A deployment mechanism for a spacecraft solar wing

Abstract

The present invention discloses a deployment mechanism of a spacecraft solar wing, belonging to the field of spacecraft solar wings. A deployment mechanism of a spacecraft solar wing comprises a mounting frame, a winding box, a side plate and a flexible solar wing, wherein the mounting frame is fixedly connected to the back of the winding box, the side plate is engaged with the opening of the winding box, and the flexible solar wing is arranged in the winding box, and further comprises: a deployment component arranged on the winding box, used to push the flexible solar wing to deploy; a cleaning mechanism located in the winding box; the present invention deploys the flexible solar wing by using a driving force to push the flexible solar wing to flip over, and this design can avoid the phenomenon that the deployment component will have a greater impact through vibration force in the traditional method, which will have a greater negative impact on the related components and spacecraft.

Description

Technical Field

[0001] The present invention relates to the technical field of spacecraft solar wing, and in particular to a deployment mechanism of a spacecraft solar wing. Background Art

[0002] Solar arrays are the main power supply device for spacecraft. Currently, the most widely used solar arrays are foldable solar arrays with rigid substrates, also known as solar wings. With the development of aerospace technology, spacecraft have an increasing demand for electricity, so large solar wings with a larger area that can be loaded on launch vehicles are needed to provide the main energy. As the area increases, the mass limitation of rigid solar arrays becomes a prominent problem. Flexible solar wings can effectively solve this problem due to their light weight and larger folding / expansion ratio. In order to enable the folded flexible solar wings to be unfolded, an unfolding mechanism is required to extend them.

[0003] At present, its deployment mechanism usually relies on the elastic force of a spring to deploy, so that the flexible solar wing connected to the deployment mechanism can be deployed. However, when the flexible solar wing is deployed using this deployment mechanism, the deployment mechanism will produce a large impact, which will have a significant negative impact on related components and spacecraft.

[0004] To this end, we proposed a deployment mechanism for spacecraft solar wings. Summary of the invention

[0005] The purpose of the present invention is to solve the problem in the prior art that a flexible solar wing connected to a deployment mechanism is deployed by relying on the elastic force of a spring, but when the flexible solar wing is deployed using this deployment mechanism, the deployment mechanism will produce a large impact, which has a significant negative impact on related components and spacecraft, and thus a deployment mechanism for a spacecraft solar wing is proposed.

[0006] In order to achieve the above object, the present invention adopts the following technical solutions:

[0007] A deployment mechanism for a spacecraft solar wing comprises a mounting frame, a winding box, a side plate and a flexible solar wing, wherein the mounting frame is fixedly connected to the back of the winding box, the side plate is engaged with an opening of the winding box, and the flexible solar wing is arranged in the winding box, and further comprises:

[0008] An unfolding assembly disposed on the winding box, used for pushing the flexible solar wing to unfold;

[0009] A cleaning mechanism located in the winding box is used to clean dust on the surface of the flexible solar wing when the flexible solar wing is retracted;

[0010] The auxiliary mechanism disposed in the unfolding assembly is used to enhance the cleaning range of the cleaning mechanism.

[0011] Preferably, the unfolding assembly includes a telescopic cylinder arranged on the top of the winding box, one end of the telescopic cylinder extension rod is fixedly connected to the side panel, a rectangular rack is fixed to the left side of the side panel, a circular gear 1 is meshed with the top of the rectangular rack, a rotating rod 1 is fixed at the axis of the circular gear 1, the rotating rod 1 is rotatably connected to the inner wall of the winding box through a bearing, a winding roller is fixed to the end of the rotating rod 1 away from the circular gear 1, one end of the flexible solar wing is fixedly connected to the outer surface of the winding roller, and the other end of the flexible solar wing is connected to the side panel.

[0012] Preferably, a mounting flange is fixed to the outer surface of the telescopic cylinder, and the mounting flange is fixed to the top of the winding box by bolts.

[0013] Preferably, the cleaning mechanism includes a support block fixed on the top of the mounting frame, a fixed cylinder is fixed on the right side of the support block, a piston moves in the fixed cylinder with a piston disk, a connecting rod is fixed on the right side of the piston disk, the right end of the connecting rod slides through the fixed cylinder and is fixedly connected to the side plate, and an outer surface of the fixed cylinder is connected to an air outlet hose.

[0014] Preferably, a mounting shell is fixed to the upper and lower top walls of the winding box, a connecting pipe is arranged in the mounting shell, the bottom end of the connecting pipe is connected to a nozzle, and the other end of the air outlet hose is connected to the mounting shell.

[0015] Preferably, the auxiliary mechanism includes a circular gear 2 fixed at the left end of a rotating rod 1, a circular gear 3 is provided above the circular gear 2, the circular gear 2 and the circular gear 3 are connected to each other through a belt gear transmission, a rotating rod 2 is fixed at the axis of the circular gear 3, and the rotating rod 2 is rotatably connected to the side wall of the mounting shell through a bearing.

[0016] Preferably, the auxiliary mechanism also includes a worm fixed at the right end of the second rotating rod, the outer surface of the worm is meshed with a worm wheel, a third rotating rod is fixed at the axis of the worm wheel, the third rotating rod is rotatably connected to the mounting shell through a bearing, a cam is fixed on the outer surface of the third rotating rod, a mounting groove is provided on the bottom wall of the mounting shell, an airbag is fixed in the mounting groove, and the connecting tube is fixed in the middle of the airbag.

[0017] Preferably, a limiting plate is fixed on the outer surface of the rotating rod 2, and the limiting plate is located on two side surfaces of the circular gear 3.

[0018] Preferably, a mounting hole for screwing in is provided inside the mounting frame.

[0019] Compared with the prior art, the present invention provides a deployment mechanism for a spacecraft solar wing, which has the following beneficial effects:

[0020] 1. The deployment mechanism of the solar wing of the spacecraft adopts a driving force to push the flexible solar wing by setting the deployment component, so that the flexible solar wing is flipped to unfold. This design can avoid the traditional method of using springs to push, which causes the deployment component to produce a large impact through vibration force, and has a significant negative impact on related components and spacecraft.

[0021] 2. The deployment mechanism of the solar wing of the spacecraft connects the fixed cylinder with the compressor in the cabin through the setting of the cleaning mechanism, so that when the flexible solar wing is retracted, the gas in the fixed cylinder can be squeezed to make the squeezed gas enter the connecting pipe and be sprayed out from the nozzle, thereby blowing away the dust adhering to the surface of the flexible solar wing, avoiding the dust adhering to the surface of the flexible solar wing, which will affect the use effect of the flexible solar wing.

[0022] 3. The deployment mechanism of the solar wing of the spacecraft, when the deployment component drives the flexible solar wing to retract, through the mutual cooperation between circular gear 2, circular gear 3, belt gear, rotating rod 2, worm, worm wheel, rotating rod 3, cam, mounting groove and airbag, can make the connecting pipe swing, thereby enhancing the cleaning range of the nozzle and further improving the cleaning effect.

[0023] The parts not involved in the device are the same as the prior art or can be implemented by the prior art. When the flexible solar wing is unfolded, the present invention can reduce the damage caused to the unfolding components. When the flexible solar wing is rolled up, the dust on the surface of the flexible solar wing can be blown away to avoid dust accumulation on the surface of the flexible solar wing and affecting the use effect of the flexible solar wing. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 This is a schematic diagram of the front view of the deployment component structure of a deployment mechanism of a spacecraft solar wing proposed by the present invention;

[0025] Figure 2 A schematic side view of the deployment assembly structure of a deployment mechanism of a spacecraft solar wing proposed by the present invention;

[0026] Figure 3 A deployment mechanism for a spacecraft solar wing proposed by the present invention Figure 2 A schematic diagram of the structure enlargement in the middle;

[0027] Figure 4 A schematic diagram of the auxiliary mechanism structure of a deployment mechanism of a solar wing of a spacecraft proposed by the present invention;

[0028] Figure 5 A deployment mechanism for a spacecraft solar wing proposed by the present invention Figure 4 A magnified schematic diagram of the structure at B in the middle;

[0029] Figure 6 A schematic diagram of the internal structure of a mounting shell of a deployment mechanism of a spacecraft solar wing proposed by the present invention;

[0030] Figure 7 A deployment mechanism for a spacecraft solar wing proposed by the present invention Figure 6 A magnified schematic diagram of the structure at C in the middle;

[0031] Figure 8 This is a schematic side view of the cross-section of the winding box structure of the deployment mechanism of a spacecraft solar wing proposed by the present invention.

[0032] In the figure: 1. Mounting frame; 2. Winding box; 3. Side panel; 4. Flexible solar wing;

[0033] 5. Unfolding assembly; 51. Telescopic cylinder; 52. Rectangular rack; 53. Circular gear 1; 54. Rotating rod 1; 55. Winding roller; 56. Mounting flange; 57. Bolts;

[0034] 6. Cleaning mechanism; 60. Support block; 61. Fixed cylinder; 62. Piston plate; 63. Connecting rod; 64. Air outlet hose; 65. Mounting shell; 66. Connecting pipe; 67. Spray nozzle;

[0035] 7. Auxiliary mechanism; 71. Circular gear 2; 72. Circular gear 3; 73. Belt gear; 74. Rotating rod 2; 75. Worm; 76. Worm wheel; 77. Rotating rod 3; 78. Cam; 79. Mounting groove; 710. Airbag; 8. Limit plate; 9. Mounting hole. DETAILED DESCRIPTION

[0036] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0037] In the description of the present invention, it is necessary to understand that the terms "upper", "lower", "front", "back", "left", "right", "top", "bottom", "inside", "outside", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0038] Reference Figure 1-Figure 8 A deployment mechanism of a spacecraft solar wing comprises a mounting frame 1, a winding box 2, a side plate 3 and a flexible solar wing 4, wherein the mounting frame 1 is fixedly connected to the back of the winding box 2, the side plate 3 is engaged with the opening of the winding box 2, and the flexible solar wing 4 is arranged in the winding box 2, and further comprises:

[0039] The unfolding assembly 5 arranged on the winding box 2 is used to push the flexible solar wing 4 to unfold;

[0040] The cleaning mechanism 6 located in the winding box 2 is used to clean the dust on the surface of the flexible solar wing 4 synchronously when the flexible solar wing 4 is retracted;

[0041] The auxiliary mechanism 7 disposed in the unfolding assembly 5 is used to increase the cleaning range of the cleaning mechanism 6 .

[0042] Among them, the unfolding component 5 includes a telescopic cylinder 51 arranged on the top of the winding box 2, one end of the extension rod of the telescopic cylinder 51 is fixedly connected to the side panel 3, a rectangular rack 52 is fixed to the left side of the side panel 3, and a circular gear 53 is meshed with the top of the rectangular rack 52. A rotating rod 54 is fixed at the axis of the circular gear 53, and the rotating rod 54 is rotatably connected to the inner wall of the winding box 2 through a bearing. A winding roller 55 is fixed to the end of the rotating rod 54 away from the circular gear 53, one end of the flexible solar wing 4 is fixedly connected to the outer surface of the winding roller 55, and the other end of the flexible solar wing 4 is connected to the side panel 3.

[0043] A mounting flange 56 is fixed to the outer surface of the telescopic cylinder 51 , and the mounting flange 56 is fixed to the top of the winding box 2 by bolts 57 .

[0044] The mounting frame 1 has a mounting hole 9 inside for screwing in.

[0045] In the prior art, the flexible solar wing 4 connected to the deployment component 5 is deployed by relying on the elastic force of the spring. However, when the flexible solar wing 4 is deployed by using the deployment component 5, the deployment component 5 will produce a large impact, which will have a great negative impact on the components and spacecraft related thereto. Now, an improvement is made, and the specific implementation method is as follows:

[0046] The output end of the telescopic cylinder 51 is connected to the side panel 3. When the telescopic cylinder 51 is started, the side panel 3 can be driven to move to the right. The side panel 3 is connected to the rectangular rack 52, and the side panel 3 will drive the rectangular rack 52 to move together. The rectangular rack 52 is meshed with the circular gear 1 53. The movement of the rectangular rack 52 can drive the circular gear 1 53 to rotate. The circular gear 1 53 and the rotating rod 1 54 are connected to the winding roller 55, so the winding roller 55 will be synchronously driven to flip. The flexible solar wing 4 is connected to the winding roller 55 and the side panel 3. When the winding roller 55 flips, the movement of the side panel 3 will drive the flexible solar wing 4 to extend outward, so that the flexible solar wing 4 is unfolded. This design uses the driving force of the telescopic cylinder 51 to unfold the flexible solar wing 4 by flipping it, which can avoid the traditional method of using a spring to push the unfolding component 5 to produce a large impact through the vibration force, which has a large negative impact on the related components and spacecraft.

[0047] Specifically, the screws are screwed into the mounting holes 9 to fix the mounting frame 1 on the spacecraft, thereby completing the installation of the mounting frame 1 and the winding box 2. When the flexible solar wing 4 needs to be unfolded, the telescopic cylinder 51 is started, and the telescopic cylinder 51 drives the side panel 3 to move to the right, so that the side panel 3 is disengaged from the opening of the winding box 2. When the side panel 3 moves, it will drive the rectangular rack 52 to move together, and the rectangular rack 52 drives the circular gear 53 to rotate, and the circular gear 53 drives the rotating rod 54 and the winding roller 55 to rotate. Through the rotation of the winding roller 55, the side panel 3 drives the flexible solar wing 4 to extend outward, so that the flexible solar wing 4 is unfolded, and the flexible solar wing 4 collects light energy and converts the light energy into electrical energy to power the electrical equipment in the spacecraft. This technology is a prior art, so it will not be described in detail here. When it needs to be retracted, the telescopic cylinder 51 is driven to drive the side panel 3 to move to the left.

[0048] It should be noted that, by providing the bolts 57 and the mounting flange 56 , the telescopic cylinder 51 can be installed on the top of the winding box 2 to improve stability.

[0049] In one embodiment, the cleaning mechanism 6 includes a support block 60 fixed on the top of the mounting frame 1, a fixed cylinder 61 is fixed on the right side of the support block 60, a piston moves in the fixed cylinder 61 with a piston disk 62, a connecting rod 63 is fixed on the right side of the piston disk 62, the right end of the connecting rod 63 slides through the fixed cylinder 61 and is fixedly connected to the side plate 3, and the outer surface of the fixed cylinder 61 is connected to an air outlet hose 64.

[0050] Among them, the upper and lower top walls of the winding box 2 are fixed with a mounting shell 65, a connecting pipe 66 is arranged in the mounting shell 65, the bottom end of the connecting pipe 66 is connected to the nozzle 67, and the other end of the air outlet hose 64 is connected to the mounting shell 65.

[0051] Specifically, it is connected to the side panel 3 through a connecting rod 63. When the telescopic cylinder 51 drives the side panel 3 to move to the left to retract the flexible solar wing 4, it can drive the connecting rod 63 to move to the left together, and is connected to the piston disk 62 through the connecting rod 63, thereby driving the piston disk 62 to move to the left in the fixed cylinder 61. A compressor is provided in the spacecraft, and the output end of the compressor is connected to the fixed cylinder 61 through an air intake pipe. The compressor injects air into the fixed cylinder 61 through the air intake pipe. Through the movement of the piston disk 62, the air is squeezed, so that the squeezed air enters the air outlet hose 64, and is connected to the mounting shell 65 through the air outlet hose 64. The air enters the mounting shell 65 from the air outlet hose 64, and is connected to the mounting shell 65 through the connecting pipe 66, so that the air can be ejected from the connecting pipe 66 and the nozzle 67, and the dust adhering to the surface of the flexible solar wing 4 can be blown away by the blown gas. This design can prevent dust from adhering to the surface of the flexible solar wing 4, thereby affecting the use effect of the flexible solar wing 4.

[0052] It should be noted that the air inlet pipe can be a hose to prevent the movement of the winding box 2 from affecting the entry of gas.

[0053] In one embodiment, the auxiliary mechanism 7 includes a circular gear 2 71 fixed at the left end of the rotating rod 1 54, a circular gear 3 72 is provided above the circular gear 2 71, the circular gear 2 71 and the circular gear 3 72 are connected to each other through a belt gear 73, a rotating rod 2 74 is fixed at the axis of the circular gear 3 72, and the rotating rod 2 74 is rotatably connected to the side wall of the mounting shell 65 through a bearing.

[0054] Among them, the auxiliary mechanism 7 also includes a worm 75 fixed at the right end of the rotating rod 2 74, the outer surface of the worm 75 is meshed with a worm wheel 76, a rotating rod 3 77 is fixed at the axis of the worm wheel 76, the rotating rod 3 77 is rotatably connected to the mounting shell 65 through a bearing, a cam 78 is fixed on the outer surface of the rotating rod 3 77, a mounting groove 79 is opened on the bottom wall of the mounting shell 65, an airbag 710 is fixed in the mounting groove 79, and the connecting tube 66 is fixed in the middle of the airbag 710.

[0055] A limiting plate 8 is fixed on the outer surface of the second rotating rod 74 , and the limiting plate 8 is located on two side surfaces of the circular gear three 72 .

[0056] Specifically, circular gear 2 71 is connected to rotating rod 1 54. When telescopic cylinder 51 drives side panel 3 and rectangular rack 52 to move left to retract flexible solar wing 4, circular gear 2 71 is driven to rotate together through rotation of circular gear 1 53 and rotating rod 1 54. Since circular gear 2 71 is connected to circular gear 3 72 through belt gear 73, circular gear 3 72 and rotating rod 2 74 are driven to rotate. Since rotating rod 2 74 is connected to worm 75, when rotating rod 2 74 rotates, worm 75 is driven to rotate. Through worm 75 meshing with worm wheel 76, worm wheel 76 and rotating rod 3 77 are driven to rotate. The third rod 77 is connected to the cam 78, and the rotating rod 77 drives the cam 78 to rotate. Due to the elasticity of the airbag 710, the connecting tube 66 and the nozzle 67 are in an unfixed state. When the cam 78 contacts the surface of the connecting tube 66, it drives the connecting tube 66 to deviate to the left, thereby increasing the spraying range of the connecting tube 66, thereby further improving the cleaning effect. The power for its operation is provided by the telescopic cylinder 51, and there is no need to install other power supplies, so that it can operate with the operation of the unfolding component 5, which is more convenient. When the cam 78 is separated from the surface of the connecting tube 66, the elasticity of the airbag 710 will reset the connecting tube 66 and the nozzle 67.

[0057] It should be noted that, by setting the limiting plate 8, the belt gear 73 can be limited to prevent the belt gear 73 from deviating during transmission.

[0058] Working principle: when the flexible solar wing 4 needs to be unfolded, the telescopic cylinder 51 is started, and the telescopic cylinder 51 drives the side panel 3 to move to the right, so that the side panel 3 is separated from the opening of the winding box 2. When the side panel 3 moves, it will drive the rectangular rack 52 to move together, and the rectangular rack 52 drives the circular gear 1 53 to rotate, and the circular gear 1 53 drives the rotating rod 1 54 and the winding roller 55 to rotate. Through the rotation of the winding roller 55, the side panel 3 drives the flexible solar wing 4 to extend outward, so that the flexible solar wing 4 is unfolded, and the flexible solar wing 4 is opened. The solar wing 4 collects light energy and converts it into electrical energy to power the electrical equipment in the spacecraft. When the telescopic cylinder 51 drives the side panel 3 to move leftward to retract the flexible solar wing 4, it can drive the connecting rod 63 to move leftward together, thereby driving the piston plate 62 to move leftward in the fixed cylinder 61. A compressor is provided in the spacecraft, and the output end of the compressor is connected to the fixed cylinder 61 through an air intake pipe. The compressor injects air into the fixed cylinder 61 through the air intake pipe, and the air is squeezed by the movement of the piston plate 62, so that the squeezed air is compressed. The compressed air enters the air outlet hose 64, and the air enters the mounting shell 65 from the air outlet hose 64, so that the air can be ejected from the connecting pipe 66 and the nozzle 67. The blown gas can blow away the dust adhering to the surface of the flexible solar wing 4. When the telescopic cylinder 51 drives the side plate 3 and the rectangular rack 52 to move to the left to retract the flexible solar wing 4, the circular gear 1 53 and the rotating rod 1 54 rotate, which will drive the circular gear 2 71 to rotate together, thereby driving the circular gear 3 72 and the rotating rod 2 74 to rotate. When the rotating rod 2 74 rotates, it will drive the worm 75 to rotate, and through the meshing of the worm 75 and the worm wheel 76, it will drive the worm wheel 76 and the rotating rod 3 77 to rotate, and the rotating rod 3 77 is connected to the cam 78, and the rotating rod 3 77 drives the cam 78 to rotate. Due to the elasticity of the airbag 710, the connecting tube 66 and the nozzle 67 will be in an unfixed state. When the cam 78 contacts the surface of the connecting tube 66, it will drive the connecting tube 66 to deviate to the left, thereby increasing the spraying range of the connecting tube 66 and improving the cleaning effect.

[0059] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. A deployment mechanism for a spacecraft solar wing, comprising a mounting frame (1), a winding box (2), a side plate (3) and a flexible solar wing (4), wherein the mounting frame (1) is fixedly connected to the back of the winding box (2), the side plate (3) is engaged with an opening of the winding box (2), and the flexible solar wing (4) is arranged in the winding box (2), characterized in that: Also includes: An unfolding assembly (5) arranged on the winding box (2) and used for pushing the flexible solar wing (4) to unfold; A cleaning mechanism (6) located in the reel box (2) is used to simultaneously clean dust on the surface of the flexible solar wing (4) when the flexible solar wing (4) is retracted; An auxiliary mechanism (7) disposed in the deployment assembly (5) and used to increase the cleaning range of the cleaning mechanism (6); The unfolding assembly (5) comprises a telescopic cylinder (51) arranged on the top of the winding box (2), one end of the extension rod of the telescopic cylinder (51) is fixedly connected to the side plate (3), a rectangular rack (52) is fixed to the left side of the side plate (3), a circular gear (53) is meshed on the top of the rectangular rack (52), a rotating rod (54) is fixed at the axis of the circular gear (53), the rotating rod (54) is rotatably connected to the inner wall of the winding box (2) through a bearing, a winding roller (55) is fixed to the end of the rotating rod (54) away from the circular gear (53), one end of the flexible solar wing (4) is fixedly connected to the outer surface of the winding roller (55), and the other end of the flexible solar wing (4) is connected to the side plate (3); The cleaning mechanism (6) comprises a support block (60) fixed to the top of the mounting frame (1); a fixed cylinder (61) is fixed to the right side of the support block (60); a piston disc (62) moves in the fixed cylinder (61); a connecting rod (63) is fixed to the right side of the piston disc (62); the right end of the connecting rod (63) slides through the fixed cylinder (61) and is fixedly connected to the side plate (3); and an air outlet hose (64) is connected to the outer surface of the fixed cylinder (61); The upper and lower top walls of the winding box (2) are both fixed with a mounting shell (65), a connecting pipe (66) is arranged inside the mounting shell (65), one end of the connecting pipe (66) is connected to a nozzle (67), and one end of the air outlet hose (64) is connected to the mounting shell (65); The auxiliary mechanism (7) comprises a circular gear 2 (71) fixed to the left end of the rotating rod 1 (54), a circular gear 3 (72) is provided above the circular gear 2 (71), the circular gear 2 (71) and the circular gear 3 (72) are connected to each other through a belt gear (73), a rotating rod 2 (74) is fixed at the axis of the circular gear 3 (72), and the rotating rod 2 (74) is rotatably connected to the side wall of the mounting shell (65) through a bearing; The auxiliary mechanism (7) further comprises a worm (75) fixed to the right end of the second rotating rod (74); the outer surface of the worm (75) is meshed with a worm wheel (76); a third rotating rod (77) is fixed at the axis of the worm wheel (76); the third rotating rod (77) is rotatably connected to the mounting shell (65) via a bearing; a cam (78) is fixed to the outer surface of the third rotating rod (77); a mounting groove (79) is formed on the bottom wall of the mounting shell (65); an air bag (710) is fixed in the mounting groove (79); and the connecting pipe (66) is fixed at the middle of the air bag (710).

2. A spacecraft solar wing deployment mechanism according to claim 1, characterized in that: A mounting flange (56) is fixed to the outer surface of the telescopic cylinder (51), and the mounting flange (56) is fixed to the top of the winding box (2) by bolts (57).

3. The deployment mechanism of a spacecraft solar wing according to claim 1, characterized in that: A limiting plate (8) is fixed on the outer surface of the second rotating rod (74), and the limiting plate (8) is located on two side surfaces of the third circular gear (72).

4. The deployment mechanism of a spacecraft solar wing according to claim 1, characterized in that: The interior of the mounting frame (1) is provided with a mounting hole (9) for screwing in a screw.

Images