 100, a countersunk assembly 200, a guide mechanism 300, a positioning assembly 400, a connecting assembly 500 and a top plate 600 disposed on a side wall of the connecting assembly 500;

[0043] The unfolding base assembly 100 includes a base plate 110, a ramp plate 120 integrally connected to the top of the base plate 110, a motor seat 130 disposed on the top of the ramp plate 120, a motor 140 disposed on the top of the motor seat 130, and a motor rod 150 connected to the countersunk assembly 200 disposed at the output end of the motor 140;

[0044] The other end of the countersunk assembly 200 is provided with a crossbar 160, and the side wall of the countersunk assembly 200 is hinged with multiple groups of carbon fiber scissor rods 170 in a vertically crossed manner. During the unfolding process, the motor 140 drives the motor rod 150 to rotate, and then drives the three pairs of carbon fiber scissor rods 170 to open upward, pushing the crossbar 2 530 to move upward, and finally unfolding the folded solar wing. The crossbar 160 and the crossbar 2 530 are respectively connected to the proximal end and the distal end of the flexible solar wing film 180, supporting the solar wing after unfolding and providing tension. Constant force springs 190 are provided at both ends of the crossbar 160, and a flexible solar wing film 180 is provided on the top of the crossbar 160. The flexible solar wing film 180 is stored in an accordion-shaped folding manner, which is similar to the folding manner of the traditional rigid solar wing substrate.

[0045] The connection between the crossbar 1 160 and the crossbar 2 530 and the bottom frame is separated, and the crossbar 1 160 and the crossbar 2 530 are transmitted through a crank rocker mechanism, so that the movement can be kept approximately symmetrical during the unfolding process. Such a design can improve the reliability of the mechanism and increase the rigidity in the left and right directions. At the same time, a completely identical four-bar mechanism is configured at the connection between the top plate 600 and the carbon fiber scissor rod 170, so that the top plate 600 and the bottom frame always remain parallel during the unfolding process;

[0046] In some embodiments, the specific parameters of the four-bar mechanism are designed next. In order to keep the bottom plate 110 and the top plate 600 parallel in the compressed state and the unfolded state, it is necessary to meet the following conditions: when the angle between the crossbar 160 and the frame is 0°, the crossbar 160 and the crossbar 2 530 are both horizontal; when the angle is 90°, the crossbar 160 and the crossbar 2 530 are both perpendicular to the frame. Written in the form of an equation:

[0047]

[0048] If l0 is too long, the weight of the four-bar mechanism will also be higher. If it is too short, the left-right stiffness will not be significantly improved. Considering that the short side of the solar wing is 3m, l0=600mm is taken, and the lengths of the remaining three bars are calculated by the formula:

[0049]

[0050] At the same time, according to the requirement that the length of the solar wing is greater than 6m, three pairs of carbon fiber scissor rods 170 are taken, and the length l of the carbon fiber scissor rod 170 is calculated. s =1.8m. Theoretically, the length of the entire mechanism after unfolding is

[0051]

[0052] meet the requirements;

[0053] The guide assembly 300 includes a horizontal plate 310 disposed on the side wall of the ramp plate 120, and a plurality of small holes are provided on the horizontal plate 310 to facilitate the entry of the guide rope;

[0054] The positioning assembly 400 includes a connection block 410 disposed on the side wall of the countersunk assembly 200. The connection block 410 is disposed to facilitate positioning and cooperation, and to facilitate the formation of a V-shaped groove 411 and a spherical surface 412 structure.

[0055] The connection assembly 500 includes a connection buckle 510 disposed on the top of the carbon fiber scissor rod 170, a plurality of connection plates 520 are disposed on the top of the connection buckle 510, and a second cross bar 530 is snap-connected to the side wall of the connection plate 520;

[0056] The top plate 600 includes a transverse frame 610 disposed on the side wall of the second transverse bar 530. The transverse frame 610 has a T-shaped combination buckle 620. The T-shaped combination buckle 620 is used to combine the vertical frame 630. When the transverse frame 610 and the vertical frame 630 are intertwined, they are combined through the cross-shaped combination buckle 640 to form a mesh structure.

[0057] In some embodiments, when the solar wing is not unfolded, the entire mechanism and the flexible solar wing film 180 are packaged together in the fairing of the launch rocket. During transportation and launch, the environment is relatively harsh and will be adversely affected by irregular impact loads, vibrations, temperature changes, etc. In order to prevent the flexible solar wing film 180 from being damaged before unfolding, it is necessary to compress and protect it before unfolding. A rigid frame and foam substrate design is adopted, in which the rigid frame is in a grid shape and is also composed of carbon fiber rods and aluminum connectors. The aluminum connectors serve as nodes of the grid, and the carbon fiber rods serve as edges of the grid. The frame is glued to the hard polyimide foam, and these two layers of foam are in direct contact with the flexible solar wing film 180, which plays a protective role;

[0058] Through holes are punched at each aluminum connector or node of the frame to facilitate connection between the upper and lower parts. A commercial locking device is used, specifically the FLLM-2C double-layer clamp from Differential Aerospace. The locking device is installed between the upper and lower plates at the four corners and the two most central nodes to completely clamp the upper and lower plates and the folded flexible solar wing in the middle. When release is required, the memory alloy pin puller in the locking device is powered on to unlock, and the spring is pushed away to achieve low-impact unlocking;

[0059] In addition, the conventional accessories and conventional structures involved in the present invention are all prior art, and can be fully implemented by those skilled in the art. Needless to say, the content protected by the present invention does not involve improvements to the internal structure and method;

[0060] Working principle: During specific use, firstly, a ramp plate 120 is arranged on the bottom plate 110 of the unfolding base assembly 100 to facilitate the installation of the motor seat 130 carrying the motor 40. The motor 140 is connected to the motor rod 150, and will cooperate with the carbon fiber scissor rod 170 on the cross bar 160 to unfold during driving. During the unfolding process of multiple sets of carbon fiber scissor rods 170, the flexible solar wing film 180 will be opened. At the same time, the countersunk assembly 200 is used to connect the carbon fiber scissor rods 170, and a wear-resistant and self-lubricating L-shaped bushing 222 is added between the pin shaft 221 and the rod member. The material may be Teflon; the pin shaft 221 is positioned upward in the form of an end cover 223 and a set screw 224 for easy assembly. At the same time, a guide assembly 300 is also arranged. The guide assembly 300 includes a guide rope wound on a winding wheel 331, and the winding wheel 331 can rotate freely around the axis. On another axis parallel to it, a torsion spring 343 is installed on the axis to provide a torque tending to tighten inward, so that the clamping plate 350 clamps the winding wheel 331. Therefore, when the guide rope is pulled upward, it will be subjected to the friction of the clamping plate 350, so that the guide rope maintains a certain degree of compactness and rigidity during the entire mechanism deployment process, playing a role in supporting the flexible solar wing. At the same time, there is a connecting block 410 at the end of the carbon fiber scissor rod 170, and the top of the connecting block 410 has a V-shaped groove 411, and the bottom of the connecting block 410 has a spherical surface 412, and the two can cooperate with each other for positioning, and the top plate 600 has a transverse frame 610 carrying a T-shaped combination buckle 620 and a vertical frame 630 carrying a cross-shaped combination buckle 640, and the two can be spliced ​​together to form a mesh structure.

[0061] At the same time, in order to drill two threaded holes 260 at corresponding positions on the countersunk assembly 200, and then drill two tapered countersunk holes 230 on the upper surface, so that only two countersunk screws are needed to completely position and lock the carbon fiber scissor rod 170 and the aluminum connector, without the need for screws and nuts to lock, which can save the weight of two nuts. Specifically, the countersunk assembly 200 includes a countersunk 210, a pin shaft hole 220 arranged on the side wall of the countersunk 210, a tapered countersunk hole 230 and a square hole 240 arranged on the top of the countersunk 210, and an empty groove 250 arranged on the side wall of the countersunk 210. A threaded hole 260 is reserved at the bottom of the inner cavity of the empty groove 250, which can ensure the stability of the mechanism. The strength, rigidity and stability of each rod must be ensured.

[0062] Subsequently, in order to make the movement of the actual mechanism completely consistent with the theory, it is necessary to reduce the clearance of the rotating pair as much as possible, and at the same time reduce the friction. In the planar connecting rod mechanism, the design of the rotating pair is equally important. Specifically, the circumferential inner wall of the plurality of pin shaft holes 220 is penetrated by a pin shaft 221, the circumferential outer wall of the pin shaft 221 is sleeved with an L-shaped sleeve 222, the side wall of the pin shaft 221 is snap-connected with an end cover 223, and the side wall of the end cover 223 is penetrated by a fastening screw 224.

[0063] Next, in order to wind the guide rope around the reel, the reel can rotate freely around the axis. On another axis parallel to it, a rotatable clamping plate 350 is installed, and a torsion spring 343 is installed on the torsion spring rod 342, providing a torque tending to tighten inward, so that the clamping plate 350 clamps the reel. Therefore, when the guide rope is pulled upward, it will be subject to the friction of the clamping plate 350, so that the guide rope maintains a certain degree of tightness and rigidity during the entire mechanism deployment process, playing a role in supporting the flexible solar wing. Specifically, a cross plate hole 311 is reserved at the top of the cross plate 310, and the bottom of the cross plate 310 is integrally formed with a triangular plate 312 and a bracket 320, and an ear plate 330 is oppositely arranged at the bottom of the bracket 320, and the side wall of the ear plate 330 is penetrated by a winding wheel 331, and the winding wheel 331 is penetrated by a plate cover 340.

[0064] Furthermore, in order to enable the clamping plate 350 to cooperate with the torsion spring 343 to generate a rebound force, specifically, a triangular plate 2 341 is arranged opposite to the top of the plate cover 340, and the side walls of the plurality of triangular plates 2 341 are provided with a torsion spring rod 342, and the circumferential outer wall of the torsion spring rod 342 is sleeved with a torsion spring 343, and one end of the torsion spring 343 is provided with a clamping plate 350 that fits with the side wall of the plate cover 340.

[0065] Next, in order to add a complete positioning design for compression to the positioning components 400 at both ends of the carbon fiber scissor rod 170, specifically, the top of the connecting block 410 is integrally formed with a reserved V-shaped groove 411, and the bottom of the connecting block 410 is integrally formed with a reserved spherical surface 412 that matches the position and size of the V-shaped groove 411. If there is no special positioning design, they are in plane contact, which is easy to tilt and become point contact, which will make the scissor mechanism part incompletely positioned in the undeployed state, easy to shake, and very easy to loosen or even fail under the impact load environment;

[0066] In some embodiments, after the solar wing is unfolded and tensioned, the entire mechanism needs to be locked to prevent any displacement or shaking. A locking mechanism can be set to lock when the angle between the rod body and the horizontal reaches 90°. A spring plus a round-headed slider is used in conjunction with a locking groove. During the rotation of the rod body, the round-headed slider gradually approaches the locking groove along the inclined surface under the action of the spring; when the limit position is reached, the round-headed slider enters the groove and the mechanism is locked. At this time, the mechanism will theoretically no longer have any displacement, and the degree of shaking depends on the matching tolerance of the slider and the groove. This part of the structure is a prior art, and the locking mechanism commonly used on the market can be directly selected.

[0067] Subsequently, in order to facilitate the mutual combination of the transverse frame 610 and the vertical frame 630, specifically, the transverse frame 610 includes T-shaped combination buckles 620 arranged at equal intervals, the side walls of multiple T-shaped combination buckles 620 are provided with vertical frames 630, and the ends of multiple groups of vertical frames 630 are socketed with cross-shaped combination buckles 640.

[0068] It is worth noting that because the flexible solar wing film 180 is in a Z-shaped folded state before and during the unfolding process, in order to prevent the folding of the flexible solar wing film 180 from being disrupted during the unfolding process, it needs to be constrained and two guide ropes are set. Specifically, a wire wheel corresponding to the guide assembly 300 is provided at the bottom of the second cross bar 530, and a guide rope is wound between the guide assembly 300 and the wire wheel.

[0069] Next, in order to make the flexible solar wing film 180 adapt to the carbon fiber scissor rod 170 after being unfolded, specifically, the flexible solar wing film 180 is stored in an accordion-like folding manner, and the length of the flexible solar wing film 180 is consistent with the unfolded height of multiple groups of carbon fiber scissor rods 170.

[0070] Finally, because the flexible solar wing uses a flexible material substrate such as a polyimide film, it is almost completely flexible and has no ability to withstand external forces to maintain its shape. In order to improve the stiffness of the flexible solar wing, it needs to be properly tensioned. When the flexible solar wing adopts a four-point tensioning method, the system has a higher fundamental frequency, so the solar wing is tensioned by a four-point tensioning method, that is, a tensioning force is applied to the four corners of the flexible film. Specifically, a rotatable constant force spring 190 is provided on both sides of the crossbar 160 and the crossbar 2 530. The four constant force springs 190 are respectively connected to the four corners of the flexible solar wing film 180. The flexible solar wing film 180 of similar size has the highest fundamental frequency when the tension force is 16 to 18N under the condition of four-point tensioning. A constant force spring with a load of 1.8kgf, i.e. 17.64N, is selected, so that after the mechanism is unfolded, the tensioning force on the flexible solar wing film 180 can always remain constant, thereby improving stability and reliability. At the same time, due to the influence of the four-bar mechanism, the system has lateral displacement during the unfolding process. A constant force spring tensioning assembly is designed that can rotate about the axis shown in the figure. During the deployment process, its rotation can passively adapt to the lateral displacement of the upper and lower plates.

[0071] Although the present invention has been described above with reference to the embodiments, various modifications may be made thereto and parts thereof may be replaced with equivalents without departing from the scope of the present invention. In particular, as long as there is no structural conflict, the various features in the embodiments disclosed by the present invention may be used in combination with each other in any manner, and the fact that these combinations are not exhaustively described in this specification is only for the sake of omitting space and saving resources. Therefore, the present invention is not limited to the specific embodiments disclosed herein, but includes all technical solutions falling within the scope of the claims.

Claims

1. A scissor-type solar wing deployment device based on a planar four-bar mechanism, characterized in that: It comprises an unfolding base assembly (100), a countersunk assembly (200), a guide mechanism (300), a positioning assembly (400), a connecting assembly (500), and a top plate (600) arranged on a side wall of the connecting assembly (500); in: An unfolding base assembly (100), the unfolding base assembly (100) comprising a base plate (110), a ramp plate (120) integrally connected to the top of the base plate (110), and a motor seat (130) arranged on the top of the ramp plate (120); a motor (140) is arranged on the top of the motor seat (130); and a motor rod (150) connected to the countersunk assembly (200) is arranged at the output end of the motor (140); A countersunk head assembly (200), wherein the other end of the countersunk head assembly (200) is provided with a cross bar (160), a side wall of the countersunk head assembly (200) is hinged with a plurality of groups of carbon fiber scissor rods (170) in a vertically cross-shaped manner, constant force springs (190) are provided at both ends of the cross bar (160), and a flexible solar wing film (180) is provided at the top of the cross bar (160); A guide assembly (300), the guide assembly (300) comprising a transverse plate (310) arranged on a side wall of the ramp plate (120); A positioning assembly (400), the positioning assembly (400) comprising a connecting block (410) arranged on a side wall of the countersunk assembly (200); A connection assembly (500), the connection assembly (500) comprising a connection buckle (510) arranged at the top of the carbon fiber scissor rod (170), a plurality of connection plates (520) being arranged at the top of the connection buckle (510), and a second cross bar (530) being snap-connected to the side wall of the connection plate (520); A top plate (600) includes a transverse frame (610) disposed on a side wall of the second crossbar (530).

2. The scissor-type solar wing deployment device based on a planar four-bar mechanism according to claim 1 is characterized in that: The countersunk assembly (200) comprises a countersunk device (210), a pin shaft hole (220) arranged on the side wall of the countersunk device (210), a conical countersunk hole (230) and a square hole (240) arranged on the top of the countersunk device (210), and a hollow groove (250) arranged on the side wall of the countersunk device (210), wherein a threaded hole (260) is reserved at the bottom of the inner cavity of the hollow groove (250).

3. The scissor-type solar wing deployment device based on a planar four-bar mechanism according to claim 2 is characterized in that: A pin (221) penetrates the circumferential inner wall of the plurality of pin holes (220), an L-shaped shaft sleeve (222) is sleeved on the circumferential outer wall of the pin (221), an end cover (223) is snap-connected to the side wall of the pin (221), and a fastening screw (224) penetrates the side wall of the end cover (223).

4. The scissor-type solar wing deployment device based on a planar four-bar mechanism according to claim 3 is characterized in that: A transverse plate hole (311) is reserved at the top of the transverse plate (310); a triangular plate (312) and a bracket (320) are integrally formed and connected at the bottom of the transverse plate (310); an ear plate (330) is oppositely arranged at the bottom of the bracket (320); a winding wheel (331) is passed through the side wall of the ear plate (330); and a plate cover (340) is passed through the winding wheel (331).

5. The scissor-type solar wing deployment device based on a planar four-bar mechanism according to claim 4 is characterized in that: A second triangular plate (341) is arranged opposite to the top of the plate cover (340), and a plurality of side walls of the second triangular plate (341) are provided with a torsion spring rod (342). A torsion spring (343) is sleeved on the circumferential outer wall of the torsion spring rod (342), and a clamping plate (350) is arranged at one end of the torsion spring (343) and is in contact with the side wall of the plate cover (340).

6. The scissor-type solar wing deployment device based on a planar four-bar mechanism according to claim 5 is characterized in that: The top of the connection block (410) is integrally formed with a reserved V-shaped groove (411), and the bottom of the connection block (410) is integrally formed with a reserved spherical surface (412) that matches the position and size of the V-shaped groove (411).

7. The scissor-type solar wing deployment device based on a planar four-bar mechanism according to claim 6 is characterized in that: The transverse frame (610) comprises T-shaped combination buckles (620) arranged at equal intervals, the side walls of the plurality of T-shaped combination buckles (620) are provided with vertical frames (630), and the ends of the plurality of groups of vertical frames (630) are sleeved with cross-shaped combination buckles (640).

8. The scissor-type solar wing deployment device based on a planar four-bar mechanism according to claim 7 is characterized in that: A wire wheel corresponding to the guide assembly (300) is arranged at the bottom of the second crossbar (530), and a guide rope is wound between the guide assembly (300) and the wire wheel.

9. The scissor-type solar wing deployment device based on a planar four-bar mechanism according to claim 8 is characterized in that: The flexible solar wing film (180) is stored in an accordion-shaped folding manner, and the length of the flexible solar wing film (180) is consistent with the unfolded height of the multiple groups of carbon fiber scissor rods (170).

10. The scissor-type solar wing deployment device based on a planar four-bar mechanism according to claim 9, characterized in that: Rotatable constant force springs (190) are provided on both sides of the cross bar 1 (160) and the cross bar 2 (530), and the four constant force springs (190) are respectively connected to the four corners of the flexible solar wing film (180).

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