A flexible hinge deployment mechanism for a spacecraft solar array

Abstract

The application discloses a flexible hinge unfolding mechanism for a spacecraft solar array and belongs to the field of spacecraft instruments. The flexible hinge unfolding mechanism for the spacecraft solar array comprises a connecting plate, further comprises a cross connecting rod rotating on one side of the connecting plate through a rotating shaft, and is further provided with a driving assembly connected between the connecting plate and the cross connecting rod through the rotating shaft rotating connection; and the unfolding plate is arranged on both sides of the cross connecting rod. The application can be stored for protection according to requirements, prevent the area of impact from being easily increased due to the excessively large unfolding angle, and can spray protective oil during the unfolding process of the flexible solar panel, prevent the problem that the surface protection measures of the flexible solar panel are reduced due to long-time use, further prolong the service life, and can uniformly scrape the surface protective oil of the flexible solar panel, prevent the local surface of the flexible solar panel from being unable to spray the protective oil, and further reduce the waste of the protective oil.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of space equipment, and particularly relates to a flexible hinge unfolding mechanism for a solar array of a spacecraft. BACKGROUND

[0002] With the increasing demand of space missions and the development of spacecraft technology, more and more attention has been paid to the research and development of spacecraft mechanism technology. The flexible chain unfolding mechanism of a spacecraft solar array is a mechanism for unfolding a solar cell array. It is mainly used on spacecraft such as satellites and space probes to unfold solar cells for power supply.

[0003] The flexible chain unfolding mechanism usually uses one or more flexible chains to unfold the solar cell array from the spacecraft through pulses or other mechanical means. These chains can bend and stretch to adapt to the changing shape in the space environment.

[0004] The existing solar cell array is not convenient to adjust and store due to the large angle during unfolding, which can increase the impact area. In addition, the protective measures on the surface of the solar cell array will decrease over time due to long-term use, which is not convenient for timely maintenance, further reducing the service life. SUMMARY

[0005] The purpose of the present application is to solve the problem of the prior art that the angle is too large to be adjusted and stored, and a flexible hinge unfolding mechanism for a solar array of a spacecraft is provided.

[0006] In order to achieve the above purpose, the present application adopts the following technical scheme:

[0007] A flexible hinge unfolding mechanism for a solar array of a spacecraft, comprising a connecting plate, a cross link rotating on one side of the connecting plate through a rotating shaft, and a driving assembly connected between the connecting plate and the cross link through the rotating shaft, further comprising:

[0008] An unfolding plate is arranged on both sides of the cross link and connected through hinges, one side of the unfolding plate is provided with a winding box, and the inside of the winding box is provided with a flexible solar panel.

[0009] A linkage mechanism is arranged on one side of the unfolding plate, and the linkage mechanism is used for winding the flexible solar panel.

[0010] A protection mechanism is arranged above the winding box to spray protective oil on the surface of the flexible solar panel.

[0011] A scraping mechanism is arranged on one side of the winding box to scrape the protective film after spraying on the flexible solar panel.

[0012] Preferably, the linkage mechanism comprises a winding roller rotatably connected to one side of the winding box through a bearing, the winding roller being used for winding the flexible solar panel, one end of the winding roller being fixedly connected with a bevel gear one.

[0013] Preferably, the linkage mechanism further comprises a connecting shaft rotatably connected to the inner side of the unfolding plate through a bearing, both ends of the connecting shaft being fixedly connected with a bevel gear two and a gear disc respectively, the gear disc being meshingly connected with the surface of the bevel gear one, the gear disc being meshingly connected with each other.

[0014] Preferably, the protection mechanism comprises a storage box fixed to the top of the winding box, the inside of the storage box being slidably connected with a baffle, one side of the baffle being provided with a rotating tooth and a limiting box respectively, the end of the rotating tooth being fixedly connected with the winding roller, the limiting box being fixedly connected with the surface of the baffle, the inside of the limiting box being slidably connected with an abutting block, the surface of the abutting block being fitted with the surface of the rotating tooth.

[0015] Preferably, one side of the storage box is fixedly connected with a fixed plate, the inside of the fixed plate being slidably connected with a guide rod, the end of the guide rod being fixedly connected with the limiting box, the fixed plate and the guide rod being fixedly connected with a return spring.

[0016] Preferably, the inside of the limiting box is fixedly connected with an abutting spring, the end of the abutting spring being fixedly connected with the abutting block.

[0017] Preferably, the scraping mechanism comprises a fixed box fixed to both sides of the winding box, the inside of the fixed box being fixedly connected with a fixed rod, the surface of the fixed rod being slidably connected with a moving plate, the surface of the moving plate being fixedly connected with a plurality of scraping brushes.

[0018] Preferably, the inside of the fixed box is fixedly connected with a supporting spring one, the surface of the supporting spring one being fixedly connected with the surface of the moving plate.

[0019] Preferably, the end of the flexible solar panel is fixedly connected with a limiting plate, the surface of the limiting plate being fixedly connected with a supporting spring two, the limiting plate being slidably connected with the surface of the connecting shaft, the supporting spring two being fixedly connected with the inside of the unfolding plate.

[0020] Compared with the prior art, the present application provides a flexible hinge unfolding mechanism for a spacecraft solar array, which has the following beneficial effects:

[0021] 1. The flexible hinge unfolding mechanism for the spacecraft solar array, through the action of linkage mechanism, makes it can roll or release the flexible solar panel in the process of unfolding or folding the cross link pair of unfolding plate, through the setting of this way, realizes can be stored according to the demand protection, prevent the area of impact from being easily increased due to the angle of unfolding is too large, further improve the safety when using.

[0022] 2. The flexible hinge unfolding mechanism for the spacecraft solar array, through the cooperation between the baffle, rotating tooth, limiting box and abutting block, the protection liquid in the storage box can be sprayed out, through the setting of this way, realizes that the flexible solar panel can be sprayed with protective oil during unfolding, prevents the problem that the protective measures of the surface of the flexible solar panel are reduced after long-term use, further prolongs the service life.

[0023] 3. The flexible hinge unfolding mechanism for the spacecraft solar array, through the cooperation between the fixed box, fixed rod, moving plate and scraping brush, the protective oil after spraying can be scraped, through the setting of this way, realizes that the surface protective oil of the flexible solar panel can be scraped uniformly, prevents the local surface of the flexible solar panel from being unable to spray protective oil, further reduces the waste of protective oil.

[0024] The part not involved in the device is the same as or can be realized by the prior art, the present application can be stored according to the demand protection, prevent the area of impact from being easily increased due to the angle of unfolding is too large, and the flexible solar panel can be sprayed with protective oil during unfolding, prevents the problem that the protective measures of the surface of the flexible solar panel are reduced after long-term use, further prolongs the service life, and the surface protective oil of the flexible solar panel can be scraped uniformly, prevents the local surface of the flexible solar panel from being unable to spray protective oil, further reduces the waste of protective oil. BRIEF DESCRIPTION OF DRAWINGS

[0025] Figure 1 It is a structure diagram of a flexible hinge unfolding mechanism for the spacecraft solar array proposed by the present application;

[0026] Figure 2 It is a linkage mechanism structure diagram of a flexible hinge unfolding mechanism for the spacecraft solar array proposed by the present application Figure One ;

[0027] Figure 3 It is a linkage mechanism structure diagram of a flexible hinge unfolding mechanism for the spacecraft solar array proposed by the present application Figure Two ;

[0028] Figure 4A structural schematic diagram of a flexible hinge deployment mechanism for a spacecraft solar array is provided in the present application.

[0029] Figure 5 A protective mechanism structural schematic diagram of a flexible hinge deployment mechanism for a spacecraft solar array is provided in the present application. Figure One

[0030] Figure 6 A protective mechanism structural schematic diagram of a flexible hinge deployment mechanism for a spacecraft solar array is provided in the present application. Figure Two

[0031] Figure 7 A structural schematic diagram of a scraping mechanism of a flexible hinge deployment mechanism for a spacecraft solar array is provided in the present application.

[0032] Figure 8 A structural schematic diagram of a deployment plate of a flexible hinge deployment mechanism for a spacecraft solar array is provided in the present application.

[0033] In the figure: 1, connecting plate; 2, cross link; 3, deployment plate; 4, winding box; 5, flexible solar panel;

[0034] 6, linkage mechanism; 61, winding roller; 62, conical gear one; 63, connecting shaft; 64, conical gear two; 65, gear disc;

[0035] 7, protective mechanism; 71, storage box; 72, baffle; 73, rotating teeth; 74, limiting box; 75, abutting block; 76, fixed plate; 77, guide rod; 78, reset spring; 79, abutting spring;

[0036] 8, scraping mechanism; 81, fixed box; 82, fixed rod; 83, moving plate; 84, scraping brush; 85, supporting spring one;

[0037] 9, driving assembly; 10, limiting plate; 11, supporting spring two. DETAILED DESCRIPTION

[0038] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all the embodiments.

[0039] ​​In the description of the present application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do 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.

[0040] In one embodiment, referring to Figures 1-8 A flexible hinge deployment mechanism for a spacecraft solar array, comprising a connecting plate 1, further comprising a cross-link 2 rotating on one side of the connecting plate 1 through a rotating shaft, and a driving assembly 9 rotatingly connected between the connecting plate 1 and the cross-link 2 through a rotating shaft, further comprising:

[0041] A deployment plate 3 is arranged on both sides of the cross-link 2, and the deployment plates 3 are connected by a hinge, and one side of the deployment plate 3 is provided with a winding box 4, and the inside of the winding box 4 is provided with a flexible solar panel 5;

[0042] A linkage mechanism 6 is arranged on one side of the deployment plate 3, and the linkage mechanism 6 is used to wind the flexible solar panel 5;

[0043] A protection mechanism 7 is arranged above the winding box 4 to spray protective oil on the surface of the flexible solar panel 5;

[0044] A scraping mechanism 8 is arranged on one side of the winding box 4 to scrape the protective film sprayed on the flexible solar panel 5.

[0045] With such a scheme, the driving assembly 9 at the bottom of the connecting plate 1 is driven to expand the cross-link 2, which will drive the deployment plate 3 to expand synchronously during the expansion of the cross-link 2. At this time, the deployment plate 3 will drive the linkage mechanism 6 to rotate synchronously during the expansion, and the flexible solar panel 5 in the winding box 4 will be loosened during the expansion of the linkage mechanism 6, so as to gradually expand the flexible solar panel 5. During the driving of the linkage mechanism 6, the protection mechanism 7 will work synchronously to spray protective oil on the flexible solar panel 5 during the expansion, and the scraping mechanism 8 will uniformly scrape the protective oil, further improving the service life of the flexible solar panel 5.

[0046] On the basis of the prior art, sensors and control systems can be introduced to increase the control of the expansion process of the driving assembly 9. By measuring the mechanical state inside the expander, the control system can adjust the expansion speed and amplitude in real time according to the set rules, and correct the influence of the external environment on the expansion movement, so as to achieve more stable and controllable results;

[0047] And in response to extreme environmental changes, such as the atmosphere and space electromagnetic radiation, etc. ; because the material commonly used in the flexible hinge deployment mechanism is mainly metal material, this material is easy to damage or deformation, so that the deployment mechanism fails, therefore, can consider the use of new composite materials, such as high polymer plastics, carbon fiber, etc. These materials have better fatigue resistance and corrosion resistance, and can overcome the shortcomings of metal materials, improve the robustness and reliability of the flexible hinge deployment mechanism, at the same time, optimize the structure design of the deployment mechanism, reduce the material stress and reduce the accidental friction between the parts, to reduce the generation of defects.

[0048] It should be noted that the driving assembly 9 is a linear motion mode, such as hydraulic cylinder, electric push rod, screw rod and other groups.

[0049] In one embodiment, the linkage mechanism 6 includes a winding roller 61 rotating on one side of the winding box 4 through a bearing, the winding roller 61 is used to wind the flexible solar panel 5, one end of the winding roller 61 is fixedly connected with a bevel gear one 62, the linkage mechanism 6 further includes a connecting shaft 63 rotating in the inside of the deployment plate 3 through a bearing, both ends of the connecting shaft 63 are fixedly connected with a bevel gear two 64 and a gear disc 65 respectively, the gear disc 65 is engagedly connected with the surface of the bevel gear one 62, and the gear disc 65 is engagedly connected with each other.

[0050] With such a scheme, during the driving of the linkage mechanism 6, since the gear disc 65 is engagedly connected, an angle difference will be generated when the deployment plate 3 is deployed, which will drive the gear disc 65 to rotate, the gear disc 65 drives the connecting shaft 63 to rotate, the connecting shaft 63 drives the bevel gear two 64 to rotate, and the bevel gear two 64 drives the fixed winding roller 61 of the bevel gear one 62 to rotate during the rotation of the bevel gear two 64, through the rotation of the winding roller 61, the flexible solar panel 5 is sent and placed, so as to be deployed and used. Through the opposite operation, the flexible solar panel 5 can be wound to protect it.

[0051] It should be noted that the gear ratio of the gear disc 65, the bevel gear two 64 and the bevel gear one 62 is matched, so when the deployment plate 3 is in a horizontal state, the flexible solar panel 5 can also be completely deployed for use.

[0052] In one embodiment, the protection mechanism 7 includes a storage box 71 fixed on the top of the winding box 4, the inside of the storage box 71 is slidingly connected with a baffle 72, one side of the baffle 72 is respectively provided with a rotating tooth 73 and a limiting box 74, the rotating tooth 73 is fixedly connected with the end of the winding roller 61, the limiting box 74 is fixedly connected with the surface of the baffle 72, the inside of the limiting box 74 is slidingly connected with a contact block 75, the contact block 75 is attached to the surface of the rotating tooth 73, one side of the storage box 71 is fixedly connected with a fixed plate 76, the inside of the fixed plate 76 is slidingly connected with a guide rod 77, the end of the guide rod 77 is fixedly connected with the limiting box 74, the fixed plate 76 and the guide rod 77 are fixedly connected with a return spring 78, the inside of the limiting box 74 is fixedly connected with a contact spring 79, the contact spring 79 is fixedly connected with the end of the contact block 75.

[0053] With such a scheme, during the driving process of the protection mechanism 7, the rotating tooth 73 is driven to rotate by the winding roller 61, when the rotating tooth 73 is in the process of forward rotation, the rotating tooth 73 drives the contact block 75 on the surface to rotate, because the contact block 75 and the rotating tooth 73 are in contact with each other at this time, the contact block 75 is pushed by the rotating tooth 73, so that the contact block 75 drives the limiting box 74 to move, the limiting box 74 in turn drives the baffle 72 and the guide rod 77 to move, when the baffle 72 moves, the bottom of the storage box 71 is intermittently formed to automatically overflow the protection oil in the storage box 71 to the surface of the flexible solar panel 5, and the rotating tooth 73 rotates to continuously spray the protection oil on the flexible solar panel 5, so as to play a protective role every time when it is unfolded.

[0054] When the rotating tooth 73 is in the process of reverse rotation, when the rotating tooth 73 contacts the contact block 75, because the rotating tooth 73 and the contact block 75 are both trapezoidal, the rotating tooth 73 will lift the contact block 75 upward, so as not to affect the normal operation of the rotating tooth 73, under the setting of the contact spring 79, the automatic resetting of the contact block 75 can be ensured, so as to be used repeatedly for many times.

[0055] The setting of the return spring 78 can support the fixed plate 76 and the guide rod 77, so that the baffle 72 can be automatically reset when the guide rod 77 does not move, the baffle 72 can be automatically reset to prevent the protection oil in the storage box 71 from continuing to overflow.

[0056] It should be noted that the material of the protection oil is polyimide oil, which has the effects of high temperature resistance, corrosion resistance, ultraviolet resistance and the like on the surface of the flexible solar panel 5, thereby greatly improving the safety of the flexible solar panel 5 in use, and the polyimide oil is in a semi-liquid state, so it will not be affected by the gravity of outer space and cannot be attached to the surface of the flexible solar panel 5.

[0057] In one embodiment, the scraping mechanism 8 comprises a fixed box 81 fixed on both sides of the winding box 4, the inside of the fixed box 81 is fixedly connected with a fixed rod 82, the surface of the fixed rod 82 is slidingly connected with a moving plate 83, the surface of the moving plate 83 is fixedly connected with a plurality of scraping brushes 84, the inside of the fixed box 81 is fixedly connected with a supporting spring one 85, and the surface of the supporting spring one 85 is fixedly connected with the moving plate 83.

[0058] With such a scheme, the fixed rod 82 can be supported and fixed by the fixed box 81. Since the fixed box 81 is connected with the inside of the winding box 4, the moving plate 83 slidingly connected with the surface of the fixed rod 82 can be penetrated into the inside of the winding box 4. Since the moving plate 83 is provided in two groups, the moving plate 83 can be located on the upper and lower surfaces of the flexible solar panel 5. Then, the scraping brushes 84 are provided to make the flexible solar panel 5 adhere to the surface of the flexible solar panel 5, so that the residual protective oil on the surface of the flexible solar panel 5 can be scraped, which can be evenly applied to the surface of the flexible solar panel 5, thereby greatly improving the service life of the flexible solar panel 5.

[0059] With the supporting spring one 85, the adhesion between the scraping brushes 84 and the flexible solar panel 5 can be automatically adjusted, so that the scraping is more uniform.

[0060] In one embodiment, the end of the flexible solar panel 5 is fixedly connected with a limiting plate 10, the surface of the limiting plate 10 is fixedly connected with a supporting spring two 11, the limiting plate 10 is slidingly connected with the surface of the connecting shaft 63, and the supporting spring two 11 is fixedly connected with the inside of the unfolding plate 3.

[0061] With such a scheme, the limiting plate 10 can be sleeved with the surface of the connecting shaft 63 to ensure the performance of the end of the flexible solar panel 5 during movement. Meanwhile, the end of the flexible solar panel 5 is limited during winding to prevent the flexible solar panel 5 from being completely recovered by the linkage mechanism 6 and being difficult to unfold. Furthermore, the supporting spring two 11 can provide a reaction force to the limiting plate 10 during the loosening and releasing of the flexible solar panel 5, so that the limiting plate 10 can be quickly lifted to horizontally unfold the flexible solar panel 5, thereby further ensuring the flatness of the unfolding of the flexible solar panel 5.

[0062] It should be noted that the existing parts are all spacecrafts.

[0063] Specific use, use, first install the connecting plate 1 on the spacecraft, then through the drive assembly 9 at the bottom of the connecting plate 1 drive, so that it can deploy the cross link 2, in the process of cross link 2 expansion will drive the expansion plate 3 to expand, at this time the expansion plate 3 in the process of expansion, will drive the linkage mechanism 6 to rotate, in the process of linkage mechanism 6 expansion, can the flexible solar panel 5 in the winding box 4 to release, in order to gradually expand the flexible solar panel 5, and in the process of linkage mechanism 6 drive, in the process of linkage mechanism 6 drive, due to the meshing connection between the gear disc 65, so that when the expansion plate 3 is expanded, an angle difference will be generated, which will drive the gear disc 65 to rotate, the connecting shaft 63 drives the bevel gear two 64 to rotate, the bevel gear two 64 rotates and drives the winding roller 61 fixed with the bevel gear one 62 to rotate, through the rotation of the winding roller 61, the flexible solar panel 5 will be sent, in order to expand the flexible solar panel 5 for use, through the opposite operation, the flexible solar panel 5 can be wound, in order to play a protective role, at the same time will drive the protection mechanism 7 to work, through the winding roller 61 drive the rotating tooth 73 to rotate, when the rotating tooth 73 rotates, the rotating tooth 73 will drive the surface of the abutting block 75 to rotate, because the abutting block 75 and the rotating tooth 73 are in mutual abutting state at this time, the abutting block 75 will be pushed by the rotating tooth 73, so that the abutting block 75 drives the limiting box 74 to move, the limiting box 74 drives the baffle 72 and the guide rod 77 to move in turn, when the baffle 72 moves, the bottom of the storage box 71 forms an intermittent, so that the protective oil in the storage box 71 automatically overflow to the surface of the flexible solar panel 5, in the rotating process of the rotating tooth 73, the protective oil on the flexible solar panel 5 is continuously sprayed, and under the action of the scraping mechanism 8, then through the setting of the scraping brush 84, it is attached to the surface of the flexible solar panel 5, so that the residual protective oil on the surface of the flexible solar panel 5 is scraped flat, so that it can be evenly applied on the surface of the flexible solar panel 5, further greatly improving the service life of the flexible solar panel 5.

[0064] The above is only the preferred embodiment of the present application, but the protection scope of the present application is not limited to this, any skilled person in the art can make equivalent replacement or change according to the technical scheme and the inventive concept of the present application within the technical range disclosed by the present application, which should be covered in the protection scope of the present application.

Claims

1. A flexible hinge deployment mechanism for a spacecraft solar array comprising a connecting plate (1), further comprising a cross-link (2) pivoted on one side of the connecting plate (1) by a pivot axis, and a drive assembly (9) connected between the connecting plate (1) and the cross-link (2) by a pivot axis, characterised in that, Also include; The expansion plate (3) is arranged on both sides of the cross link (2), and the expansion plates (3) are connected by hinges. One side of the expansion plate (3) is provided with a winding box (4), and the inside of the winding box (4) is provided with a flexible solar panel (5); The linkage mechanism (6) is arranged on one side of the expansion plate (3), and is used for winding the flexible solar panel (5); The protection mechanism (7) is arranged above the winding box (4) to spray protective oil on the surface of the flexible solar panel (5). The protection mechanism (7) includes a storage box (71) fixed on the top of the winding box (4), a baffle (72) slidably connected in the storage box (71), a rotating tooth (73) and a limiting box (74) arranged on one side of the baffle (72), respectively, the end of the winding roller (61) is fixedly connected with the rotating tooth (73), the limiting box (74) is fixedly connected with the surface of the baffle (72), and the limiting box (74) is slidably connected with a contact block (75), and the surface of the contact block (75) is matched with the surface of the rotating tooth (73). The scraping mechanism (8) is arranged on one side of the winding box (4) to scrape the protective film of the flexible solar panel (5) after spraying.

2. A flexible hinge deployment mechanism for a spacecraft solar array according to claim 1, wherein, The linkage mechanism (6) includes a winding roller (61) rotatably connected to one side of the winding box (4) through a bearing, and the winding roller (61) is used for winding the flexible solar panel (5), and one end of the winding roller (61) is fixedly connected with a bevel gear one (62).

3. A flexible hinge deployment mechanism for a spacecraft solar array according to claim 2, wherein, The linkage mechanism (6) further includes a connecting shaft (63) rotatably connected to the inside of the expansion plate (3) through a bearing, both ends of the connecting shaft (63) are fixedly connected with a bevel gear two (64) and a gear disc (65), respectively, the gear disc (65) is meshingly connected with the surface of the bevel gear one (62), and the gear disc (65) is meshingly connected with each other.

4. A flexible hinge deployment mechanism for a spacecraft solar array as in claim 1, wherein, One side of the storage box (71) is fixedly connected with a fixed plate (76), the inside of the fixed plate (76) is slidably connected with a guide rod (77), the end of the guide rod (77) is fixedly connected with a limiting box (74), and the fixed plate (76) and the guide rod (77) are fixedly connected with a return spring (78).

5. A flexible hinge deployment mechanism for a spacecraft solar array according to claim 4, wherein, The inside of the limiting box (74) is fixedly connected with a contact spring (79), and the end of the contact spring (79) is fixedly connected with the contact block (75).

6. A flexible hinge deployment mechanism for a spacecraft solar array as in claim 1, wherein, The scraping mechanism (8) includes a fixed box (81) fixed on both sides of the winding box (4), a fixed rod (82) fixedly connected in the fixed box (81), a movable plate (83) slidably connected with the surface of the fixed rod (82), and a plurality of scraping brushes (84) fixedly connected with the surface of the movable plate (83).

7. A flexible hinge deployment mechanism for a spacecraft solar array according to claim 6, wherein, The inside of the fixed box (81) is fixedly connected with a supporting spring one (85), and the surface of the movable plate (83) is fixedly connected with the supporting spring one (85).

8. A flexible hinge deployment mechanism for a spacecraft solar array according to claim 3, wherein, The end of the flexible solar panel (5) is fixedly connected with a limiting plate (10), the surface of the limiting plate (10) is fixedly connected with a supporting spring two (11), the limiting plate (10) is in surface sliding connection with a connecting shaft (63), and the supporting spring two (11) is fixedly connected with the inside of the unfolding plate (3).

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