Locking device for multi-angle solar wing

Abstract

The utility model relates to the technical field of cubesat energy, in particular to a locking device of a multi-angle solar wing, which comprises a female chain, a male chain, a connecting shaft, a torsion spring and a control part, the end part of the female chain is symmetrically provided with a positioning hole and a positioning seat, the positioning seat on one side is provided with a fixing hole, and the positioning seat on the other side is provided with a matching hole; a limiting strip is arranged on the inner circumferential face of the matching hole, a mounting hole and a mounting base are symmetrically arranged at the end of the male chain, a mounting base hole is formed in the end face of the mounting base, a positioning ring is arranged in the mounting base hole in one side, a first limiting wheel is arranged on the end face of the mounting base on the other side, and a connecting shaft is rotationally arranged in a fixing hole; according to the utility model, the flexible unfolding of the solar wing in the range of 0-90 degrees and 0-180 degrees is realized through the slidable moving cylinder and the electromagnetic control technology.

Description

Technical Field

[0001] This utility model relates to the field of CubeSat energy technology, specifically to a locking device for a multi-angle solar array. Background Technology

[0002] In recent years, with the rapid development of CubeSat technology, remote measurement and experimentation using CubeSats has gradually become a reality. Power is one of the key energy sources for CubeSats, with solar arrays being their primary energy source. Solar arrays convert sunlight into electricity to power the CubeSat's payload equipment and charge its batteries, maintaining normal operation during shadow periods. Therefore, solar arrays play a crucial role in CubeSats. However, due to the small size and limited surface area of ​​CubeSats, the area of ​​the solar array is also limited, resulting in insufficient power supply and thus limiting the payload capacity that CubeSats can carry. To address this issue, researchers have designed deployable solar arrays.

[0003] In existing deployable solar array technologies, the hinge design of the deployment mechanism is a key challenge. Specifically, the solar array of a CubeSat is connected to the celestial body via a hinge structure, enabling the solar array to rotate relative to the celestial body and complete deployment movements from 0° to 90° or from 90° to 180°. However, current hinge designs can only support a single movement mode and cannot achieve flexible deployment at multiple angles, which to some extent limits the flexibility and adaptability of the solar array. Summary of the Invention

[0004] Therefore, this utility model was made in view of the above problems. This utility model uses a sliding movable cylinder and electromagnetic control to realize the unfolding of the solar panel angle from 0° to 90° and from 0° to 180°, making the hinge more versatile.

[0005] A locking device for a multi-angle solar panel includes: a female chain, a male chain, a connecting shaft, a torsion spring, and a control unit. The female chain has symmetrically arranged positioning holes and positioning seats at its ends. One side of the positioning seat has a fixing hole, and the other side has a mating hole. A limiting strip is provided on the inner circumferential surface of the mating hole. The male chain has symmetrically arranged mounting holes and mounting seats at its ends. The end face of the mounting seat has a mounting seat hole. One side of the mounting seat hole has a positioning ring, and the end face of the other mounting seat has a limiting wheel. The connecting shaft is rotatably mounted within the fixing hole. One end of the connecting shaft is provided with a limiting post, and the outer circumferential surface of the connecting shaft is provided with a limiting groove. A torsion spring is sleeved on the connecting shaft, one end of the torsion spring is fixed to the limiting post, and the other end of the torsion spring is fixed to the mounting base. The control unit includes an electromagnet, a moving cylinder, and a spring. The electromagnet is fixed to one end of the connecting shaft. The moving cylinder is slidably disposed in the mating hole. The outer circumferential surface of the moving cylinder is provided with a positioning groove that mates with the limiting strip. The end of the moving cylinder is provided with a magnetic ring and a limiting wheel. The spring is sleeved on the connecting shaft, and the two ends of the spring are respectively fixed to the electromagnet and the magnetic ring.

[0006] Preferably, the first limiting wheel and the second limiting wheel are gear structures with a number of teeth or an adjustable number to adapt to different locking angle requirements.

[0007] Preferably, the cross-sectional shape of the positioning groove is adapted to the limiting strip to ensure the guiding accuracy when the moving cylinder slides along the axial direction.

[0008] Preferably, the spring is a compression spring, and its preload is greater than the residual magnetic force when the electromagnet is de-energized.

[0009] Preferably, the mother chain is fixedly connected to the CubeSat body, and the male chain is fixedly connected to the solar array substrate.

[0010] Preferably, the limiting groove and the positioning ring cooperate to limit the rotation range of the male chain, and the mating surfaces of the limiting groove and the positioning ring are provided with a wear-resistant coating.

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

[0012] 1. This utility model achieves flexible deployment of the solar array within the range of 0°-90° and 0°-180° through a sliding movable cylinder and electromagnetic control technology. This design breaks through the limitations of traditional hinges, allowing the solar array to flexibly adjust its deployment angle according to different mission requirements and orbital environments, thereby better adapting to diverse application scenarios and significantly improving the applicability of the hinge and the utilization efficiency of the solar array;

[0013] 2. Electromagnetic control enables precise deployment and angle adjustment of the solar array, ensuring it always faces sunlight during operation and maximizing solar energy absorption and conversion efficiency. Simultaneously, the precision and reliability of electromagnetic control reduce the risk of mechanical failures during deployment, improving the overall performance and stability of the solar array deployment system and providing strong support for the long-term stable operation of the CubeSat. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the overall structure of this utility model.

[0015] Figure 2 This is an exploded view of the present invention.

[0016] Figure 3 This is a partial enlarged view of the present invention.

[0017] Figure 4 This is a schematic diagram of the overall structure of the movable cylinder of this utility model.

[0018] Figure 5 This is a schematic diagram of the motion state of the present invention. Figure 1 .

[0019] Figure 6 This is a schematic diagram of the motion state of the present invention. Figure 2 .

[0020] Figure 7 This is a schematic diagram of the motion state of the present invention. Figure 3 .

[0021] Explanation of reference numerals in the attached figures:

[0022] 1. Female chain; 101. Positioning hole; 102. Positioning seat; 103. Fixing hole; 104. Mating hole; 105. Limiting strip; 2. Male chain; 201. Mounting hole; 202. Mounting seat; 203. Mounting seat hole; 204. Positioning ring; 205. Limiting wheel one; 3. Connecting shaft; 301. Limiting post; 302. Limiting groove; 4. Torsion spring; 5. Control unit; 51. Electromagnet; 52. Moving cylinder; 521. Magnetic ring; 522. Positioning groove; Limiting wheel two; 523. Limiting wheel two; 53. Spring. Detailed Implementation

[0023] 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, parts not connected to the utility model will be omitted from the drawings.

[0024] like Figure 1 , 2 The locking device for a multi-angle solar panel shown includes: a female chain 1, a male chain 2, a connecting shaft 3, a torsion spring 4, and a control unit 5;

[0025] The main chain 1 is the supporting component of the entire structure;

[0026] The end face of the mother chain 1 is symmetrically provided with two through connection holes and positioning holes 101.

[0027] The end of the mother chain 1 is supported by two symmetrical positioning seats 102;

[0028] The end face of the right positioning seat 102 is provided with a fixing hole 103, and the end face of the other positioning seat 102 is provided with a mating hole 104, and the mating hole 104 and the fixing hole 103 are concentrically arranged.

[0029] A limiting strip 105 is provided on the inner circumferential surface of the fitting hole 104;

[0030] The connecting shaft 3 is rotatably disposed within the connecting fixing hole 103;

[0031] The end of the connecting shaft 3 is provided with a limiting post 301, which is rotatably disposed outside the fixing hole 103;

[0032] The outer circumferential surface of the connecting shaft 3 is provided with a limiting groove 302;

[0033] The public chain 2 is rotatably mounted on the connecting shaft 3 and located between the two positioning seats 102;

[0034] The end face of the public chain 2 is provided with two symmetrical connection holes and a mounting hole 201, which is used to fix and connect the solar panel substrate.

[0035] The end of the public chain 2 is supported by two symmetrical mounting bases 202, and the center of the end face of the mounting base 202 is provided with a through mounting base hole 203;

[0036] A positioning ring 204 is provided on the inner circumferential surface of the mounting hole 203 on the right side. The positioning ring 204 is rotatably disposed in the limiting groove 302. The mating surface between the limiting groove 302 and the positioning ring 204 is provided with a wear-resistant coating to reduce wear during long-term use.

[0037] On the other side, the mounting base 202 end face is provided with a limiting wheel 205. The number of teeth of the limiting wheel 205 can be set as needed to lock at multiple angles. This utility model is provided with four gears, but is not limited to four.

[0038] The torsion spring 4 is sleeved on the connecting shaft 3. One end of the torsion spring 4 is fixedly connected to the side of the limiting post 301, and the other end is fixedly set on the side of the mounting base 202. When the entire device is located in Figure 1 In the motion state shown, the torsion spring 4 has a directional force. Figure 7 The motion state shown indicates the trend of motion;

[0039] The control unit 5 is fixedly mounted on the connecting shaft 3;

[0040] The control unit 5 includes: an electromagnet 51, a moving cylinder 52, and a spring 53;

[0041] The electromagnet 51 is fixedly mounted at the other end of the connecting shaft 3;

[0042] The movable cylinder 52 is slidably disposed within the mating hole 104;

[0043] like Figure 4 As shown, a magnetic ring 521 is provided at the end of the movable cylinder 52;

[0044] The outer circumferential surface of the movable cylinder 52 is provided with a positioning groove 522, which is slidably disposed on the limiting strip 105 to limit the entire movable cylinder 52.

[0045] The other end of the movable cylinder 52 is provided with a second limiting wheel 523 corresponding to the first limiting wheel 205;

[0046] The spring 53 is sleeved on the connecting shaft 3, and one end of the spring 53 is fixedly set on the end face of the electromagnet 51, and the other end is fixedly set on the end face of the magnetic ring 521. The spring 53 is a compression spring, and its preload is greater than the residual magnetic force when the electromagnet 51 is de-energized, ensuring that the moving cylinder 52 resets when there is no electromagnetic effect.

[0047] Working principle of this utility model:

[0048] The initial state of the entire device is as follows Figure 1 As shown, when the CubeSat needs to deploy its solar array 4, firstly, the electromagnet 51 is activated. The electromagnet 51 attracts the moving cylinder 52, which moves along the mating hole 104. At this time, the moving cylinder 52 is disengaged from the control of the limit wheel 205, and the entire movement process of the device is... Figure 1 The motion state shown moves to, as Figure 5 The motion state shown;

[0049] Secondly, under the action of the torsion spring 4, the male chain 2 flips relative to the female chain 1. At the same time, the electromagnet 51 is closed, and the moving cylinder 52 is reset under the action of the spring 53, re-limiting the limiting wheel 205 of the male chain 2. At this time, the motion state of the entire device changes from... Figure 5 The motion state shown moves to, as Figure 6 The movement state shown can be used to lock the position from 0° to 90°.

[0050] If a 0°-180° locking is required, electromagnet 51 can be activated again. Electromagnet 51 attracts the moving cylinder 52, causing it to move along the mating hole 104. At this time, the moving cylinder 52 disengages from the control of the limiting wheel 205, and the male chain 2 flips relative to the female chain 1 under the action of the torsion spring 4. Simultaneously, electromagnet 51 is deactivated, and the moving cylinder 52 resets under the action of the spring 53, re-limiting the limiting wheel 205 of the male chain 2. The motion state of the entire device then changes from... Figure 6 The motion state shown moves to, as Figure 7 The motion state shown;

[0051] The above describes the movement flow of the locking device from 0° to 90° and from 0° to 180°. If other angles are required, the number of teeth on the first limiting wheel 205 and the second limiting wheel 523 can be adjusted to complete the movement flow of the entire device.

Claims

1. A locking device for a multi-angle solar wing, characterized in that The utility model relates to a kind of locking mechanism of cubic star, including: female chain (1), male chain (2), connecting shaft (3), torsion spring (4) and control part (5), the end of female chain (1) is symmetrically provided with positioning hole (101) and positioning seat (102), one side positioning seat (102) is provided with fixed hole (103), the other side positioning seat (102) is provided with cooperation hole (104), the inner circumferential surface of the cooperation hole (104) is provided with limit strip (105), the end of male chain (2) is symmetrically provided with mounting hole (201) and mounting seat (202), the end surface of the mounting seat (202) is provided with mounting seat hole (203), one side mounting seat hole (203) is provided with positioning ring (204) inside, the end surface of the other side mounting seat (202) is provided with limit wheel one (205), connecting shaft (3) is rotationally arranged in fixed hole (103), one end of connecting shaft (3) is provided with limit post (301), the outer circumferential surface of connecting shaft (3) is provided with limit groove (302), torsion spring (4) is sleeved on connecting shaft (3), one end of torsion spring (4) is fixed to limit post (301), the other end of torsion spring (4) is fixed to mounting seat (202), control part (5) includes electromagnet (51), moving cylinder (52) and spring (53), electromagnet (51) is fixed to one end of connecting shaft (3), moving cylinder (52) is slidably arranged in cooperation hole (104), the outer circumferential surface of moving cylinder (52) is provided with positioning groove (522) cooperating with limit strip (105), the end of moving cylinder (52) is provided with magnetic ring (521) and limit wheel two (523);Spring (53) is sleeved on connecting shaft (3), and both ends of spring (53) are fixed to electromagnet (51) and magnetic ring (521) respectively. The limit wheel one (205) and limit wheel two (523) are gear structures, with 4 or adjustable number of teeth to adapt to different locking angle requirements.

2. A locking device for a multi-angle solar wing according to claim 1, characterized in that: The cross-sectional shape of the positioning groove (522) is adapted to the limit strip (105), ensuring the guiding accuracy of the moving cylinder (52) when sliding axially.

3. The locking device of a multi-angle solar wing according to claim 1, characterized in that: The spring (53) is a compression spring, and its pre-tightening force is greater than the residual magnetic force of the electromagnet (51) when it is powered off.

4. The locking device of a multi-angle solar wing according to claim 1, characterized in that: The female chain (1) is fixedly connected with the cubic star body, and the male chain (2) is fixedly connected with the solar wing base plate.

5. The locking device of a multi-angle solar wing according to claim 1, characterized in that: The limit groove (302) cooperates with the positioning ring (204) to limit the rotation range of the male chain (2), and the cooperation surface of the limit groove (302) and the positioning ring (204) is provided with a wear-resistant coating.

6. The locking device of a multi-angle solar wing according to claim 1, characterized in that: ​

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