Mechanical separation nut assembly for satellite sailboard

Abstract

The utility model discloses a satellite sailboard mechanical separation nut assembly which comprises a base and a separation column, a through hole is formed in the top wall of the base, the separation column penetrates through the through hole to enter the base, a clamping mechanism is arranged in the base, and the clamping mechanism can clamp and fix the separation column. The structural design is miniaturized and light, the operation is stable, and the unfolding efficiency and reliability of the sailboard are improved.

Description

Technical Field

[0001] The utility model relates to the technical field of spacecraft, in particular to a satellite sailboard mechanical separation nut assembly. Background Art

[0002] With the rapid development of aerospace technology, satellites are becoming increasingly diverse in their functionality and increasingly reliant on solar panels. However, traditional solar panel deployment mechanisms are bulky, complex, heavy, and lack reliability, limiting the flexibility of satellite design and the stability of on-orbit operations. Utility Model Content

[0003] In response to the defects in the existing technology, the utility model provides a satellite sailboard mechanical separation nut assembly. The structural design is miniaturized and lightweight, and the operation is stable, which improves the efficiency and reliability of sailboard deployment.

[0004] A satellite sailboard mechanical separation nut assembly includes a base and a separation column. The top wall of the base is provided with a through hole, and the separation column passes through the through hole into the base. A clamping mechanism is provided in the base, and the clamping mechanism can clamp and fix the separation column.

[0005] Preferably, the clamping mechanism includes a first clamp and a second clamp, a fixed shaft is provided in the base, the first clamp and the second clamp are both rotatably provided on the fixed shaft, a torsion spring is provided on the fixed shaft, the two ends of the torsion spring are respectively connected to the first clamp and the second clamp, and a limiting mechanism is provided on the first clamp, and the limiting mechanism can fix the first clamp and the second clamp when the first clamp and the second clamp clamp the separation column.

[0006] Preferably, the limiting mechanism includes a controller, a driving mechanism and a limiting column. The controller is connected to the driving mechanism, and the driving mechanism is connected to the limiting column. A limiting slot is provided on the second clamp, and the controller can control the driving mechanism to drive the limiting column to disengage from the limiting slot.

[0007] Preferably, a compression spring is provided in the base, and when the first clamp and the second clamp clamp the separation column, the first clamp and the second clamp contact both ends of the compression spring to compress the compression spring.

[0008] Preferably, a mounting post is further included, wherein the mounting post has a through hole, and the compression spring passes through the through hole.

[0009] Preferably, a compression spring fixing wire is further included. A screw hole is opened on the bottom wall of the mounting column. The compression spring fixing wire passes through the screw hole and enters the through hole to be pressed against the compression spring.

[0010] Preferably, an annular groove is provided on the separation column, and the clamping mechanism can be clamped on the annular groove.

[0011] Preferably, it also includes a sleeve, two first plates are connected to the first clamp, two second plates are connected to the second clamp, the first plates and the second plates are both sleeved on the fixed shaft, the two second plates are located between the two first plates, the sleeve is sleeved on the fixed shaft, the top wall of the upper first plate contacts the inner top wall of the base, the bottom wall of the lower first plate contacts the sleeve, the bottom wall of the sleeve contacts the inner bottom wall of the base, the top wall of the upper second plate contacts the bottom wall of the upper first plate, and the bottom wall of the lower second plate contacts the top wall of the lower first plate.

[0012] The beneficial effects of this utility model are embodied in the following aspects: in this technical solution, a through hole is provided in the top wall of the base, through which a separation column passes into the base, a spring is connected between the separation column and the solar panel, and a clamping mechanism is provided in the base. In the normal state, the clamping mechanism clamps and secures the separation column. When the solar panel needs to be released, the satellite sends a signal, the clamping mechanism releases the clamping mechanism, and the spring between the separation column and the solar panel is used to release the separation column from the base, thereby achieving the deployment of the solar panel. This structure can be miniaturized, lightweight, and stable in operation, improving the efficiency and reliability of panel deployment, effectively reducing the overall weight of the satellite and improving launch efficiency.

[0013] This technical solution utilizes precisely designed torsion springs, compression springs, and a limiting mechanism. Simple mechanical manipulation and remote control commands trigger the limiting post to move out of the limiting slot, allowing the separation post to detach from the base. This ensures the panel remains stable and secure even under severe vibration and acceleration, enabling effective deployment and ensuring smooth, stable operation even in harsh aerospace environments. This structure also simplifies operation and reduces maintenance. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly describes the drawings required for the specific embodiments or the description of the prior art. Similar elements or parts are generally identified by similar reference numerals throughout the drawings. Elements or parts in the drawings are not necessarily drawn to scale.

[0015] Figure 1 It is a schematic diagram of the overall structure of the utility model;

[0016] Figure 2 This is a structural diagram of the utility model in which the base and the separation column are separated;

[0017] Figure 3 It is an exploded schematic diagram of the overall structure of the utility model.

[0018] In the accompanying drawings, 1-base, 2-sleeve, 3-torsion spring, 4-compression spring, 5-compression spring fixing wire, 6-first clamp, 7-second clamp, 8-separation column, 9-mounting column, 10-through hole, 11-limiting groove, 12-through hole, 13-annular groove, 14-first set of plates, 15-second set of plates. DETAILED DESCRIPTION

[0019] The following embodiments of the technical solution of the present invention are described in detail with reference to the accompanying drawings. The following embodiments are only used to more clearly illustrate the technical solution of the present invention and are therefore only examples and are not intended to limit the scope of protection of the present invention.

[0020] It should be noted that, unless otherwise specified, the technical terms or scientific terms used in this application should have the common meanings understood by those skilled in the art to which this utility model belongs.

[0021] Example 1

[0022] like Figure 1-Figure 3 As shown, this embodiment provides a satellite sailboard mechanical separation nut assembly, including a base 1 and a separation column 8. The top wall of the base 1 is provided with a through hole 10, and the separation column 8 passes through the through hole 10 into the base 1. A clamping mechanism is provided in the base 1, and the clamping mechanism can clamp and fix the separation column 8.

[0023] In this embodiment, a through hole 10 is provided on the top wall of the base 1, through which the separation column 8 passes into the base 1. A spring is connected between the separation column 8 and the solar panel, and a clamping mechanism is provided within the base 1. In a normal state, the clamping mechanism clamps and secures the separation column 8. When the solar panel needs to be released, the satellite sends a signal, and the clamping mechanism releases the clamping mechanism from the separation column 8. The spring between the separation column 8 and the solar panel allows the separation column 8 to be separated from the base 1, thereby achieving the deployment of the solar panel. This structure can be miniaturized, lightweight, and stable in operation, improving the efficiency and reliability of panel deployment, effectively reducing the overall weight of the satellite and improving launch efficiency.

[0024] In this embodiment, the base 1 is made of lightweight and high-strength material to reduce the overall weight and protect the internal structure.

[0025] The clamping mechanism described in this embodiment includes a first clamp 6 and a second clamp 7. A fixed shaft is provided in the base 1. The first clamp 6 and the second clamp 7 are both rotatably provided on the fixed shaft. A torsion spring 3 is sleeved on the fixed shaft. The two ends of the torsion spring 3 are respectively connected to the first clamp 6 and the second clamp 7. A limiting mechanism is provided on the first clamp 6. The limiting mechanism can fix the first clamp 6 and the second clamp 7 when the first clamp 6 and the second clamp 7 clamp the separation column 8.

[0026] The limiting mechanism described in this embodiment includes a controller, a driving mechanism and a limiting column. The controller is connected to the driving mechanism, and the driving mechanism is connected to the limiting column. A limiting slot 11 is provided on the second clamp 7. The controller can control the driving mechanism to drive the limiting column to disengage from the limiting slot 11.

[0027] In the normal state, the limit post enters the limit slot 11, and the first clamp 6 and the second clamp 7 clamp the separation post 8. When the solar panel is released, the satellite sends a signal to the controller, which controls the drive mechanism to operate, and the drive mechanism drives the limit post to move, so that the limit post leaves the limit slot 11. At this time, the elastic restoring force of the torsion spring 3 causes the first clamp 6 and the second clamp 7 to move in opposite directions, releasing the clamp on the separation post 8. In this way, through simple mechanical operation and remote control commands, the limit post can be triggered to leave the limit slot 11, so that the separation post 8 can be separated from the base 1, thereby allowing the solar panel to be smoothly deployed.

[0028] In this embodiment, the driving mechanism may be a component such as a cylinder.

[0029] In this embodiment, a compression spring 4 is provided within the base 1. When the first and second clamps 6 and 7 clamp the separation post 8, the first and second clamps 6 and 7 contact the ends of the compression spring 4, compressing the compression spring 4. In this embodiment, the compression spring 4 is provided. When the first and second clamps 6 and 7 clamp the separation post 8, the compression spring 4 is compressed. After the limiting post leaves the limiting slot 11, the elastic restoring force of the compression spring 4, combined with the elastic restoring force of the torsion spring 3, facilitates the separation of the first and second clamps 6 and 7.

[0030] This embodiment utilizes precisely designed torsion springs 3, compression springs 4, and a limiting mechanism to ensure the stable positioning of the sailboard even under severe vibration and acceleration changes, enabling effective deployment and ensuring smooth deployment and stable operation even in harsh aerospace environments. This structure also simplifies operation and reduces maintenance.

[0031] This embodiment also includes a mounting post 9 having a through-hole, through which the compression spring 4 passes. This embodiment also includes a compression spring fixing wire 5. The bottom wall of the mounting post 9 has a screw hole, through which the compression spring fixing wire 5 passes and enters the through-hole 12, where it is tightened against the compression spring 4. In this embodiment, the mounting post 9 and the compression spring fixing wire 5 cooperate to secure the compression spring 4.

[0032] In this embodiment, an annular groove 13 is formed on the separation column 8 , and the clamping mechanism can be clamped on the annular groove 13 .

[0033] This embodiment also includes a sleeve 2, two first plates 14 are connected to the first clamp 6, and two second plates 15 are connected to the second clamp 7. The first plates 14 and the second plates 15 are both sleeved on the fixed shaft, and the two second plates 15 are located between the two first plates 14. The sleeve 2 is sleeved on the fixed shaft, the top wall of the upper first plate 14 contacts the inner top wall of the base 1, the bottom wall of the lower first plate contacts the sleeve 2, the bottom wall of the sleeve 2 contacts the inner bottom wall of the base 1, the top wall of the upper second plate 15 contacts the bottom wall of the upper first plate 14, and the bottom wall of the lower second plate 15 contacts the top wall of the lower first plate 14.

[0034] In this embodiment, the shaft sleeve 2, two first plates 14, and two second plates 15 cooperate with the fixed shaft to achieve the rotational arrangement of the first clamp 6 and the second clamp 7. The shaft sleeve 2 cooperates with the inner top wall of the base 1 to limit the upper and lower positions of the first clamp 6 and the second clamp 7. Specifically, the torsion spring 3 is disposed between the two second plates 15.

[0035] In order to achieve the goals of small size, simple structure and durability, the mechanical properties of the materials and the feasibility of the processing technology are fully considered in the design. All structures are made of high-strength and corrosion-resistant materials and have undergone rigorous testing and verification to ensure their reliability.

[0036] The application of this structure helps to improve the satellite's energy supply capability and on-orbit operation stability, thereby extending the satellite's service life and improving its overall performance.

[0037] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the above embodiments, or make equivalent replacements for some or all of the technical features therein. These modifications or replacements do not deviate the essence of the corresponding technical solutions from the scope of the technical solutions of the embodiments of the present invention, and they should all be included in the scope of the claims and description of the present invention.

Claims

1. A satellite sailboard mechanical separation nut assembly, characterized in that: The invention comprises a base (1) and a separation column (8); a through hole (10) is opened on the top wall of the base (1); the separation column (8) passes through the through hole (10) and enters the base (1); a clamping mechanism is provided in the base (1); the clamping mechanism can clamp and fix the separation column (8).

2. The satellite sailboard mechanical separation nut assembly according to claim 1, characterized in that: The clamping mechanism comprises a first clamp (6) and a second clamp (7); a fixed shaft is provided in the base (1); the first clamp (6) and the second clamp (7) are both rotatably provided on the fixed shaft; a torsion spring (3) is sleeved on the fixed shaft; the two ends of the torsion spring (3) are respectively connected to the first clamp (6) and the second clamp (7); a limiting mechanism is provided on the first clamp (6); the limiting mechanism can fix the first clamp (6) and the second clamp (7) when the first clamp (6) and the second clamp (7) clamp the separation column (8).

3. The satellite sailboard mechanical separation nut assembly according to claim 2, characterized in that: The limiting mechanism comprises a controller, a driving mechanism and a limiting column, the controller is connected to the driving mechanism, the driving mechanism is connected to the limiting column, a limiting slot (11) is provided on the second clamp (7), and the controller can control the driving mechanism to drive the limiting column to disengage from the limiting slot (11).

4. The satellite sailboard mechanical separation nut assembly according to claim 2, characterized in that: A compression spring (4) is provided in the base (1); when the first clamp (6) and the second clamp (7) clamp the separation column (8), the first clamp (6) and the second clamp (7) contact both ends of the compression spring (4) to compress the compression spring (4).

5. The satellite sailboard mechanical separation nut assembly according to claim 4, characterized in that: It also includes a mounting post (9), the mounting post (9) has a through hole, and the compression spring (4) passes through the through hole (12).

6. The satellite sailboard mechanical separation nut assembly according to claim 5, characterized in that: It also includes a compression spring fixing wire (5), the bottom wall of the installation column (9) is provided with a screw hole, and the compression spring fixing wire (5) passes through the screw hole and enters the through hole (12) to press against the compression spring (4).

7. The satellite sailboard mechanical separation nut assembly according to claim 1, characterized in that: An annular groove (13) is formed on the separation column (8), and the clamping mechanism can be clamped on the annular groove (13).

8. The satellite sailboard mechanical separation nut assembly according to claim 2, characterized in that: The invention also includes a shaft sleeve (2), two first sets of plates (14) are connected to the first clamp (6), and two second sets of plates (15) are connected to the second clamp (7), the first sets of plates (14) and the second sets of plates (15) are both sleeved on the fixed shaft, and the two second sets of plates (15) are located between the two first sets of plates (14), the shaft sleeve (2) is sleeved on the fixed shaft, the top wall of the upper first set of plates (14) contacts the inner top wall of the base (1), the bottom wall of the lower first set of plates contacts the shaft sleeve (2), the bottom wall of the shaft sleeve (2) contacts the inner bottom wall of the base (1), the top wall of the upper second set of plates (15) contacts the bottom wall of the upper first set of plates (14), and the bottom wall of the lower second set of plates (15) contacts the top wall of the lower first set of plates (14).

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