Adjustable solar wing unfolding device

Abstract

The utility model relates to the field of spacecrafts, in particular to an adjustable solar wing unfolding device which comprises a supporting shell and an unfolding device, the supporting shell comprises a main shell body and a penetrating opening, the main shell body is fixed outside a cubesat, the penetrating opening is formed in the peripheral face of the main shell body, and the unfolding device is arranged on the supporting shell body. The unfolding device comprises an external containing part, a solar wing part, a driving motor, a driving shaft, an adjusting rack, an adjusting gear shaft, a supporting ring, a supporting fixing ring and a main telescopic rod, the external containing part is fixed to the upper portion of the penetrating opening, and the external containing part comprises a containing shell, an extrusion spring plate, a partition plate, a solar wing plate and a connecting shaft; the solar wing plate is magnetically connected with the supporting and fixing ring through the connecting shaft, and the inclination angle of the solar wing plate is adjusted through the arrangement of the adjusting shaft and the adjusting gear shaft fixed on the solar wing.

Description

Technical Field

[0001] This utility model relates to the field of spacecraft, specifically to an adjustable solar array deployment device. Background Technology

[0002] As a core component of spacecraft energy supply, the deployment and angle control technology of CubeSat solar arrays directly affects the performance and lifespan of spacecraft. With the increasing complexity and diversification of space missions, the size and power requirements of solar arrays are constantly increasing, placing higher demands on their containment and deployment control. The containment issue mainly stems from space constraints during launch. Solar arrays must be folded and stored within a limited space during launch. This requires solar arrays to have a high containment ratio, meaning the ratio of their area in the deployed state to their volume in the folded state should be as large as possible. Traditional folding methods such as Z-folding and roll-up folding are no longer sufficient to meet the ever-increasing power demands, and new folding methods such as Miura origami and petal-shaped folding have become research hotspots. Furthermore, issues such as material stress and mechanical interference during folding must be considered to ensure the reliability and safety of the solar arrays during launch.

[0003] Angle control primarily involves the tracking accuracy of sunlight during the solar array's on-orbit operation. To improve solar energy utilization, the solar array needs to adjust its angle in real time to ensure it remains perpendicular to the sunlight. Traditional angle control methods use stepper motors or servo motors for driving, combined with sensors such as solar sensors to achieve closed-loop control. However, as the size of the solar array increases, its moment of inertia also increases, placing higher demands on the response speed and accuracy of the control system. Summary of the Invention

[0004] Therefore, this utility model is an adjustable solar array deployment device. Through the coordinated arrangement of the external housing, solar array, support ring, and support fixing ring, the solar array device can be driven to adjust the solar array surface according to actual conditions, meeting the requirements of solar array deployment surfaces for different CubeSats. The adjustment shaft and the adjustment gear shaft fixed on the solar array ensure the solar array area for receiving solar energy. This utility model achieves the above objectives through the following technical solutions:

[0005] An adjustable solar array deployment device includes: a support shell and a deployment device. The support shell includes a main shell and a through-hole. The main shell is fixed to the outside of a CubeSat, and the through-hole is opened on the outer periphery of the main shell. The deployment device includes an outer receiving part, a solar array part, a drive motor, a drive shaft, an adjusting rack, an adjusting gear shaft, a support ring, a support fixing ring, and a main telescopic rod. The outer receiving part is fixed above the through-hole and includes a receiving shell, a compression spring plate, a partition, a solar array plate, and a connecting shaft. The solar array plate is magnetically connected to the support fixing ring through the connecting shaft. The solar array part is located below the outer receiving part. Adjusting gear shafts are fixed on both sides of the solar array part. The adjusting gear shafts mesh with the adjusting rack. The drive motor drives the adjusting rack to translate through the drive shaft. The support ring is sleeved on the adjusting gear shaft and is linked to the support fixing ring through a telescopic connection device. The main telescopic rod drives the support fixing ring to translate synchronously with the support ring.

[0006] Preferably, the adjusting gear shaft is divided into two sections. One section is rotatably connected to the support ring, and the other section is provided with teeth that mesh with the adjusting rack. The solar panel is driven to rotate around the support ring by the translation of the adjusting rack.

[0007] Preferably, the inner ring of the support fixing ring is provided with a magnet, which cooperates with the magnet of the connecting shaft to be used for adsorption and fixation when the solar panel moves downward.

[0008] Preferably, the compression spring plate is located at the top of the housing, and the partitions are located on both sides of the compression spring plate.

[0009] Preferably, the external receiving portion is provided in four groups, located on the four outer surfaces of the main housing, and each group of external receiving portions is independently controlled.

[0010] Preferably, the telescopic connection device between the support ring and the support fixing ring is an electrically controlled telescopic rod, which synchronously adjusts the unfolded length of the support ring and the support fixing ring by driving the main telescopic rod.

[0011] The beneficial effects of this utility model are:

[0012] 1. This utility model, through the linkage of the external receiving part, the solar wing part, the support ring, and the support fixing ring, drives the solar wing device to set the solar wing plate surface according to the actual situation. At the same time, since the number and spatial position of the external receiving part can be adjusted, this solution only sets one external receiving part. According to the actual situation, multiple sets of external receiving parts can be set at multiple angles on the left, right, front and back to meet the needs of solar wing unfolding surface of different CubeSats.

[0013] 2. This utility model achieves the adjustment of the tilt angle of the solar panel by adjusting the shaft and the adjusting gear shaft fixed on the solar panel. Since the attitude of the CubeSat towards the sun and towards the earth needs to be adjusted in space, in order to ensure the area of ​​the solar panel that receives sunlight, the angle of the solar panel needs to be adjusted in real time to ensure the area of ​​the solar panel that receives solar energy. Attached Figure Description

[0014] Figure 1 This is the front view of the present utility model.

[0015] Figure 2 This is a schematic diagram of the support shell of this utility model.

[0016] Figure 3 This utility model Figure 2 -A enlarged view.

[0017] Figure 4 This is a schematic diagram of the unfolding device components of this utility model.

[0018] Figure 5 This is a schematic diagram of the external receiving part of this utility model.

[0019] Figure 6 This is a schematic diagram of the external receiving part of this utility model.

[0020] Figure 7 This utility model Figure 6 Enlarged view in -B.

[0021] Figure 8 This is a front view of the external receiving part of this utility model.

[0022] Figure 9 This is a side view of the external receiving part of this utility model.

[0023] Explanation of reference numerals in the attached figures:

[0024] 1. Support shell; 11. Main shell; 12. Through opening; 2. Deployment device; 21. External receiving part; 211. Receiving shell; 212. Compression spring plate; 213. Partition plate; 214. Solar wing plate; 215. Connecting shaft; 22. Solar wing part; 23. Drive motor; 24. Drive shaft; 25. Adjusting rack; 26. Adjusting gear shaft; 27. Support ring; 28. Support fixing ring; 29. ​​Main telescopic rod. Detailed Implementation

[0025] 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.

[0026] like Figure 1 As shown, an adjustable solar array deployment device includes: a support housing 1 and a deployment device 2;

[0027] like Figure 2 As shown, the supporting shell 1 includes: a main shell 11 and a through opening 12;

[0028] The main housing 11 is located outside the CubeSat and is used to support and accommodate the through-hole 12, the external accommodating part 21, the drive motor 23, the adjusting rack 25, the supporting fixing ring 28, and the main telescopic rod 29.

[0029] The through-hole 12 is located on the outer peripheral surface of the main housing 11 and penetrates the housing, and is used to accommodate the supporting adjustment rack 25 and the supporting fixing ring 28;

[0030] like Figure 3-7 As shown, the deployment device 2 includes: an outer housing 21, a solar panel 22, a drive motor 23, a drive shaft 24, an adjusting rack 25, an adjusting gear shaft 26, a support ring 27, and a support fixing ring 28.

[0031] The external receiving part 21 is located above the through opening 12 and is fixedly connected to the outer peripheral surface of the main shell 11. Four sets of external receiving parts 21 are provided on the four sides of the main shell 11 to accommodate other solar panel surfaces.

[0032] The solar wing 22 is located below the outer housing 21. The solar wing 22 is supported and its spatial position is adjusted by adjusting the gear shaft 26, and it is used to receive solar energy.

[0033] The adjusting gear shaft 26 is located on the left and right sides of the solar wing 22 and is fixedly connected to each other. The adjusting gear shaft 26 is divided into two parts: one part is rotatably connected to the support ring 27, and the other part is provided with a gear shaft to support the adjusting solar wing 22.

[0034] The support rings 27 are nested on the adjusting gear shaft 26. The support rings 27 are divided into multiple groups, and a telescopic connection device is provided between the support rings 27. The support ring 27 is composed of a circular ring and an electrically controlled telescopic rod. The spatial position of the support ring 27 is adjusted by driving the electrically controlled telescopic rod.

[0035] The support fixing ring 28 is located on the side of the support ring 27 near the main housing 11 and is connected by a telescopic rod. It has the same function as the support ring 27. The support fixing ring 28 is divided into multiple groups, and each group is connected by a telescopic connecting device. The inner ring of the support fixing ring 28 is provided with a magnet, which attracts the inner ring magnet of the connecting shaft 215 to support the solar panel 214 in the outer housing 21.

[0036] The main telescopic rod 29 is located above the support fixing ring 28 and is fixedly connected to each other. One end of the main telescopic rod 29 is fixedly connected to the inner wall of the main housing 11, and the other end is fixedly connected to the end of the support fixing ring 28 near the drive shaft 24, which is used to drive the support fixing ring 28 and the support ring 27 to translate together.

[0037] The adjusting rack 25 is located below the adjusting gear shaft 26 and meshes with it. The adjusting rack 25 is driven to translate by the drive shaft 24, thereby driving the adjusting gear shaft 26. The angle of the solar panel 22 is driven by the driving adjusting gear shaft 26.

[0038] The drive shaft 24 is located above the adjusting rack 25 and meshes with it, and is used to drive the adjusting rack 25.

[0039] The drive motor 23 is located on one side of the drive shaft 24 and is fixedly connected to the inner wall of the main housing 11, and is used to drive the drive shaft 24 to rotate.

[0040] like Figure 8 , 9 As shown, the external receiving part 21 includes: a receiving housing 211, a compression spring plate 212, a partition 213, a solar panel 214, and a connecting shaft 215;

[0041] The housing 211 is located on the outer peripheral surface of the main housing 11 and is fixedly connected to each other, and is used to accommodate the supporting compression spring plate 212, partition 213, and solar panel 214.

[0042] The compression spring plate 212 is located in the center area of ​​the top plate of the housing 211. When the solar wing portion 22 below the solar wing plate 214 has not left, the solar wing plate 214 compresses the compression spring plate 212. When the solar wing portion 22 leaves, the compression spring plate 212 releases pressure and drives the solar wing plate 214 to move down. Then the connecting shaft 215 and the support fixing ring 28 attract each other to provide support.

[0043] The partition 213 is located on both sides of the compression spring plate 212 and is fixedly connected to the top plate of the housing 211. It is used to separate the distance between the solar panels 214 and ensure that the solar panels 214 correspond one-to-one with the support fixing rings 28 when they fall.

[0044] The solar panel 214 is located below the partition 213 and is used to provide an additional solar panel surface;

[0045] The connecting shaft 215 is located on the left and right sides of the solar panel 214 and is fixedly connected to each other. The side of the connecting shaft 215 closest to the solar panel 214 is magnetic and attracts each other with the magnetism on the support fixing ring 28.

[0046] Working principle of this utility model:

[0047] In the CubeSat solar wing deployment device 2, firstly, the main telescopic rod 29 drives the support fixing ring 28 and the support ring 27 to translate together, while simultaneously driving the drive motor 23 to rotate the drive shaft 24. The rotating drive shaft 24 drives the adjusting rack 25 to move forward, ensuring that the spatial position of the solar wing 22 remains constant when it moves forward. Then, after the solar wing 22 completely leaves the solar wing plate 214, the spring plate 212 is compressed to release pressure and drive the solar wing plate 214 to move downward. Then, the connecting shaft 215 and the support fixing ring 28 attract each other, and at the same time, the front end of the connecting shaft 215... Partially engaged with the adjusting rack 25, after the supporting fixing ring 28 and the supporting ring 27 are fully extended, the telescopic device on the supporting fixing ring 28 and the supporting ring 27 is driven to unfold. At the same time as unfolding, the drive motor 23 continuously drives the drive shaft 24 to rotate, keeping the solar wing 22 and the solar wing plate 214 in a vertical state. After the supporting fixing ring 28 and the supporting ring 27 are fully extended, the driving adjusting rack 25 controls the solar wing 22 and the solar wing plate 214 so that the solar wing 22 and the solar wing plate 214 can have an optimal angle to the sun, thus completing the unfolding of the solar wing.

Claims

1. An adjustable solar wing deployment device, characterized by, The utility model relates to a kind of solar wing deployment device, including: Support shell (1) and deployment device (2), support shell (1) includes main shell (11) and through port (12), main shell (11) is fixed to the outside of cube star, through port (12) is opened in the outer peripheral surface of main shell (11), deployment device (2) includes external container (21), solar wing part (22), drive motor (23), drive shaft (24), adjusting rack (25), adjusting pinion (26), support ring (27), support fixed ring (28) and main telescopic rod (29), external container (21) is fixed above through port (12), external container (21) includes containing shell (211), extrusion spring plate (212), partition (213), solar wing plate (214) and connecting shaft (215), solar wing plate (214) is magnetically connected with support fixed ring (28) by connecting shaft (215), solar wing part (22) is below external container (21), adjusting pinion (26) is fixed on the both sides of solar wing part (22), adjusting pinion (26) is engaged with adjusting rack (25), drive motor (23) drives adjusting rack (25) to translate by drive shaft (24), support ring (27) is sleeved on adjusting pinion (26), and support fixed ring (28) is linked by telescopic connecting device, main telescopic rod (29) drives support fixed ring (28) and support ring (27) synchronous translation.

2. An adjustable solar wing deployment device according to claim 1, wherein: Adjusting pinion (26) is divided into two sections, one section is rotatably connected with support ring (27), and the other section is provided with tooth portion engaged with adjusting rack (25), and solar wing part (22) is driven to rotate around support ring (27) by the translation of adjusting rack (25).

3. An adjustable solar wing deployment device according to claim 1, wherein: The inner ring of the support fixed ring (28) is provided with a magnet that cooperates with the magnet of the connecting shaft (215) to absorb and fix the solar wing plate (214) when it moves downward.

4. An adjustable solar wing deployment device according to claim 1, wherein: The extrusion spring plate (212) is arranged on the top of the containing shell (211), and the partition (213) is located on both sides of the extrusion spring plate (212).

5. An adjustable solar wing deployment device according to claim 1, wherein: The external container (21) is provided with four groups, which are respectively located on the four outer surfaces of the main shell (11), and each group of external containers (21) is independently controlled.

6. An adjustable solar wing deployment device according to claim 1, wherein: The telescopic connecting device between the support ring (27) and the support fixed ring (28) is an electric telescopic rod that synchronously adjusts the deployment length of the support ring (27) and the support fixed ring (28) by the drive of the main telescopic rod (29).

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