Solar wing synchronous deployment structure

Abstract

The present application relates to the field of space folding and unfolding mechanism, and in particular to a solar wing synchronous unfolding structure. The solar wing synchronous unfolding structure comprises a first synchronous wheel, a second synchronous wheel, a first hinge, a second hinge and a connecting rope. The first hinge is used to connect an inner panel and a spacecraft body, and the second hinge is used to connect the inner panel and an outer panel. The first synchronous wheel is coaxially arranged with the first hinge and can drive the inner panel to rotate around the first hinge. The second synchronous wheel is coaxially arranged with the second hinge and can drive the outer panel to rotate around the second hinge. The first synchronous wheel and the second synchronous wheel are connected by the connecting rope. The overall structure of the present application is simple in form, light in weight and reliable in unfolding. Compared with the traditional synchronous unfolding mechanism, the synchronous unfolding mechanism of the present application can be placed on the inner side of the panel or on the outer side of the panel, and is more flexible to use.

Description

Technical Field

[0001] This invention relates to the field of aerospace deployment mechanisms, and more specifically, to a solar array synchronous deployment structure. Background Technology

[0002] Solar panels, an indispensable part of spacecraft, primarily provide power. Due to their large size, they are folded before launch and unfold after the spacecraft enters orbit. Most current spacecraft have two or more solar panels on one side, requiring that the solar panels not interfere with other components during deployment. Summary of the Invention

[0003] The purpose of this invention is to provide a solar array synchronous deployment structure that is more flexible in use and allows the solar array to deploy without interfering with other devices.

[0004] The embodiments of the present invention are implemented as follows:

[0005] A solar array synchronous deployment structure includes a first synchronous pulley, a second synchronous pulley, a first hinge, a second hinge, and a connecting rope;

[0006] The first hinge is used to connect the inner solar panel and the spacecraft body, and the second hinge is used to connect the inner solar panel and the outer solar panel;

[0007] The first synchronous pulley is coaxially arranged with the first hinge, which can drive the inner sail to rotate around the first hinge;

[0008] The second synchronous pulley is coaxially arranged with the second hinge, and can drive the outer sail to rotate around the second hinge;

[0009] The first synchronous pulley and the second synchronous pulley are connected by the connecting rope.

[0010] Furthermore, the first synchronous pulley includes a first pulley body, a main shaft, a preload member, a line stop plate, and a first pressure plate;

[0011] The pretensioner is disposed inside the first wheel body, and the connecting rope is connected to the pretensioner;

[0012] The line stop plate is disposed at the end of the wheel body to prevent the connecting rope from detaching from the pretensioner;

[0013] The main shaft passes through the first wheel body and is connected to the preload member;

[0014] A notch is provided on the side wall of the first wheel body, and the connecting rope is set on the pretensioner through the notch;

[0015] The first pressure plate is disposed on the outer wall of the wheel body and is used to press the connecting rope wrapped around the outer wall of the first wheel body onto the first wheel body.

[0016] Furthermore, the first wheel body includes a hub, a rim, a mounting plate, and a connecting rib;

[0017] The rim is disposed at opposite ends of the hub, so that the outer wall of the hub forms a limiting groove that can limit the position of the connecting rope.

[0018] The mounting plate is disposed on the inner side of the wheel body and is coaxially disposed with the wheel hub. The mounting plate is connected to the inner wall of the wheel hub through the connecting rib.

[0019] The mounting plate is provided with a first mounting hole and a second mounting hole.

[0020] Furthermore, the pretensioning component includes a pretensioning disc, gear teeth, a first positioning part, and a second positioning part;

[0021] Both the first positioning part and the second positioning part are disposed on one side of the pre-tightening plate, and there is a set gap between the first positioning part and the second positioning part;

[0022] The gear teeth are disposed on the outer edge of the other side of the preload disc;

[0023] The pre-tightening plate is provided with a third mounting hole.

[0024] Furthermore, a boss is provided on the second positioning part.

[0025] Furthermore, the first pressure plate is provided with a fourth mounting hole, and the first wheel body is provided with a threaded hole corresponding to the fourth mounting hole.

[0026] Furthermore, the second synchronous pulley includes a second pulley body, an end plate, and a second pressure plate;

[0027] The end plate is disposed at one end of the second wheel body and is used to seal one end of the second wheel body;

[0028] The end plate is provided with a fifth mounting hole;

[0029] The second pressure plate is disposed on the outer wall of the second wheel body and is used to fix the connecting rope to the second wheel body.

[0030] Furthermore, the synchronous deployment structure of the solar array also includes a guide member for guiding the connecting rope.

[0031] Furthermore, the guide component includes a mounting base, a guide plate, and a guide shaft;

[0032] The guide plate is disposed on the mounting base, and a guide groove is formed between multiple guide plates;

[0033] The guide shaft is disposed through the guide plate.

[0034] Furthermore, the connecting rope is a Kevlar rope.

[0035] The beneficial effects of the embodiments of the present invention are:

[0036] In the synchronous deployment mechanism, the first synchronous wheel and the first hinge are coaxial, and the second synchronous wheel and the second hinge are coaxial. The first synchronous wheel and the second synchronous wheel are linked by a pull rope, which can realize the synchronous deployment of the inner and outer solar panels.

[0037] The overall structure is simple, lightweight, and reliable in deployment. Compared with traditional synchronous deployment mechanisms, the synchronous deployment mechanism of this invention can be placed on either the inside or outside of the sailboard, making it more flexible in use. Attached Figure Description

[0038] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of the present invention and should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0039] Figure 1 This is a schematic diagram of the synchronous deployment structure of the solar array provided in an embodiment of the present invention;

[0040] Figure 2 An exploded view of the first synchronous wheel of the solar array synchronous deployment structure provided in an embodiment of the present invention;

[0041] Figure 3 This is a front view of the first synchronous wheel of the solar array synchronous deployment structure provided in an embodiment of the present invention;

[0042] Figure 4 for Figure 3 AA section view;

[0043] Figure 5 A perspective view of the first wheel of the synchronous deployment structure of the solar array provided in an embodiment of the present invention;

[0044] Figure 6 A three-dimensional structural diagram of the preload of the solar array synchronous deployment structure provided in an embodiment of the present invention;

[0045] Figure 7 A three-dimensional structural schematic diagram of the pretensioner of the solar array synchronous deployment structure provided in an embodiment of the present invention from another perspective;

[0046] Figure 8 A three-dimensional structural diagram of the second synchronous wheel of the solar array synchronous deployment structure provided in an embodiment of the present invention;

[0047] Figure 9 A three-dimensional structural diagram of the guide component for the synchronous deployment structure of the solar array provided in an embodiment of the present invention;

[0048] Figure 10 This is a schematic diagram of the initial state of the synchronous deployment structure of the solar array provided in an embodiment of the present invention;

[0049] Figure 11 A first schematic diagram of the intermediate state of the synchronous deployment structure of the solar array provided in an embodiment of the present invention;

[0050] Figure 12 A second schematic diagram of the intermediate state of the synchronous deployment structure of the solar array provided in an embodiment of the present invention;

[0051] Figure 13 This is a schematic diagram of the deployed state of the solar array synchronous deployment structure provided in an embodiment of the present invention.

[0052] Icons: 1-First synchronizer pulley; 2-First hinge; 3-Guide component; 4-Pull rope; 5-Inner sail; 6-Outer sail; 7-Second synchronizer pulley; 8-Second hinge; 9-First wheel body; 10-Main shaft; 11-First pressure plate; 12-Pretensioner component; 13-Line baffle; 14-Screw; 15-Hub; 16-Mounting plate; 17-Connecting rib; 18-First mounting hole; 19-Second mounting hole; 20-Wheel rim; 21-Notch; 22-Pretensioner plate; 23-Wheel tooth; 24-First positioning part; 25-Second positioning part; 26-Boss; 27-Threaded hole; 28-Third mounting hole; 29-Second wheel body; 30-End plate; 31-Second pressure plate; 32-Fifth mounting hole; 33-Mounting seat; 34-Guide plate; 35-Guide shaft. Detailed Implementation

[0053] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The components of the embodiments of the present invention described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0054] Therefore, the following detailed description of the embodiments of the invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the invention without inventive effort are within the scope of protection of the invention.

[0055] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0056] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product of this invention is in use. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention. In addition, the terms "first," "second," "third," etc., are only used to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0057] Furthermore, terms such as "horizontal," "vertical," and "sag" do not imply that components must be absolutely horizontal or suspended, but rather that they can be slightly tilted. For example, "horizontal" simply means that its direction is more horizontal relative to "vertical," and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0058] In the description of this invention, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0059] The following is combined with Figures 1 to 13 The following describes some embodiments of the present invention in detail. Unless otherwise specified, the following embodiments and features can be combined with each other.

[0060] A synchronous deployment structure for a solar array includes a first synchronous pulley 1, a second synchronous pulley 7, a first hinge 2, a second hinge 8, and a connecting rope. The first hinge 2 connects the inner solar panel 5 to the spacecraft body, and the second hinge connects the inner solar panel 5 to the outer solar panel 6. The first synchronous pulley 1 is coaxially arranged with the first hinge 2 and can drive the inner solar panel 5 to rotate around the first hinge 2. The second synchronous pulley 7 is coaxially arranged with the second hinge 8 and can drive the outer solar panel 6 to rotate around the second hinge 8. The first synchronous pulley 1 and the second synchronous pulley 7 are connected by a connecting rope.

[0061] In this embodiment, the first synchronous wheel 1 and the first hinge 2 are coaxially connected, enabling the first synchronous wheel 1 to drive the first hinge 2 to rotate. The second synchronous wheel 7 and the second hinge 8 are coaxially connected, enabling the second hinge 8 to rotate through the rotation of the second synchronous wheel 7. The first synchronous wheel 1 and the second synchronous wheel 7 are connected by a pull rope 4, so that the first synchronous wheel 1 and the second synchronous wheel 7 can rotate synchronously, thereby achieving the purpose of driving the inner solar panel 5 or the outer solar panel 6 of the solar wing to deploy and retract.

[0062] Specifically, in this embodiment, the two protruding ends of the first hinge 2 are respectively connected to one end of the inner solar panel 5 and the spacecraft body, so that the inner solar panel 5 can rotate on the spacecraft body with the hinge center of the first hinge 2 as the axis; the two protruding ends of the second hinge 8 are respectively connected to the other end of the inner solar panel 5 and one end of the outer solar panel 6. When the first synchronous wheel 1 drives the pull rope 4 to rotate, and then drives the second synchronous wheel 7 to rotate, the second synchronous wheel 7 can drive the second hinge 8 to rotate, thereby driving the inner solar panel 5 and the outer solar panel 6 to rotate relative to each other with the rotation center of the second hinge 8 as the axis, further achieving the purpose of deploying or retracting the inner solar panel 5 and the outer solar panel 6.

[0063] Furthermore, the first synchronous pulley 1 includes a first pulley body 9, a main shaft 10, a pretensioner 12, a line stop plate 13, and a first pressure plate 11; the pretensioner 12 is disposed inside the first pulley body 9, and the connecting rope is connected to the pretensioner 12; the line stop plate 13 is disposed at the end of the pulley body to prevent the connecting rope from detaching from the pretensioner 12; the main shaft 10 passes through the first pulley body 9 and is connected to the pretensioner 12; a notch 21 is provided on the side wall of the first pulley body 9, and the connecting rope is disposed on the pretensioner 12 through the notch 21; the first pressure plate 11 is disposed on the outer wall of the pulley body to press the connecting rope wrapped around the outer wall of the first pulley body 9 tightly onto the first pulley body 9.

[0064] Specifically, in this embodiment, the first wheel body 9, the main shaft 10, the pretensioner 12 and the baffle plate 13 are coaxially installed, and the first pressure plate 11 is installed on the outer wall of the first wheel body 9.

[0065] A notch 21 is provided on the side wall of the first wheel body 9. The connecting rope enters and exits the inside and outside of the first wheel body 9 through the notch 21. The connecting rope inside the first wheel body 9 is connected to the pretensioner 12. The connecting rope outside the first wheel body 9 is wound around the first wheel body 9 and connected to the second synchronous wheel 7. The first pressure plate 11 presses the connecting rope on the outer wall of the first wheel body 9 to prevent the connecting rope from slipping.

[0066] In this embodiment, the rotation of the pretensioner 12 can achieve tensioning of the connecting rope. The line stop plate 13 is installed on the pretensioner 12 by screws 14 to prevent the connecting rope on the pretensioner 12 from detaching axially.

[0067] In this embodiment, the main shaft 10 passes through the first wheel body 9 and is connected to the pre-tightening member 12. One end of the main shaft 10 is connected to the first wheel body 9 by a screw 14, and the other end of the main shaft 10 passes through the pre-tightening member 12 and is connected to the end of the pre-tightening member 12 near the baffle plate 13 by a screw 14, thereby achieving axial and radial positioning of the main shaft 10.

[0068] Furthermore, the first wheel body 9 includes a hub 15, a rim 20, a mounting plate 16, and a connecting rib 17; the rim 20 is disposed at opposite ends of the hub 15, so that the outer wall of the hub 15 forms a limiting groove that can limit the connecting rope; the mounting plate 16 is disposed on the inner side of the wheel body and is coaxially disposed with the hub 15, and the mounting plate 16 is connected to the inner wall of the hub 15 through the connecting rib 17; the mounting plate 16 is provided with a first mounting hole 18 and a second mounting hole 19.

[0069] Specifically, in this embodiment, the rim 20 is provided at both ends on the outer side of the hub 15, and a limiting groove is formed on the outer wall of the hub 15. When the connecting rope is arranged around the hub 15, the connecting rope can be limited by the limiting groove to prevent the connecting rope from detaching from the hub 15.

[0070] In this embodiment, the hub 15 and the mounting plate 16 are coaxially arranged, and the mounting plate 16 is located on the inner ring of the hub 15. The hub 15 is connected to the mounting plate 16 through the connecting rib 17. Specifically, in this embodiment, the connecting rib 17 is located at one end of the hub 15.

[0071] In this embodiment, the mounting plate 16 is provided with a first mounting hole 18 and a second mounting hole 19. The first mounting hole 18 is used for the spindle 10 to pass through, so that one end of the spindle 10 can be inserted into the mounting plate 16 and connected with the pre-tightening member 12 and the wire baffle 13. The second mounting hole 19 is used to cooperate with the screw 14 to fix the spindle 10.

[0072] Furthermore, the pretensioning member 12 includes a pretensioning disc 22, a gear tooth 23, a first positioning part 24, and a second positioning part 25; the first positioning part 24 and the second positioning part 25 are both disposed on one side of the pretensioning disc 22, and there is a set gap between the first positioning part 24 and the second positioning part 25; the gear tooth 23 is disposed on the outer edge of the other side of the pretensioning disc 22; a third mounting hole 28 is provided on the pretensioning disc 22.

[0073] Specifically, in this embodiment, a tooth 23 is provided on one side of the pre-tightening disc 22. The teeth of the tooth 23 cooperate with the connecting rib 17 to achieve circumferential positioning of the pre-tightening disc 22. A first positioning part 24 and a second positioning part 25 are provided on the other side of the pre-tightening disc 22. The outer contours of the first positioning part 24 and the second positioning part 25 can jointly form a circle. There is a set gap between the first positioning part 24 and the second positioning part 25. This set gap allows the connecting rope to pass through. That is, when the connecting rope is wound on the pre-tightening member 12, it is completely sleeved on the first positioning part 24 and the second positioning part 25, and then passes back through the set gap, thereby achieving positioning between the pre-tightening member 12 and the connecting rope and preventing the connecting rope from slipping when the pre-tightening member 12 rotates.

[0074] In this embodiment, a third mounting hole 28 is provided on the pre-tightening plate 22, which is corresponding to the first mounting hole 18, and is used to allow the spindle 10 to pass through.

[0075] The pretensioner 12 is the pretensioning device for the first synchronous pulley 1. The connecting rope is looped in the set gap of the pretensioner 12. When the pretensioner 12 rotates in the same direction, the connecting rope can be wound around the first positioning part 24 and the second positioning part 25. The gear teeth 23 of the pretensioner 12 are used to cooperate with the connecting rib 17. After the pretensioner 12 rotates a certain angle, the gear teeth 23 cooperate with the connecting rib 17 and restrict the reverse rotation of the pretensioner 12, thereby achieving the purpose of rope pretensioning. The end faces of the first positioning part 24 and the second positioning part 25 are both reserved with threaded holes 27 for the installation of the wire stop plate 13.

[0076] Furthermore, a boss 26 is provided on the second positioning part 25.

[0077] The protruding boss 26 on the second positioning part 25 is used to clamp the tool and tension the connecting rope.

[0078] In this embodiment, the boss 26 is shaped as a direction, and after passing through the square hole on the wire baffle 13, it extends out of the wire baffle 13.

[0079] Meanwhile, the boss 26 is provided with a hole that communicates with the third mounting hole 28, so that the screw 14 can pass through the boss 26 and be fixed to the spindle 10, thereby fixing the spindle 10 and the preload 12 in a fixed connection.

[0080] Furthermore, the first pressure plate 11 is provided with a fourth mounting hole, and the first wheel body 9 is provided with a threaded hole corresponding to the fourth mounting hole.

[0081] In this embodiment, the threaded hole 27 corresponding to the fourth mounting hole is provided on the outer side of the hub 15. After the connecting rope completes the preset action, the first pressure plate 11 is fixed to the outer wall of the hub 15 by screws, thereby pressing the connecting rope and fixing the connecting rope.

[0082] In this embodiment, there are at least two fourth mounting holes, which can ensure that the first pressure plate 11 will not rotate, thereby improving the stability of the first pressure plate 11 and the connecting rope.

[0083] Furthermore, the second synchronous pulley 7 includes a second pulley body 29, an end plate 30, and a second pressure plate 31; the end plate 30 is disposed at one end of the second pulley body 29 and is used to seal one end of the second pulley body 29; the end plate 30 is provided with a fifth mounting hole 32; the second pressure plate 31 is disposed on the outer wall of the second pulley body 29 and is used to fix the connecting rope on the second pulley body 29.

[0084] In this embodiment, the end plate 30 is equivalent to the mounting plate 16 in the first wheel body 9, and a fifth mounting hole 32 is provided on it for connecting with the second hinge 8.

[0085] In this embodiment, the connecting rope is wound around the outer wall of the second wheel body 29, and the connecting rope is pressed by the second pressure plate 31 to fix the connecting rope.

[0086] In this embodiment, the structure of the second pressure plate 31 is the same as that of the first pressure plate 11.

[0087] Furthermore, the synchronous deployment structure of the solar array also includes a guide 3, which is used to guide the connecting rope.

[0088] In this embodiment, the guide member 3 is used to guide the connecting rope between the first synchronous pulley 1 and the second synchronous pulley 7.

[0089] Specifically, in this embodiment, the guide member 3 is disposed at both ends of the inner sail 5.

[0090] Furthermore, the guide component 3 includes a mounting base 33, a guide plate 34, and a guide shaft 35; the guide plate 34 is disposed on the mounting base 33, and a guide groove is formed between multiple guide plates 34; the guide shaft 35 passes through the guide plate 34.

[0091] Specifically, in this embodiment, the mounting base 33 is used to install the guide member 3 at the end of the inner sail 5, the guide plate 34 is fixed on the mounting base 33, the guide shaft 35 is set through all the guide plates 34, the connecting rope passes through the guide groove formed between adjacent guide plates 34, and rotates around the guide shaft 35.

[0092] Furthermore, the connecting rope is Kevlar rope 4.

[0093] Kevlar rope 4 has the following characteristics: high temperature resistance, fire retardancy, light weight, high strength, high modulus, dimensional stability, low shrinkage, puncture resistance, wear resistance, heat resistance, chemical corrosion resistance, good mechanical properties, and good dielectric properties.

[0094] Kevlar rope 4 is widely used in the manufacture of ship cables, submarine cables, and fiber optic reinforced cables.

[0095] It should be noted that in this embodiment, the connecting rope can be a Kevlar rope 4, but it is not limited to Kevlar rope 4. It can also be other rope structures that can be used for connection, as long as they can enable the first synchronous pulley 1 and the second synchronous pulley 7 to rotate synchronously.

[0096] In this invention, such as Figures 10 to 13 As shown, the solar array synchronous deployment mechanism is a synchronous mechanism for the deployment of the solar array, used for the synchronous deployment of each solar array panel. In the initial deployment state, the solar array is folded and pressed against the surface of the celestial body. After the spacecraft enters orbit, the pressing release device is unlocked, and the panels are deployed under the action of the hinge. The inner panel 5 rotates around the first hinge 2, and the connecting rope wrapped around the first synchronous wheel 1 rotates counterclockwise around the rotation axis of the first hinge 2 in the direction shown in the figure. The connecting rope on the side closer to the outer panel 6 in the figure is the tight side, and the connecting rope on the side closer to the inner panel 5 is the loose side. Since the connecting rope is pressed by the first pressure plate 11 and the second pressure plate 31 after being wrapped around the first synchronous wheel 1 and the second synchronous wheel 7, the connecting rope and the first synchronous wheel 1 and the second synchronous wheel 7 will not slip. As the panels are continuously deployed, the tight side continuously pulls the loose side and causes the outer panel 6 to deploy. After the inner panel 5 is deployed and locked, the outer panel 6 is simultaneously deployed and locked.

[0097] The beneficial effects of the embodiments of the present invention are:

[0098] In the synchronous deployment mechanism, the first synchronous wheel 1 and the first hinge 2 are coaxial, the second synchronous wheel 7 and the second hinge 8 are coaxial, and the first synchronous wheel 1 and the second synchronous wheel 7 are linked by the pull rope 4, which can realize the synchronous deployment of the inner solar panel 5 and the outer solar panel 6.

[0099] The overall structure is simple, lightweight, and reliable in deployment. Compared with traditional synchronous deployment mechanisms, the synchronous deployment mechanism of this invention can be placed on either the inside or outside of the sailboard, making it more flexible in use.

[0100] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A solar wing synchronous deployment structure, characterized in that, It includes a first synchronous pulley, a second synchronous pulley, a first hinge, a second hinge, and a connecting rope; The first hinge is used to connect the inner solar panel and the spacecraft body, and the second hinge is used to connect the inner solar panel and the outer solar panel; The first synchronous pulley is coaxially arranged with the first hinge, which can drive the inner sail to rotate around the first hinge; The second synchronous pulley is coaxially arranged with the second hinge, and can drive the outer sail to rotate around the second hinge; The first synchronous pulley and the second synchronous pulley are connected by the connecting rope; The first synchronous pulley includes a first pulley body, a main shaft, a preload, a line stop plate, and a first pressure plate; The pretensioner is disposed inside the first wheel body, and the connecting rope is connected to the pretensioner; The line stop plate is disposed at the end of the wheel body to prevent the connecting rope from detaching from the pretensioner; The main shaft passes through the first wheel body and is connected to the preload member; A notch is provided on the side wall of the first wheel body, and the connecting rope is set on the pretensioner through the notch; The first pressure plate is disposed on the outer wall of the wheel body and is used to press the connecting rope wrapped around the outer wall of the first wheel body onto the first wheel body; The pretensioning component includes a pretensioning disc, gear teeth, a first positioning part, and a second positioning part; Both the first positioning part and the second positioning part are disposed on one side of the pre-tightening plate, and there is a set gap between the first positioning part and the second positioning part; The gear teeth are disposed on the outer edge of the other side of the preload disc; The pre-tightening plate is provided with a third mounting hole.

2. Solar wing synchronous deployment structure according to claim 1, characterized in that The first wheel body includes a hub, a rim, a mounting plate, and a connecting rib; The rim is disposed at opposite ends of the hub, so that the outer wall of the hub forms a limiting groove that can limit the position of the connecting rope. The mounting plate is disposed on the inner side of the wheel body and is coaxially disposed with the wheel hub. The mounting plate is connected to the inner wall of the wheel hub through the connecting rib. The mounting plate is provided with a first mounting hole and a second mounting hole.

3. The synchronous deployment structure of the solar array according to claim 1, characterized in that, The second positioning part is provided with a boss.

4. The synchronous deployment structure of the solar array according to claim 1, characterized in that, The first pressure plate is provided with a fourth mounting hole, and the first wheel body is provided with a threaded hole corresponding to the fourth mounting hole.

5. The synchronous deployment structure of the solar array according to claim 1, characterized in that, The second synchronous pulley includes a second pulley body, an end plate, and a second pressure plate; The end plate is disposed at one end of the second wheel body and is used to seal one end of the second wheel body; The end plate is provided with a fifth mounting hole; The second pressure plate is disposed on the outer wall of the second wheel body and is used to fix the connecting rope to the second wheel body.

6. The synchronous deployment structure of the solar array according to claim 1, characterized in that, It also includes a guide member for guiding the connecting rope.

7. The synchronous deployment structure of the solar array according to claim 6, characterized in that, The guide component includes a mounting base, a guide plate, and a guide shaft; The guide plate is disposed on the mounting base, and a guide groove is formed between multiple guide plates; The guide shaft is disposed through the guide plate.

8. The solar array synchronous deployment structure according to claim 1, characterized in that, The connecting rope is a Kevlar rope.

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