Comprehensive unfolding flexible solar wing device

Abstract

The utility model relates to the field of aircrafts, in particular to a fully unfolded flexible solar wing which comprises a shell and an unfolding device, the shell comprises a supporting body, a long side plate, a short side plate, a lower side plate and a front side plate, the long side plate is hinged to the upper end of the supporting body through a spring shaft, and the short side plate is hinged to one side of the long side plate through a spring shaft; the lower side plates are hinged to the lower ends of the long side plates through spring shafts, and the front side plates are hinged to the sides, away from the supporting body, of the long side plates through spring shafts. The unfolding device comprises a telescopic spring rod, an inner ring flexible solar wing roll, a middle ring flexible solar wing roll, an outer ring flexible solar wing roll, a front connecting rope, a middle connecting rope, a rear connecting rope, a front torsional spring rod, a middle torsional spring rod and a rear torsional spring rod. The telescopic spring rods are driven to automatically extend and stretch out and draw back, and meanwhile the three sets of flexible solar wing rolls are driven to be unfolded.

Description

Technical Field

[0001] This utility model relates to the field of aircraft, specifically to a fully deployable flexible solar panel. Background Technology

[0002] As a core component of next-generation spacecraft power systems, the flexible solar array's deployment ratio is one of the key indicators for evaluating its performance. The deployment ratio is defined as the ratio of the solar array's area when fully deployed to its volume when folded. A higher deployment ratio means that the solar array can provide a larger power generation area within the limited rocket payload space, thereby increasing the spacecraft's power output. Therefore, optimizing the solar array's folding method and packaging structure to minimize the folded volume and improve the deployment ratio is crucial. Summary of the Invention

[0003] Therefore, this utility model is a fully deployable flexible solar array. By installing thermocouples on the front and lower side plates, and the short and lower side plates, when the satellite is in space, the thermocouples are sequentially heated until they melt. Then, the hinged long, short, lower, and front side plates retract, preventing the plates from obstructing the solar array's light-receiving surface and affecting its efficiency. By releasing the long side plate's restriction on the telescopic spring rod, the telescopic spring rod automatically extends and retracts, simultaneously deploying three sets of flexible solar array rolls. Three sets of torsion spring rods also pull on these rolls, achieving automatic solar array extension and reducing the satellite's overall weight. This utility model achieves the above objectives through the following technical solutions:

[0004] A fully deployable flexible solar array device includes: a housing and a deployment mechanism. The housing includes a support body, a long side plate, a short side plate, a lower side plate, and a front side plate. The long side plate is hinged to the upper end of the support body via a spring shaft. The short side plate is hinged to one side of the long side plate via a spring shaft. The lower side plate is hinged to the lower end of the long side plate via a spring shaft. The front side plate is hinged to the side of the long side plate away from the support body via a spring shaft. The deployment mechanism includes a telescopic spring rod, an inner flexible solar array roll, a middle flexible solar array roll, an outer flexible solar array roll, a front connecting rope, a middle connecting rope, a rear connecting rope, a front torsion spring rod, a middle torsion spring rod, and a rear torsion spring rod. The telescopic spring rod is fixed to the long side plate. On one side, the inner flexible solar panel roll is fixed to the outer circumference of the telescopic spring rod, the middle flexible solar panel roll is slidably connected to the outer circumference of the inner flexible solar panel roll, the outer flexible solar panel roll is slidably connected to the outer circumference of the middle flexible solar panel roll, the front torsion spring rod is nested in the inner circumference of the middle torsion spring rod, the middle torsion spring rod is nested in the inner circumference of the rear torsion spring rod, the two ends of the front connecting rope are respectively fixed to the outer rotating ring plate of the front torsion spring rod and the head of the inner flexible solar panel roll, the two ends of the middle connecting rope are respectively fixed to the outer rotating ring plate of the middle torsion spring rod and the head of the middle flexible solar panel roll, and the two ends of the rear connecting rope are respectively fixed to the outer rotating ring plate of the rear torsion spring rod and the head of the outer flexible solar panel roll.

[0005] Preferably, the hinge between the long side plate and the short side plate, and the hinge between the lower side plate and the front side plate are provided with hot-melt wires, which are fixed to the edges of adjacent plate surfaces.

[0006] Preferably, the telescopic spring rod includes a bottom support rod, an inner spring rod, a middle connecting rod, an inner ring support rod, and an inner ring spring rod. The bottom support rod is fixed to the support body, the inner spring rod is slidably connected to the inside of the bottom support rod, the middle connecting rod is fixed to the outer circumference of the inner spring rod and fixedly connected to the rear end of the middle ring flexible solar panel roll, the inner ring support rod slides through the top cover of the inner spring rod, and the inner ring spring rod is fixed inside the inner ring support rod.

[0007] Preferably, the outer ring plates of the front torsion spring rod, the middle torsion spring rod, and the rear torsion spring rod are all provided with long sliders, and the support body is provided with a groove that matches the long slider. The groove of the front torsion spring rod is slidably connected to the slider of the middle torsion spring rod, and the groove of the middle torsion spring rod is slidably connected to the slider of the rear torsion spring rod.

[0008] Preferably, the inner flexible solar array roll, the middle flexible solar array roll, and the outer flexible solar array roll are all provided with ring plates on their solar array support plates, and the ring plates are slidably connected to the crossbars of adjacent flexible solar array rolls through crossbars.

[0009] Preferably, after the shell is unfolded, the long side plate is perpendicular to the supporting body, the short side plate is parallel to the long side plate, and the lower side plate and the front side plate are coplanar with the bottom of the supporting body.

[0010] The beneficial effects of this utility model are:

[0011] 1. This utility model provides hot-melt wires on the front and lower side plates, and the short and lower side plates. When the satellite is in space, the hot-melt wires are heated sequentially to melt them. Then, the long side plates, short side plates, lower side plates, and front side plates, which are hinged to each other, are folded together to avoid the plates blocking the light-receiving surface of the solar array and affecting the efficiency of the solar array.

[0012] 2. This utility model removes the restriction of the telescopic spring rod on the long side plate, causing the telescopic spring rod to automatically extend and retract, while simultaneously driving the three sets of flexible solar array rolls to unfold. At the same time, it works in conjunction with three sets of torsion spring rods to pull the three sets of flexible solar array rolls, achieving the purpose of automatic extension of the solar array and reducing the overall weight of the satellite. Attached Figure Description

[0013] Figure 1 This is the front view of the present utility model.

[0014] Figure 2 This is a schematic diagram of the internal structure of this utility model.

[0015] Figure 3This is a schematic diagram of the unfolded shell of this utility model.

[0016] Figure 4 This is a schematic diagram of the outer shell of this utility model.

[0017] Figure 5 This is a schematic diagram of the unfolding device of this utility model.

[0018] Figure 6 This is a schematic diagram of the telescopic spring rod of this utility model.

[0019] Figure 7 This is a schematic diagram of the unfolded telescopic spring rod of this utility model.

[0020] Figure 8 This is a schematic diagram of the inner flexible solar panel roll of this utility model.

[0021] Figure 9 This is a schematic diagram of the torsion spring rod connection of this utility model.

[0022] Explanation of reference numerals in the attached figures:

[0023] 1. Shell; 11. Support body; 12. Long side plate; 13. Short side plate; 14. Lower side plate; 15. Front side plate; 2. Deployment device; 21. Telescopic spring rod; 211. Bottom support rod; 212. Internal spring rod; 213. Middle layer connecting rod; 214. Inner ring support rod; 215. Inner ring spring rod; 22. Inner ring flexible solar wing roll; 221. Solar wing support plate; 222. Flexible solar wing; 23. Middle ring flexible solar wing roll; 24. Outer ring flexible solar wing roll; 25. Front connecting rope; 26. Middle connecting rope; 27. Rear connecting rope; 28. Front torsion spring rod; 29. ​​Middle torsion spring rod; 210. Rear torsion spring rod. Detailed Implementation

[0024] Preferred embodiments of this utility model will be described in detail with reference to the accompanying drawings, which will make it easy for those skilled in the art to implement these embodiments. However, this utility model can also be implemented in various different forms, and therefore this utility model is not limited to the embodiments described below. In addition, for the purpose of more clearly describing this utility model, components not connected to this utility model will be omitted from the drawings.

[0025] like Figure 1 , 2 As shown, a fully deployable flexible solar array includes: a shell 1 and a deployment device 2;

[0026] like Figure 3 , 4 As shown, the housing 1 includes: a support body 11, a long side plate 12, a short side plate 13, a lower side plate 14, and a front side plate 15;

[0027] The supporting body 11 is located in the central area of ​​the device. The body is composed of a central square column and four plates, which are used to support the long side plate 12 and the lower side plate 14.

[0028] The long side plate 12 is located above the support body 11 and is hinged to each other by a spring shaft, serving as the upper end plate for forming a closed space;

[0029] The short side plate 13 is located on one side of the long side plate 12 and is hinged to each other by a spring shaft to form a side plate that encloses a space.

[0030] The front side plate 15 is located on the side of the long side plate 12 away from the supporting body 11 and is hinged to each other by a spring shaft to form a side plate that encloses a space.

[0031] The lower side plate 14 is located below the long side plate 12 and is hinged to each other by a spring shaft, serving as the lower end plate for forming a closed space;

[0032] like Figure 5 As shown, the deployment device 2 includes: a telescopic spring rod 21, an inner flexible solar wing roll 22, a middle flexible solar wing roll 23, an outer flexible solar wing roll 24, a front connecting rope 25, a middle connecting rope 26, a rear connecting rope 27, a front torsion spring rod 28, a middle torsion spring rod 29, and a rear torsion spring rod 210.

[0033] The telescopic spring rod 21 is located on one side of the long side plate 12 and is fixedly connected to each other. After the front side plate 15 is opened, the telescopic spring rod 21, which is no longer compressed, extends and drives the inner flexible solar panel roll 22 to expand outward.

[0034] The inner flexible solar wing roll 22 is located on the outer circumference of the telescopic spring rod 21 and is fixedly connected to each other. The inner flexible solar wing roll 22, the middle flexible solar wing roll 23, and the outer flexible solar wing roll 24 have the same structure and are fixedly connected by a connecting rod, which is used for fixing the flexible solar wing and supporting it after it is deployed.

[0035] The middle flexible solar wing roll 23 is located on the outer circumferential surface of the inner flexible solar wing roll 22 and is slidably connected to it. The rear end of the middle flexible solar wing roll 23 is fixedly connected to the middle layer connecting rod 213 for fixing the flexible solar wing and supporting it after deployment.

[0036] The outer flexible solar wing roll 24 is located on the outer periphery of the middle flexible solar wing roll 23 and is slidably connected to it. The rear end plate of the outer flexible solar wing roll 24 is fixedly connected to the support body 11, which is used for fixing and supporting the flexible solar wing after it is unfolded, and also supports the middle flexible solar wing roll 23.

[0037] The rear connecting rope 27 is located between the head of the outer flexible solar wing roll 24 and the front end of the rear torsion spring rod 210 and is fixedly connected to each other, and is used to transmit the torque of the rear torsion spring rod 210 itself.

[0038] The rear torsion spring rod 210 is located at one end of the rear connecting rope 27 and is fixedly connected to it. At the same time, the rear end of the rear torsion spring rod 210 is slidably connected to the support body 11. The rear torsion spring rod 210 is divided into a central fixed plate, a torsion spring, and an outer ring rotating plate. A long slider is provided on the outer ring sliding plate and is slidably connected to the groove on the support body 11. A groove is provided on the central fixed plate and is slidably connected to the outer ring slider of the central torsion spring rod 29. This is used to provide spring torque to pull the rear connecting rope 27 to pull and unfold the solar wings in the outer ring flexible solar wing roll 24.

[0039] The middle torsion spring rod 29 is located on the inner circumferential surface of the rear torsion spring rod 210 and is slidably connected to it. The middle torsion spring rod 29 is divided into a central fixed plate, a torsion spring, and an outer rotating ring plate. A long slider is provided on the outer ring slide plate and is slidably connected to the slide groove on the rear torsion spring rod 210. A slide groove is provided on the central fixed plate and is slidably connected to the outer ring slider of the front torsion spring rod 28. It is used to provide spring torque to pull the middle connecting rope 26 to pull and unfold the solar wing in the middle flexible solar wing roll 23.

[0040] The front torsion spring rod 28 is located on the inner circumferential surface of the middle torsion spring rod 29 and is slidably connected to it. The front torsion spring rod 28 is divided into a central fixed plate, a torsion spring, and an outer rotating ring plate. A long slider is set on the outer ring slide plate and is slidably connected to the slide groove on the middle torsion spring rod 29. A slider is set on the central fixed plate of the front torsion spring rod 28 and is slidably connected to the outer ring slide groove of the middle torsion spring rod 29. This is used to provide spring torque to pull the front connecting rope 25 to pull and unfold the solar wing in the inner flexible solar wing roll 22.

[0041] The central connecting rope 26 is located between the central torsion spring rod 29 and the central flexible solar panel roll 23, and is used to transmit the spring torque of the central torsion spring rod 29;

[0042] The front connecting rope 25 is located between the front torsion spring rod 28 and the inner flexible solar panel roll 22, and is used to transmit the spring torque of the front torsion spring rod 28.

[0043] like Figure 6 , 7 As shown, the telescopic spring rod 21 includes: a bottom support rod 211, an inner spring rod 212, a middle connecting rod 213, an inner ring support rod 214, and an inner ring spring rod 215;

[0044] The bottom support rod 211 is located on the support body 11 and is fixedly connected to each other. The outer peripheral surface of the bottom support rod 211 is provided with a sliding groove that is slidably connected to the slider on the inner spring rod 212 to support the inner spring rod 212.

[0045] The internal spring rod 212 is located inside the bottom support rod 211. The internal spring rod 212 consists of a support spring and a support rod. The support rod is supported by the spring provided in the bottom support rod 211. At the same time, a slider middle layer connecting rod 213 is provided on the outer circumference of the support rod to drive the middle layer connecting rod 213 to move.

[0046] The middle layer connecting rod 213 is located on the outer peripheral surface of the inner spring rod 212 and is fixedly connected to each other. At the same time, the outer peripheral surface of the middle layer connecting rod 213 is fixedly connected to the rear end of the middle ring flexible solar wing roll 23, which is used to drive the middle ring flexible solar wing roll 23 to expand outward.

[0047] The inner ring support rod 214 is located above the inner spring rod 212 and is fixedly connected to each other. At the same time, the inner ring support rod 214 passes through the top cover of the upper end of the inner spring rod 212 and is slidably connected to each other. A spring is provided inside the inner ring support rod 214 to support and control the inner ring spring rod 215.

[0048] The inner ring spring rod 215 is located inside the inner ring support rod 214, and the inner ring spring rod 215 is located above the spring of the inner ring support rod 214 and is fixedly connected to each other, which is used to drive the inner ring flexible solar panel roll 22 to lift.

[0049] like Figure 8 As shown, the inner flexible solar array roll 22 includes: solar array support plate 221 and flexible solar array 222;

[0050] The solar wing support plate 221 is located in the inner circle of the inner flexible solar wing roll 22. The solar wing support plate 221 is formed by a ring plate and a crossbar on one side. At the same time, the ring plate on the inner flexible solar wing roll 22 is slidably connected to the crossbar in the middle flexible solar wing roll 23, and the ring plate in the middle flexible solar wing roll 23 is slidably connected to the crossbar in the outer flexible solar wing roll 24, which is used to support the flexible solar wing 222.

[0051] The flexible solar array 222 is located on the outer ring of the solar array support plate 221. The flexible solar arrays are stacked and arranged so that the lifting front torsion spring rod 28 does not require any other external force when pulling the inner flexible solar array.

[0052] Working principle of this utility model:

[0053] During the deployment of the CubeSat, the thermal control blade first melts the thermal fuses between the four sets of lower side plates 14 and front side plates 15. The thermal fuses then melt and break, interrupting the connection between the lower side plates 14 and front side plates 15, releasing their mutual constraints. The lower side plate 14, hinged to the support body 11, rotates to be parallel to the support body 11. Simultaneously, the front side plate 15, hinged to the long side plate 12, rotates to one side of the long side plate 12, and the long side plate 12, hinged to the support body 11, rotates to a position parallel to the support body 11. Then, the thermal fuse between the long side plate 12 and the short side plate 13 melts. As the long side plate 12 becomes vertical, the short side plate 13, hinged to the long side plate 12, becomes parallel to the long side plate 12, completing the deployment of the shell 1. Then, the front side plate 15 releases its constraint on the telescopic spring rod 21, and the spring inside the bottom support rod 211 changes from a compressed state to a released state. The internal spring rod 212 and the inner ring support rod 214 expand outwards. At the same time, the spring inside the inner ring support rod 214 compresses the inner ring spring rod 215. When the internal spring rod 212 expands, it drives the middle ring flexible solar wing roll 23, which is fixedly connected to the middle layer connecting rod 213, to rise. Then, the inner ring spring rod 215 drives the inner ring flexible solar wing roll 22 to expand outwards. While the inner ring flexible solar wing roll 22 and the middle ring flexible solar wing roll 23 are expanding, the front connecting rope 25 and the middle connecting rope 26, which are connected to the inner ring flexible solar wing roll 22 and the middle ring flexible solar wing roll 23, drive the front torsion spring rod 28 and the middle torsion spring rod 29 to expand outwards. After the two sets of flexible solar wing rolls and the two sets of torsion spring rods have completed their expansion, the three sets of torsion spring rods are no longer restricted. The three sets of torsion spring rods release the pre-stored torque, which drives the connecting ropes to pull the three sets of flexible solar wing rolls to unfold, thus completing the unfolding of the solar wing.

Claims

1. A fully deployed flexible solar wing apparatus, characterized by, The utility model relates to a kind of solar wing deployment device, including: shell (1) and deployment device (2), shell (1) includes support body (11), long side plate (12), short side plate (13), lower side plate (14) and front side plate (15), long side plate (12) is hinged on support body (11) upper end by spring shaft, short side plate (13) is hinged on long side plate (12) one side by spring shaft, lower side plate (14) is hinged on long side plate (12) lower end by spring shaft, front side plate (15) is hinged on long side plate (12) side away from support body (11) by spring shaft, deployment device (2) includes telescopic spring rod (21), inner circle flexible solar wing roll (22), middle circle flexible solar wing roll (23), outer circle flexible solar wing roll (24), front connecting rope (25), middle connecting rope (26), rear connecting rope (27), front torsion spring rod (28), middle torsion spring rod (29) and rear torsion spring rod (210), telescopic spring rod (21) is fixed on long side plate (12) one side, inner circle flexible solar wing roll (22) is fixed on the outer peripheral surface of telescopic spring rod (21), middle circle flexible solar wing roll (23) is slidably connected on the outer peripheral surface of inner circle flexible solar wing roll (22), outer circle flexible solar wing roll (24) is slidably connected on the outer peripheral surface of middle circle flexible solar wing roll (23), front torsion spring rod (28) is nested in the inner peripheral surface of middle torsion spring rod (29), middle torsion spring rod (29) is nested in the inner peripheral surface of rear torsion spring rod (210), front connecting rope (25) both ends are fixed on the outer circle rotating ring plate of front torsion spring rod (28) and the head of inner circle flexible solar wing roll (22) respectively, middle connecting rope (26) both ends are fixed on the outer circle rotating ring plate of middle torsion spring rod (29) and the head of middle circle flexible solar wing roll (23) respectively, rear connecting rope (27) both ends are fixed on the outer circle rotating ring plate of rear torsion spring rod (210) and the head of outer circle flexible solar wing roll (24) respectively. The hinged place between long side plate (12) and short side plate (13), the hinged place between lower side plate (14) and front side plate (15) are each equipped with hot melting wire, and hot melting wire is fixed on the edge of adjacent plate face.

2. A fully deployable flexible solar wing apparatus as claimed in claim 1, wherein: Telescopic spring rod (21) includes bottom support rod (211), inner spring rod (212), middle layer connecting rod (213), inner circle support rod (214) and inner circle spring rod (215), bottom support rod (211) is fixed on support body (11), inner spring rod (212) is slidably connected in bottom support rod (211) inside, middle layer connecting rod (213) is fixed on the outer peripheral surface of inner spring rod (212) and is fixedly connected with the rear end of middle circle flexible solar wing roll (23), inner circle support rod (214) is slidably penetrated through the top cover of inner spring rod (212), and inner circle spring rod (215) is fixed in inner circle support rod (214) inside.

3. A fully deployable flexible solar wing apparatus as claimed in claim 1, wherein: ​ 4. A fully deployable flexible solar wing apparatus as claimed in claim 1, wherein: The outer ring rotating ring plate of the front torsion spring rod (28), the middle torsion spring rod (29) and the rear torsion spring rod (210) is provided with a long sliding block, the support body (11) is provided with a sliding groove matched with the long sliding block, the sliding groove of the front torsion spring rod (28) is in sliding connection with the sliding block of the middle torsion spring rod (29), and the sliding groove of the middle torsion spring rod (29) is in sliding connection with the sliding block of the rear torsion spring rod (210).

5. A fully deployable flexible solar wing apparatus as claimed in claim 1, wherein: The sun wing support plate (221) of the inner ring flexible sun wing roll (22), the middle ring flexible sun wing roll (23) and the outer ring flexible sun wing roll (24) is provided with a ring plate, and the ring plate is in sliding connection with the horizontal rod of the adjacent flexible sun wing roll through the horizontal rod.

6. A fully deployable flexible solar wing apparatus as claimed in claim 1, wherein: After the shell (1) is unfolded, the long side plate (12) is perpendicular to the support body (11), the short side plate (13) is parallel to the long side plate (12), and the lower side plate (14) and the front side plate (15) are coplanar at the bottom of the support body (11).

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