Locking device suitable for body-attached type cubesat solar wing

Abstract

The utility model relates to the technical field of cubesat energy, in particular to a locking device suitable for a body-attached type cubesat solar wing, which comprises a female chain, a male chain, a connecting shaft and a control part, the end part of the male chain is symmetrically provided with two through connecting holes II, and the end part of the male chain is provided with symmetrical connecting blocks II; the end face of the second connecting block is provided with a through connecting shaft hole, the end face of the left connecting shaft hole is provided with a through fixing groove, the connecting shaft is slidably arranged in the connecting shaft hole, one end of the connecting shaft is provided with a limiting column, one side of the limiting column is provided with a limiting strip, and the limiting strip is slidably arranged in the fixing groove. According to the solar wing unfolding mechanism, the movable connecting shaft and the electromagnetic control technology are adopted, and unfolding of the solar wing within the range of 0 degree to 90 degrees and the range of 0 degree to 180 degrees can be achieved.

Description

Technical Field

[0001] This utility model relates to the field of CubeSat energy technology, specifically to a locking device suitable for the solar wings of a cubitus-type CubeSat. Background Technology

[0002] Currently, CubeSat technology is developing rapidly, making remote measurement and experimentation via CubeSats possible. Power supply plays a crucial role in CubeSat operation, and solar arrays are its primary energy source. Solar arrays convert sunlight into electricity, powering various payloads on the CubeSat and charging its batteries to ensure normal operation even when it enters shadowed regions. Therefore, solar arrays are of paramount importance to CubeSats. However, the relatively small size and limited surface area of ​​CubeSats directly limit the size of solar arrays, resulting in insufficient power supply and restricting the number of payloads that can be carried. To overcome this bottleneck, researchers have meticulously designed deployable solar arrays.

[0003] In existing patents, the main challenge in designing deployable solar arrays lies in the hinge design of the deployment mechanism. The solar wings of a CubeSat are connected to the celestial body via a hinge structure, allowing the solar wings to rotate relative to the celestial body and deploy in 0°-90° or 90°-180° configurations. Existing hinges can only achieve a single mode of movement and cannot achieve 0°-90° or 0°-180° deployment. Summary of the Invention

[0004] Therefore, this utility model was made in view of the above problems. This utility model uses a movable connecting shaft and, through electromagnetic control, enables the solar panel to unfold at angles of 0°-90° and 0°-180°, making the hinge more versatile.

[0005] A locking device suitable for a cuboidal solar array includes: a mother chain, a male chain, a connecting shaft, and a control unit. The male chain has two symmetrically arranged through-holes at its end and two symmetrical connecting blocks at its end. Each connecting block has a through-hole on its end face and a through-groove on its left side. The connecting shaft is slidably disposed within the connecting shaft hole. One end of the connecting shaft has a limiting post, and one side of the limiting post has a limiting strip that slidably disposes within the fixing groove. The mother chain is rotatably mounted on the connecting shaft and located between the two connecting blocks. The mother chain has symmetrically arranged through-holes and connecting blocks at its end. Each connecting block has a mating hole on its end face and four symmetrical limiting grooves on its left side. The control unit includes an electromagnet, a spring, and a fixing ring. The electromagnet is sleeved on the connecting shaft and fixed to the right end face of the connecting block of the male chain. The fixing ring is fixed to the right end of the connecting shaft. The spring is sleeved on the connecting shaft and located between the electromagnet and the fixing ring.

[0006] Preferably, the limiting post and the limiting strip of the connecting shaft are integrally formed, and the cross-sectional shape of the limiting strip is adapted to the cross-sectional shape of the fixing groove.

[0007] Preferably, the limiting groove of the mother chain is a rectangular groove, evenly distributed along the circumference, and corresponds to the sliding trajectory of the limiting strip.

[0008] Preferably, the mother chain is fixedly connected to the solar array substrate, and the male chain is fixedly connected to the CubeSat body.

[0009] Preferably, the spring is a compression spring, and its preload is greater than the residual magnetic force when the electromagnet is de-energized.

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

[0011] 1. This utility model employs a movable connecting shaft and electromagnetic control technology, enabling the solar array to deploy within the range of 0°-90° and 0°-180°. This design overcomes the limitations of traditional hinges, allowing the solar array to flexibly adjust its angle according to different mission requirements and orbital environments, significantly improving the adaptability of the hinge and better meeting the energy needs of CubeSats in diverse missions;

[0012] 2. This invention achieves precise deployment and angle adjustment of the solar array via electromagnetic control, ensuring that the solar array always faces the sunlight during operation, maximizing the absorption and conversion efficiency of solar energy. 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

[0013] Figure 1 This is a schematic diagram of the overall structure of this utility model.

[0014] Figure 2 This is an exploded view of the present invention.

[0015] Figure 3 This is a schematic diagram of the motion state of the present invention. Figure 1 .

[0016] Figure 4 This is a schematic diagram of the motion state of the present invention. Figure 2 .

[0017] Figure 5 This is a schematic diagram of the motion state of the present invention. Figure 3 .

[0018] Figure 6 This is a schematic diagram of the motion state of the present invention. Figure 4 .

[0019] Explanation of reference numerals in the attached figures:

[0020] 1. Female chain; 101. Connecting hole one; 102. Connecting block one; 103. Mating hole; 104. Limiting groove; 2. Male chain; 201. Connecting hole two; 202. Connecting block two; 203. Connecting shaft hole; 204. Fixing groove; 3. Connecting shaft; 301. Limiting post; 302. Limiting strip; 4. Control unit; 41. Electromagnet; 42. Spring; 43. Fixing ring. Detailed Implementation

[0021] 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.

[0022] like Figure 1 , 2 As shown, a locking device suitable for a cubitrary CubeSat solar array includes: a mother chain 1, a male chain 2, a connecting shaft 3, and a control unit 4.

[0023] The public chain 2 is the supporting component of the entire structure;

[0024] The end face of the public chain 2 is symmetrically provided with two through connection holes 201;

[0025] The end of the public chain 2 is connected by two symmetrical connecting blocks 202.

[0026] The end face of the second connecting block 202 is provided with a through connecting shaft hole 203;

[0027] The end face of the connecting shaft hole 203 located on the left side of the public chain 2 is provided with a through fixing groove 204;

[0028] The connecting shaft 3 is slidably disposed within the connecting shaft hole 203;

[0029] The end of the connecting shaft 3 is provided with a limiting post 301;

[0030] A limiting strip 302 is provided at the end of the connecting shaft 3 and at the position connected to the limiting post 301. The limiting strip 302 is slidably disposed in the fixing groove 204.

[0031] The mother chain 1 is rotatably mounted on the connecting shaft 3 and located between the two connecting blocks 202;

[0032] The end face of the mother chain 1 is provided with two symmetrical connection holes 101;

[0033] The end of the mother chain 1 is connected by two symmetrical connecting blocks 102;

[0034] The end face of the connecting block 102 is provided with a through mating hole 103;

[0035] The end face of the connecting block 102 located to the left of the connecting hole 101 is provided with four symmetrical limiting grooves 104;

[0036] The control unit 4 is fixedly mounted on the connecting shaft 3;

[0037] The control unit 4 includes: an electromagnet 41, a spring 42, and a retaining ring 43;

[0038] The electromagnet 41 is sleeved on the connecting shaft 3 and fixedly installed on the right end face of the connecting block 202 of the public chain 2;

[0039] The fixing ring 43 is fixedly installed at the right end of the connecting shaft 3;

[0040] The spring 42 is sleeved on the connecting shaft 3 and is located between the electromagnet 41 and the fixed ring 43. The spring 42 is a compression spring, and its preload is greater than the residual magnetic force when the electromagnet 41 is de-energized, ensuring that the connecting shaft 3 is reset when there is no electromagnetic effect.

[0041] Working principle of this utility model:

[0042] The initial state of the entire device is as follows Figure 3 or Figure 4 As shown, the CubeSat's body-mounted solar panel substrate has two states. When the CubeSat needs to deploy the solar panel, firstly, the electromagnet 41 attracts the fixing ring 43, and the connecting shaft 3 slides synchronously within the mating hole 103 along with the fixing ring 43. At this time, the device is... Figure 3 The motion state shown moves to, as Figure 6As shown in the motion state, the limiting bar 302 disengages from the limiting groove 104. At this time, the solar array rotates, causing the main chain 1 to flip. When the entire device moves to the position shown in the figure, the limiting bar 302 disengages from the limiting groove 104. Figure 4 or Figure 5 When the motion state shown is completed, the adjustment of the mother chain 1 is completed, and the mother chain 1 and the male chain 2 can be fixed. At this time, the electromagnet 41 stops, the fixing ring 43 is reset under the action of the spring 42, the connecting shaft 3 is also reset at the same time, and the limiting strip 302 slides into the limiting groove 104 to fix the limiting groove 104. At this time, the motion process of the entire device is completed.

Claims

1. A locking device suitable for a cuboidal solar array, characterized in that, include: The system comprises a mother chain (1), a male chain (2), a connecting shaft (3), and a control unit (4). The male chain (2) has two symmetrically arranged through-holes (201) at its end, and two symmetrical connecting blocks (202) at its end. Each connecting block (202) has a through-hole (203) on its end face, and a through-groove (204) on the end face of the left connecting shaft hole (203). The connecting shaft (3) is slidably disposed within the connecting shaft hole (203). One end of the connecting shaft (3) has a limiting post (301), and one side of the limiting post (301) has a limiting strip (302). The limiting strip (302) is slidably disposed within the fixing groove (204). The mother chain (1) is rotatably disposed within the connecting shaft hole (204). The shaft (3) is located between two connecting blocks (202). The end of the mother chain (1) is symmetrically provided with a connecting hole (101) and a connecting block (102). The end face of the connecting block (102) is provided with a mating hole (103). The end face of the left connecting block (102) is provided with four symmetrical limiting grooves (104). The control unit (4) includes an electromagnet (41), a spring (42) and a fixing ring (43). The electromagnet (41) is sleeved on the connecting shaft (3) and fixed to the right end face of the connecting block (202) of the male chain (2). The fixing ring (43) is fixed to the right end of the connecting shaft (3). The spring (42) is sleeved on the connecting shaft (3) and located between the electromagnet (41) and the fixing ring (43).

2. A locking device suitable for a cuboidal solar array according to claim 1, characterized in that: The limiting post (301) and the limiting strip (302) of the connecting shaft (3) are integrally formed, and the cross-sectional shape of the limiting strip (302) is adapted to the cross-sectional shape of the fixing groove (204).

3. A locking device suitable for a cuboidal solar array according to claim 1, characterized in that: The limiting groove (104) of the mother chain (1) is a rectangular groove, which is evenly distributed along the circumference and corresponds to the sliding trajectory of the limiting strip (302).

4. A locking device for a cuboidal solar array according to claim 1, characterized in that: The mother chain (1) is fixedly connected to the solar panel substrate, and the male chain (2) is fixedly connected to the CubeSat body.

5. A locking device for a cuboidal solar array according to claim 1, characterized in that: The spring (42) is a compression spring, and its preload is greater than the residual magnetic force of the electromagnet (41) when it is de-energized.

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