A scissor-type solar wing unfolding device based on planar four-bar mechanism

Abstract

The application discloses to the technical field of solar wing unfolding mechanism, specifically to a scissor type solar wing unfolding device based on a planar four-bar mechanism, which comprises an unfolding base assembly, a countersunk head assembly, a guide assembly, a positioning assembly, a connecting assembly and a top plate arranged on the side wall of the connecting assembly. The scissor type solar wing unfolding device based on the planar four-bar mechanism is composed of a rigid unfolding mechanism and a flexible solar wing film, provides support and tension for the flexible solar wing film after complete unfolding, has a high bending-resistant cross-sectional coefficient of the rod, adopts the form of end cover and locking screw for axial positioning, the two end connectors of the scissor rod are convenient for complete positioning by compression, the guide assembly is arranged, the folding condition of the solar wing is maintained, the guide rope maintains a certain tightness and rigidity during the unfolding process of the whole mechanism, the system has a higher fundamental frequency when the flexible solar wing adopts a four-point tensioning mode, and the stability and reliability are improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of solar wing unfolding mechanism, in particular to a shearing fork type solar wing unfolding device based on a planar four-bar mechanism. BACKGROUND

[0002] Flexible solar wings have the characteristics of small envelope, light weight and modularity, and can perfectly fit the envelope requirements of layered stacking of flat plate satellites, making it possible to launch a large number of satellites in a stacked manner. Solar wings are the main source of energy for satellites. According to the different base plates carrying battery pieces, solar wings are divided into rigid, semi-rigid and flexible solar wings. Traditional rigid solar wings have relatively thick base plates and require a large gap between the plates, resulting in a large overall "block head" and occupying a lot of space for the spacecraft envelope. Semi-rigid solar wings are also similar.

[0003] However, in actual application, the framework type unfolding mechanism used by super large flexible solar wings such as the International Space Station is not suitable. The basic mass of the framework type unfolding mechanism is relatively heavy, and only when the number of unfolding nodes or the length is very long and the size of the solar wing is very large can its advantages be reflected. In addition, the hinge type or rope driven type unfolding mechanism is only suitable for rigid solar wings, and the inflation unfolding and centrifugal force unfolding types have obvious defects, such as the overall mass of the fittings is relatively heavy, the friction between them is relatively large, and in the case of compression, it is difficult to position the adjacent connecting pieces, reducing the ability to withstand impact load. In the process of unfolding the solar wing, there is a lack of guidance, and it is difficult to maintain tightness and stiffness during the unfolding process. Finally, in the process of unfolding the flexible solar wing, there is a lack of four-point positioning tensioning cooperation, poor stability and low reliability. These are actual problems that need to be solved urgently. SUMMARY

[0004] The purpose of the present application is to provide a shearing fork type solar wing unfolding device based on a planar four-bar mechanism to solve the problem that the framework type unfolding mechanism used by super large flexible solar wings such as the International Space Station is not suitable. The basic mass of the framework type unfolding mechanism is relatively heavy, and only when the number of unfolding nodes or the length is very long and the size of the solar wing is very large can its advantages be reflected. In addition, the hinge type or rope driven type unfolding mechanism is only suitable for rigid solar wings, and the inflation unfolding and centrifugal force unfolding types have obvious defects, such as the overall mass of the fittings is relatively heavy, the friction between them is relatively large, and in the case of compression, it is difficult to position the adjacent connecting pieces, reducing the ability to withstand impact load. In the process of unfolding the solar wing, there is a lack of guidance, and it is difficult to maintain tightness and stiffness during the unfolding process. Finally, in the process of unfolding the flexible solar wing, there is a lack of four-point positioning tensioning cooperation, poor stability and low reliability.

[0005] To achieve the above object, the present application provides the following technical scheme: including unfolding base assembly, countersunk assembly, guide assembly, positioning assembly, connecting assembly and top plate arranged on the side wall of the connecting assembly;

[0006] Among them:

[0007] The unfolding base assembly comprises a bottom plate, a slope plate integrally connected to the top of the bottom plate, a motor seat arranged on the top of the slope plate, a motor arranged on the top of the motor seat, and a motor rod connected with the countersunk assembly arranged on the output end of the motor;

[0008] The countersunk assembly is provided with a horizontal rod one at the other end, a plurality of groups of carbon fiber scissors fork rods are hinged on the side wall of the countersunk assembly in a vertical cross type, constant force springs are arranged at both ends of the horizontal rod one, and a flexible solar wing film is arranged on the top of the horizontal rod one;

[0009] The guide assembly comprises a horizontal plate arranged on the side wall of the slope plate, a horizontal plate hole is reserved on the top of the horizontal plate, a triangular plate one and a bracket are integrally connected on the bottom of the horizontal plate, ear plates are oppositely arranged on the bottom of the bracket, wire reels are penetrated through the side wall of the ear plate, plate covers are penetrated through the wire reels, triangular plate twos are oppositely arranged on the top of the plate cover, torsion spring rods are arranged on the side wall of a plurality of triangular plate twos, torsion springs are sleeved on the circumferential outer wall of the torsion spring rods, and pressing plates matched with the side wall of the plate cover are arranged on one end of the torsion springs;

[0010] The positioning assembly comprises a connecting block arranged on the side wall of the countersunk assembly, a V-shaped groove is integrally reserved on the top of the connecting block, and a spherical surface matched with the position and size of the V-shaped groove is integrally reserved on the bottom of the connecting block;

[0011] The connecting assembly comprises a connecting buckle arranged on the top of the carbon fiber scissors fork rod, a plurality of connecting plates are arranged on the top of the connecting buckle, and a horizontal rod two is buckled connected on the side wall of the connecting plate;

[0012] The top plate comprises a horizontal frame arranged on the side wall of the horizontal rod two.

[0013] Preferably, the countersunk assembly comprises a countersinker, pin shaft holes arranged on the side wall of the countersinker, a conical countersink hole and a square hole arranged on the top of the countersinker, and an air slot arranged on the side wall of the countersinker, wherein a threaded hole is reserved on the inner cavity bottom of the air slot.

[0014] Preferably, a plurality of pin shafts are penetrated through the circumferential inner wall of the pin shaft hole, an L-shaped shaft sleeve is sleeved on the circumferential outer wall of the pin shaft, an end cap is buckled connected on the side wall of the pin shaft, and a fastening screw is penetrated through the side wall of the end cap.

[0015] Preferably, the transverse frame comprises T-shaped combination buckles arranged at equal intervals, the side walls of the T-shaped combination buckles are provided with vertical frames, and the ends of the vertical frames are sleeved with cross-shaped combination buckles.

[0016] Preferably, the bottom of the second crossbar is provided with a wire wheel corresponding to the guide assembly, and a guide rope is wound between the guide assembly and the wire wheel.

[0017] Preferably, the flexible solar wing film is folded in an accordion form for storage, and the length of the flexible solar wing film is consistent with the unfolding height of the groups of carbon fiber scissors levers.

[0018] Preferably, the two sides of the first crossbar and the second crossbar are provided with rotatable constant force springs, and the four constant force springs are connected with the four corner positions of the flexible solar wing film, respectively.

[0019] Compared with the prior art, the beneficial effects of the present application are:

[0020] 1. The scissor-type solar wing unfolding device based on a planar four-bar mechanism is composed of a rigid unfolding mechanism and a flexible solar wing film, the main body of the rigid unfolding mechanism is composed of multiple pairs of scissors levers, the root is connected with a bottom frame, and the top is connected with a top frame; at the same time, the top frame is also connected with a top plate, and the bottom frame is also connected with a bottom plate, and the two plates are used to compress and protect the solar wing in the folded state when the mechanism is folded; when unfolded, the multiple pairs of scissors levers 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 complete unfolding;

[0021] 2. The scissor-type solar wing unfolding device based on a planar four-bar mechanism, the rod is in the form of a carbon fiber hollow rod and an aluminum alloy connecting piece, and the carbon fiber rod adopts an outer square and inner circle cross-sectional shape. Compared with a concentric circular cross section, the bending section modulus is higher, the strength and rigidity are better, and it is more convenient for positioning and assembly; compared with a hollow rectangular cross section, it does not have the problem of four-corner stress concentration, the overall quality is light, the stability is high, at the same time, a L-shaped Teflon bushing with wear resistance and self-lubricating property is added between the pin shaft and the rod; the positioning in the axial direction adopts the form of end cover and locking screw, which is convenient for assembly, reduces the gap between the rotating pairs as much as possible, and also reduces the friction;

[0022] 3. The scissor type solar wing unfolding device based on the planar four-bar mechanism, two end connectors of the scissor rod are added with complete positioning design for compression, two V-shaped grooves are processed on the upper surface of each connector, and a spherical surface is processed on the corresponding position of the lower surface. When the scissor mechanism part is subjected to compression force, the adjacent scissor rods are in contact with each other, the complete positioning between each adjacent connector is ensured, and the impact load bearing capacity of the whole mechanism is greatly improved under the action of the compression force;

[0023] 4. The scissor type solar wing unfolding device based on the planar four-bar mechanism, a guide assembly is arranged, one end of a guide rope is wound on a bottom line wheel, and the other end is fixed on a top frame. In the unfolding process, the line wheel rotates continuously, the guide rope gradually lengthens, small holes are punched on the corresponding positions of each solar wing, and the guide rope passes through the small holes. In this way, the folding of the solar wing is maintained, and the guide rope maintains a certain tightness and rigidity during the unfolding process of the whole mechanism, thereby supporting the flexible solar wing.

[0024] 5. The scissor type solar wing unfolding device based on the planar four-bar mechanism, when the flexible solar wing adopts a four-point tensioning mode, the system has a higher fundamental frequency, so the four-point tensioning mode is adopted to tension the solar wing, that is, tensioning force is applied to the four corners of the flexible film, and the rotation can passively adapt to the transverse displacement of the upper and lower plates, thereby improving the stability and reliability. BRIEF DESCRIPTION OF DRAWINGS

[0025] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the present application will be described in detail below with reference to the drawings and detailed embodiments. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor. Among them:

[0026] Figure 1 It is a whole structure schematic view of the scissor type solar wing unfolding device based on the planar four-bar mechanism of the present application;

[0027] Figure 2 It is a counterbore assembly schematic view of the scissor type solar wing unfolding device based on the planar four-bar mechanism of the present application;

[0028] Figure 3 It is a rotating pair assembly schematic view of the scissor type solar wing unfolding device based on the planar four-bar mechanism of the present application;

[0029] Figure 4 It is a counterbore assembly and rod body schematic view of the scissor type solar wing unfolding device based on the planar four-bar mechanism of the present application;

[0030] Figure 5 It is a guide assembly schematic view of the scissor type solar wing unfolding device based on the planar four-bar mechanism of the present application;

[0031] Figure 6 The unfolding process schematic diagram of the scissor type solar wing unfolding device based on the planar four-bar mechanism of the present application;

[0032] Figure 7 The unfolding base assembly schematic diagram of the scissor type solar wing unfolding device based on the planar four-bar mechanism of the present application;

[0033] Figure 8 The positioning assembly schematic diagram of the scissor type solar wing unfolding device based on the planar four-bar mechanism of the present application;

[0034] Figure 9 The fully unfolded schematic diagram of the scissor type solar wing unfolding device based on the planar four-bar mechanism of the present application.

[0035] In the figure: 100, unfolding base assembly; 110, bottom plate; 120, slope plate; 130, motor base; 140, motor; 150, motor rod; 160, horizontal rod one; 170, carbon fiber scissor rod; 180, flexible solar wing film; 190, constant force spring; 200, countersunk assembly; 210, countersinker; 220, pin shaft hole; 221, pin shaft; 222, L-shaped shaft sleeve; 223, end cover; 224, fastening screw; 230, conical countersunk hole; 240, square hole; 250, empty slot; 260, threaded hole; 300, guide assembly; 310, horizontal plate; 311, horizontal plate hole; 312, triangular plate one; 320, bracket; 330, ear plate; 331, winding wheel; 340, plate cover; 341, triangular plate two; 342, torsion spring rod; 343, torsion spring; 350, pressing 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 rod two; 600, top plate; 610, horizontal frame; 620, T-shaped combined buckle; 630, vertical frame; 640, cross-shaped combined buckle. DETAILED DESCRIPTION

[0036] In the description of the present application, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, which is only for the convenience of describing the present application and simplifying the description, and does not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.

[0037] In the description of the present application, the meaning of "a plurality of" is two or more, unless otherwise explicitly specified and limited.

[0038] In the description of the present application, it should be noted that, unless otherwise explicitly specified and limited, the terms "mounting", "provided with", "sleeved / connected", "connected" and the like should be understood broadly, for example, "connected" can be fixedly connected, or can be detachably connected, or integrally connected; can be mechanically connected, or can be electrically connected; can be directly connected, or can be indirectly connected through an intermediate medium, or can be connected inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0039] The application provides a scissor type solar wing unfolding device based on a planar four-bar mechanism, which is composed of a rigid unfolding mechanism and a flexible solar wing film, the main body of the rigid unfolding mechanism is composed of multiple pairs of scissor levers, the root is connected with a bottom frame, and the top is connected with a top frame; meanwhile, the top frame is also connected with a top plate, and the bottom frame is also connected with a bottom plate, the two plates are used for pressing and protecting the solar wing in the folded state when the mechanism is folded; when unfolded, the multiple pairs of scissor levers are opened synchronously, the top frame is driven to move away from the bottom frame, so that the solar wing is pulled to open from the folded state, and after being completely unfolded, the flexible solar wing film is provided with support and tensioning, the lever is in the form of a carbon fiber hollow lever and an aluminum alloy connecting piece, and the carbon fiber lever has an outer square and inner circle cross section; compared with a concentric circle cross section, the bending section modulus is higher, the strength and rigidity are better, and positioning and assembly are more convenient; compared with a hollow rectangular cross section, the four-corner stress concentration problem does not exist, the overall quality is light, and the stability is high; meanwhile, a wear-resistant and self-lubricating L-shaped Teflon sleeve is arranged between the pin shaft and the lever; the positioning in the axial direction is in the form of an end cover and a locking screw, assembly is facilitated, the gap between rotating pairs is reduced as much as possible, friction is also reduced, a complete positioning design for pressing is added to the connecting pieces at the two ends of the scissor lever, 2 V-shaped grooves are formed on the upper surface of each connecting piece, and a spherical surface is formed on the corresponding position of the lower surface; when the scissor mechanism part is subjected to the pressing force, the adjacent scissor levers are in contact with each other, complete positioning between each adjacent connecting piece is ensured, and the impact load bearing capacity of the whole mechanism is greatly improved under the action of the pressing force; the guiding assembly is provided, one end of the guiding rope is wound on the wire wheel at the bottom, and the other end is fixed on the top frame; during the unfolding process, the wire wheel rotates continuously, the guiding rope is gradually lengthened, small holes are punched at the corresponding positions of each solar wing, the guiding rope passes through the small holes, so that the folding state of the solar wing is maintained, the guiding rope maintains a certain tightness and rigidity during the whole mechanism unfolding process, the function of supporting the flexible solar wing is realized, the system has a higher fundamental frequency when the flexible solar wing adopts a four-point tensioning mode, so the solar wing is tensioned in the four-point tensioning mode, that is, the tensioning force is applied to the four corners of the flexible film, and the rotation can be passively adapted to the transverse displacement of the upper and lower plates, and the stability and reliability are improved, please refer to Figures 1-9 , which comprises an unfolding base assembly 100, a countersunk head assembly 200, a guiding assembly 300, a positioning assembly 400, a connecting assembly 500 and a top plate 600 arranged on the side wall of the connecting assembly 500;

[0040] The unfolding base assembly 100 comprises a bottom plate 110, a slope plate 120 integrally formed on the top of the bottom plate 110, a motor seat 130 arranged on the top of the slope plate 120, a motor 140 arranged on the top of the motor seat 130, and a motor rod 150 connected with the countersunk head assembly 200 arranged on the output end of the motor 140;

[0041] The other end of the sunk head assembly 200 is provided with a horizontal rod one 160, the side wall of the sunk head assembly 200 is hinged with a plurality of groups of vertical intersecting carbon fiber scissors levers 170, the unfolding process is driven by the rotation of the motor rod 150 driven by the motor 140, then 3 pairs of carbon fiber scissors levers 170 are opened upward, the horizontal rod two 530 is pushed to move upward, and finally the folded solar wing is unfolded, the horizontal rod one 160 and the horizontal rod two 530 are connected with the near end and the far end of the flexible solar wing film 180 respectively, supporting the solar wing after unfolding and providing tension, the horizontal rod one 160 is provided with a constant force spring 190 at both ends, and the flexible solar wing film 180 is arranged on the top of the horizontal rod one 160, and the flexible solar wing film 180 is folded in the form of an accordion, which is similar to the folding mode of the traditional rigid solar wing base plate;

[0042] The connection between the horizontal rod one 160 and the horizontal rod two 530 and the bottom frame is separated, and the horizontal rod one 160 and the horizontal rod two 530 are driven through the crank rocker mechanism, which can keep approximately symmetrical movement during the unfolding process. Such a design can improve the reliability of the mechanism and increase the stiffness in the left and right directions. At the same time, the same four-bar mechanism is configured at the connection between the top plate 600 and the carbon fiber scissors lever 170, so that the top plate 600 and the bottom frame always remain parallel during the unfolding process;

[0043] In some embodiments, the specific four-bar mechanism parameters 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 satisfy that when the horizontal rod one 160 and the rack angle is 0°, the horizontal rod one 160 and the horizontal rod two 530 remain horizontal; when the angle is 90°, the horizontal rod one 160 and the horizontal rod two 530 are perpendicular to the rack. Written in the form of equation is

[0044]

[0045] If l0 is too long, the weight of the four-bar mechanism will also be high, and if it is too short, the stiffness in the left and right directions will not be obvious. Considering that the short side of the solar wing is 3m, l0=600mm is taken, and the lengths of the remaining 3 rods are calculated according to formula (0-1):

[0046]

[0047] At the same time, according to the requirement that the length of the solar wing is greater than 6m, 3 pairs of carbon fiber scissors levers 170 are taken, and the length of the carbon fiber scissors lever 170 is calculated as l s =1.8m. Then the length of the entire mechanism after unfolding is

[0048]

[0049] Satisfies the requirement;

[0050] The guide assembly 300 comprises a horizontal plate 310 arranged on the side wall of the slope plate 120, and a plurality of small holes are formed in the horizontal plate 310, so as to facilitate the guide rope to enter;

[0051] The positioning assembly 400 comprises a connecting block 410 arranged on the side wall of the sunken head assembly 200, and the connecting block 410 is arranged to facilitate positioning cooperation, so as to form a V-shaped groove 411 and a spherical surface 412 structure;

[0052] The connecting assembly 500 comprises a connecting buckle 510 arranged on the top of the carbon fiber scissor rod 170, a plurality of connecting plates 520 are arranged on the top of the connecting buckle 510, and a horizontal rod two 530 is buckled and connected to the side wall of the connecting plate 520;

[0053] The top plate 600 comprises a horizontal frame 610 arranged on the side wall of the horizontal rod two 530, and a T-shaped combined buckle 620 is arranged on the horizontal frame 610, the vertical frame 630 is combined by using the T-shaped combined buckle 620, when the horizontal frame 610 and the vertical frame 630 are intertwined, the horizontal frame 610 and the vertical frame 630 are combined by using a cross-shaped combined buckle 640, so that the horizontal frame 610 and the vertical frame 630 form a net structure;

[0054] In some embodiments, when the solar wing is not unfolded, the whole mechanism and the flexible solar wing film 180 are packaged in the fairing of the launch rocket, and in the process of transportation and launching, the environment is relatively harsh, and the flexible solar wing film 180 will be subjected to irregular impact load, vibration and temperature change and other adverse effects. In order to prevent the flexible solar wing film 180 from being damaged before unfolding, it is necessary to compress and protect before unfolding, and a rigid frame and a foam substrate are adopted, wherein the rigid frame is a grid, which is also composed of carbon fiber rods and aluminum connectors. The aluminum connectors are nodes of the grid, and the carbon fiber rods are edges of the grid. The frame and the hard polyimide foam are glued, and the two layers of foam directly contact the flexible solar wing film 180, which plays a protective role;

[0055] A through hole is punched at each aluminum connector, i.e. node of the frame, to facilitate connection between upper and lower plates. A commercial locker is used, and the specific model is FLLM-2C double-layer compression locker of Micro Division Spaceflight. The locker is installed between the upper and lower plates of the four corners and the two center nodes, and the upper and lower plates and the flexible solar wing in the folded state are completely compressed. When release is needed, the memory alloy puller in the locker is unlocked by power supply, and the spring pushes away, so as to realize low-impact unlocking;

[0056] In addition, the conventional fittings and the conventional structures involved in the present application are prior art, and those skilled in the art can realize them without further description, and the content protected by the present application does not involve improvement of internal structure and method;

[0057] Working principle: in the specific use, first set the inclined plate 120 on the bottom plate 110 of the unfolded base assembly 100, facilitate the installation of the motor seat 130 carrying the motor 40, the motor 140 is connected with the motor rod 150, in the drive will cooperate with the carbon fiber scissors fork rod 170 on the cross rod one 160 to unfold, in the unfolding process of multiple carbon fiber scissors fork rods 170 will carry the flexible solar wing film 180 to open, at the same time, the sunken head assembly 200 is connected with the carbon fiber scissors fork rod 170, and the L-shaped shaft sleeve 222 with wear resistance and self-lubricating property is added between the pin shaft 221 and the rod, and the material can be Teflon; the upward positioning of the pin shaft 221 adopts the form of end cover 223 and locking screw 224, which is convenient for assembly, and a guide assembly 300 is also provided, which includes a guide rope wound on a winding wheel 331, which can rotate freely around the shaft. Another shaft parallel to it, and a torsional spring 343 is installed on the shaft, which provides a torque that tends to tighten inward, so that the compression plate 350 compresses the winding wheel 331. Therefore, when the guide rope is pulled upward, it will be subjected to the friction force of the compression plate 350, so that the guide rope maintains a certain tightness and rigidity during the unfolding of the entire mechanism, supporting the flexible solar wing, and the connecting block 410 is also provided at the end of the carbon fiber scissors fork rod 170, 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, which can be positioned with each other, and the top plate 600 has a horizontal frame 610 carrying a T-shaped combined buckle 620 and a vertical frame 630 carrying a cross-shaped combined buckle 640, which can be spliced to form a net-like structure.

[0058] At the same time, in order to position and lock the carbon fiber scissors fork rod 170 and the aluminum connecting piece on the sunken head assembly 200, two threaded holes 260 are drilled at the corresponding positions, and two conical countersunk holes 230 are drilled on the upper surface, so that only two countersunk screws are needed to completely position and lock the carbon fiber scissors fork rod 170 and the aluminum connecting piece, without the need for screws and nuts to lock, which can save the weight of two nuts. Specifically, the sunken head assembly 200 includes a sunken head device 210, a pin shaft hole 220 provided on the side wall of the sunken head device 210, a conical countersunk hole 230 and a square hole 240 provided on the top of the sunken head device 210, and an air slot 250 provided on the side wall of the sunken head device 210. The inner cavity of the air slot 250 is provided with a threaded hole 260 at the bottom, which can ensure the stability of the mechanism, and the strength, rigidity and stability of each rod need to be ensured.

[0059] Subsequently, in order to make the actual mechanism motion completely consistent with the theory, it is necessary to minimize the clearance between the rotating pairs, and also to reduce the friction. In the planar linkage mechanism, the design of the rotating pair is also important. Specifically, the circumferential inner wall of the plurality of pin shaft holes 220 is penetrated by the pin shaft 221, the circumferential outer wall of the pin shaft 221 is sleeved with the L-shaped shaft sleeve 222, the side wall of the pin shaft 221 is buckled with the end cover 223, and the side wall of the end cover 223 is penetrated by the fastening screw 224.

[0060] Next, in order to wrap the guide rope on the wire reel, the wire reel can rotate freely around the shaft. Another shaft parallel to it is installed with a rotatable compression plate 350, and a torsion spring 343 is installed on the torsion spring rod 342, providing a torque that tends to tighten inward, so that the compression plate 350 compresses the wire reel. Therefore, when the guide rope is pulled upward, it will be subjected to the friction of the compression plate 350, so that the guide rope maintains a certain tightness and rigidity during the entire mechanism deployment process, playing a role in supporting the flexible solar wing. Specifically, the top of the horizontal plate 310 is provided with a horizontal plate hole 311, the bottom of the horizontal plate 310 is integrally connected with a triangular plate one 312 and a bracket 320, the bottom of the bracket 320 is oppositely provided with an ear plate 330, the sidewall of the ear plate 330 is penetrated by a wire reel 331, and the wire reel 331 is penetrated by a plate cover 340.

[0061] Further, in order to enable the compression plate 350 to cooperate with the torsion spring 343 to generate a rebound force, specifically, the top of the plate cover 340 is oppositely provided with a triangular plate two 341, the sidewall of the plurality of triangular plate two 341 is provided with a torsion spring rod 342, 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 compression plate 350 abutting against the sidewall of the plate cover 340.

[0062] Next, in order to add a complete positioning design for compression on the positioning assembly 400 at both ends of the carbon fiber scissors lever 170, specifically, the top of the connecting block 410 is integrally formed with a V-shaped groove 411, the bottom of the connecting block 410 is integrally formed with a spherical surface 412 matching the position and size of the V-shaped groove 411. Without a special positioning design, they are in plane contact, which is easy to tilt and become point contact, which will cause the scissors mechanism part to be not completely positioned in the undeployed state, and is easy to shake and even fail under impact load environment.

[0063] In some embodiments, after the solar wing is deployed and tensioned, the entire mechanism needs to be locked and cannot be displaced or shaken. A locking mechanism can be provided, which is locked when the horizontal angle of the rod body reaches 90°. The form of spring plus round head slider cooperating with locking groove is adopted. During the rotation of the rod body, the round head slider gradually approaches the locking groove along the inclined surface under the action of the spring; when reaching the limit position, the round head slider enters the groove, and the mechanism is locked. At this time, the mechanism theoretically will not have any displacement, and the degree of shaking depends on the cooperation tolerance of the slider and the groove. This part of the structure is prior art, and a commonly used locking mechanism on the market can be directly selected.

[0064] Subsequently, in order to facilitate the mutual combination of the horizontal frame 610 and the vertical frame 630, specifically, the horizontal 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 the vertical frame 630, and the ends of the plurality of vertical frames 630 are sleeved with cross-shaped combination buckles 640.

[0065] Notably, because the flexible solar wing film 180 is Z-shaped folded before and during unfolding, in order to prevent the folding of the flexible solar wing film 180 from being disturbed during unfolding, it needs to be constrained, and two guide ropes are arranged, specifically, the bottom of the horizontal rod two 530 is provided with a line wheel corresponding to the guide assembly 300, and the guide assembly 300 and the line wheel are wound with a guide rope.

[0066] Subsequently, in order to enable the flexible solar wing film 180 to adapt to the carbon fiber scissor rod 170 after unfolding, specifically, the flexible solar wing film 180 is folded in the form of an accordion for storage, and the length of the flexible solar wing film 180 is consistent with the unfolding height of the plurality of carbon fiber scissor rods 170.

[0067] Finally, because the flexible solar wing adopts 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. The system has a higher fundamental frequency when the flexible solar wing adopts a four-point tensioning mode, so the four-point tensioning mode is adopted to tension the solar wing, that is, a tensioning force is applied to the four corners of the flexible film. Specifically, the two sides of the horizontal rod one 160 and the horizontal rod two 530 are provided with rotatable constant force springs 190, and the four constant force springs 190 are respectively connected to the four corner positions of the flexible solar wing film 180. The flexible solar wing film 180 of similar size has the highest fundamental frequency of the system under the four-point tensioning working condition when the tensioning force is 16-18 N. A constant force spring with a load of 1.8 kgf, i.e. 17.64 N, is selected. In this way, the tensioning force on the flexible solar wing film 180 can always remain constant after the mechanism is unfolded, improving stability and reliability. At the same time, due to the influence of the four-bar mechanism, there is a lateral displacement of the system during unfolding. A constant force spring tensioning assembly that can rotate around the axis shown in the figure is designed, and its rotation can passively adapt to the lateral displacement of the upper and lower plates during unfolding.

[0068] Although the present application has been described with reference to the embodiments above, various changes and modifications can be suggested to one skilled in the art, and it is intended that the present application encompass such changes and modifications as fall within the scope of the appended claims. Particularly, each feature of the disclosed embodiments can be used in combination with any other feature, unless the context contradicts otherwise. The description herein of any feature or embodiment in connection with its description of related art does not constitute a recognition that such feature is part of the state of the art or a common general knowledge of persons skilled in the art. Furthermore, the description herein of any feature or embodiment in connection with its description of related art does not constitute an admission that such feature or embodiment is prior art to the present application, or part of the common general knowledge of the skilled person in the art. The disclosure of a single feature or embodiment in this specification does not constitute an admission that such feature or embodiment is part of the related art or part of the common general knowledge of the skilled person in the art.

Claims

1. A planar four-bar mechanism based deployment device for a scissor-type solar wing, characterized in that: The utility model relates to a kind of deployable base assemblies, including deployable base assembly (100), countersunk head assembly (200), guide assembly (300), positioning assembly (400), connecting assembly (500) and top plate (600) arranged in the side wall of the connecting assembly (500); Wherein: Deployable base assembly (100), the deployable base assembly (100) includes bottom plate (110), integrally formed and connected to the inclined plate (120) on the top of the bottom plate (110), motor base (130) is arranged on the top of the inclined plate (120), the top of the motor base (130) is provided with motor (140), the output end of the motor (140) is provided with motor rod (150) connected with the countersunk head assembly (200); Countersunk head assembly (200), the other end of the countersunk head assembly (200) is provided with crossbar one (160), the side wall of the countersunk head assembly (200) is hinged with multiple groups of carbon fiber scissors fork rod (170) in vertical intersection type, the two ends of the crossbar one (160) are provided with constant force spring (190), the top of the crossbar one (160) is provided with flexible solar wing film (180); Guide assembly (300), the guide assembly (300) includes cross plate (310) arranged on the side wall of the inclined plate (120), the top of the cross plate (310) is reserved with cross plate hole (311), the bottom of the cross plate (310) is integrally connected with triangular plate one (312) and bracket (320), the bottom of the bracket (320) is oppositely provided with lug plate (330), the side wall of the lug plate (330) is penetrated with winding wheel (331), the winding wheel (331) is penetrated with plate cover (340), the top of the plate cover (340) is oppositely provided with triangular plate two (341), the side wall of multiple triangular plate two (341) is provided with torsion spring rod (342), the circumferential outer wall of the torsion spring rod (342) is sleeved with torsion spring (343), one end of the torsion spring (343) is provided with compression plate (350) that is attached to the side wall of the plate cover (340); Positioning assembly (400), the positioning assembly (400) includes connecting block (410) arranged on the side wall of the countersunk head assembly (200), the top of the connecting block (410) is integrally reserved with V-shaped groove (411), the bottom of the connecting block (410) is integrally reserved with spherical surface (412) that is matched with the position and size of the V-shaped groove (411); Connecting assembly (500), the connecting assembly (500) includes connecting buckle (510) arranged on the top of the carbon fiber scissors fork rod (170), the top of the connecting buckle (510) is provided with multiple connecting plates (520), the side wall of the connecting plate (520) is buckled and connected with crossbar two (530); Top plate (600), the top plate (600) includes transverse frame (610) arranged on the side wall of the crossbar two (530).

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

3. A planar four-bar mechanism based deployment device for a scissor wing according to claim 2, characterized in that: 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 shaft sleeve (222), the side wall of the pin shaft (221) is buckled with an end cover (223), and the side wall of the end cover (223) is penetrated by a fastening screw (224).

4. The planar four-bar mechanism based deployment device of the scissor wing according to claim 3, characterized in that: The transverse frame (610) comprises T-shaped combined buckles (620) arranged at equal intervals, the side wall of the plurality of T-shaped combined buckles (620) is provided with vertical frames (630), and the ends of the plurality of vertical frames (630) are sleeved with cross-shaped combined buckles (640).

5. The planar four-bar mechanism based, forked solar wing deployment apparatus according to claim 4, characterized in that: The bottom of the crossbar two (530) is provided with a line wheel corresponding to the guide assembly (300), and a guide rope is wound between the guide assembly (300) and the line wheel.

6. A planar four-bar mechanism based deployment device for a scissor-wing solar wing according to claim 5, characterized in that: The flexible solar wing film (180) is folded in an accordion form for storage, and the length of the flexible solar wing film (180) is consistent with the unfolding height of the plurality of groups of carbon fiber scissors levers (170).

7. A planar four-bar mechanism based deployment device for a scissor-wing solar wing according to claim 6, characterized in that: Both sides of the crossbar one (160) and the crossbar two (530) are provided with rotatable constant force springs (190), and four constant force springs (190) are respectively connected with four corner positions of the flexible solar wing film (180).

Images