Satellite module quick docking and separation structure and use method

Abstract

The present invention discloses a satellite module rapid docking and separation structure and a method of use, comprising a mother body and a daughter body, the mother body being provided with a transfer block 1, a magnet array, a heating plate and a positioning bolt, the transfer block 1 being provided with a truncated cone-shaped groove 1 at one end close to the daughter body, the narrower end of the groove 1 being provided with a rectangular parallelepiped-shaped groove 2, the heating plate and the magnet array being embedded in the groove 2. In the present invention, the rapid docking and separation structure has low production cost, simple structure, short cycle, and can be mass-produced; it has high reliability, strong bearing capacity, and low energy consumption; through the docking and separation between the mother body and the daughter body, the docking and separation speed of the structure is fast, the assembly efficiency is high, and it can be repeatedly and quickly disassembled; it can meet the docking and separation, assembly, transportation, testing and other process requirements of various products, facilities and instruments in space, at sea and on land, and has a wide range of uses; the magnetic array structure adopts a matrix-free design and will not produce magnetic effects on surrounding components.

Description

Technical Field

[0001] The present invention relates to the field of electromagnetic connection technology, and in particular to a satellite module rapid docking and separation structure and a use method thereof. Background Art

[0002] Satellites typically adhere to a one-satellite-one-design principle during the design, production, assembly, and testing stages. Each component, module, and interface has its own unique installation method. Even for two or more satellites with the same design, the interface design of the entire satellite or its components often struggles to accommodate rapid assembly during assembly. The interface between the payload and the satellite's cabin often utilizes screw connections. First, the payload is positioned in the mounting configuration through locating holes, and then screws are installed through multiple mounting holes. This is especially true for large payloads, and assembly time between the payload and the entire satellite can take upwards of two days, leading to excessively long satellite production cycles. With the rapid development of aerospace technology in recent years, the number of mass-produced satellites, such as Starlink and constellation satellites, has increased, leading to an increasing number of spacecraft rendezvous and docking missions. Universal docking and separation methods struggle to meet the rapid integration requirements of mass-produced satellites.

[0003] Currently, research at home and abroad is focused on electromagnetic docking in space. Limited research exists on the ground assembly phase of satellites, and most utilize electromagnetic coils, which are complex, have limited load-bearing capacity, and consume a lot of energy. Given the short production cycles, low costs, and high volume of mass-produced satellites, it is imperative to break away from traditional satellite interface configurations and break through existing assembly technologies to improve assembly efficiency and reduce assembly time. Therefore, considering the requirements for rapid satellite assembly and separation, combined with the satellite's need for environmental adaptability, a technology for rapid satellite module docking and separation is urgently needed. Summary of the Invention

[0004] The purpose of the present invention is to solve the above problems and to propose a satellite module rapid docking and separation structure and a method of use.

[0005] In order to achieve the above object, the present invention adopts the following technical solutions:

[0006] A satellite module rapid docking and separation structure comprises a mother body and a daughter body. The mother body is provided with a first adapter block, a magnet array, a heating plate, and a positioning bolt. The first adapter block has a first truncated cone-shaped groove at one end near the daughter body, and a second rectangular parallelepiped groove at the narrower end of the first groove. The heating plate and the magnet array are embedded in the second groove. The positioning bolt is located at the end of the first adapter block near the daughter body.

[0007] The sub-body is provided with a transfer block 2 and an iron-nickel block. The transfer block 2 is in the shape of a truncated cone on the side close to the mother body, which matches the groove 1. The transfer block 2 is in the shape of a cylinder on the side away from the mother body. The transfer block 2 is provided with a rectangular groove 3 on the end close to the mother body, and the iron-nickel block is embedded in the groove 3.

[0008] Preferably, the magnet array is provided with five rectangular parallelepiped magnetic blocks, the five magnetic blocks are in the same orientation and bonded sequentially from left to right, and the magnetization directions of the five magnetic blocks are top, left, bottom, right, and top from left to right.

[0009] Preferably, the mother body is connected to the satellite via a first adapter block, and the daughter body is connected to the docking module via a second adapter block.

[0010] Preferably, the heating sheet is made of a thin sheet of material with heat conduction function, one side of the heating sheet is bonded to the magnet array, and the other side is passed with current.

[0011] Preferably, the iron-nickel block is made of an alloy material made of iron and nickel and has magnetic properties.

[0012] Preferably, the method for using the quick docking and separation structure comprises the following steps:

[0013] S1, connecting the adapter block 1 of the mother body to the satellite, with the groove 1 facing the daughter body, and connecting the adapter block 2 of the daughter body to the docking module, with the side embedded with the iron-nickel block facing the mother body;

[0014] S2, open the positioning bolt on the mother body, align the end of the child body close to the mother body with the groove on the mother body, and after the mother body and the child body are attracted and closed, close the positioning bolt on the mother body to complete the docking;

[0015] S3. Utilize the heating plate on the mother body to heat the magnet array, and open the positioning bolt at the same time. When the magnet array is heated to a predetermined temperature, the magnetic attraction is lost, and the daughter body automatically falls off, completing the separation.

[0016] In summary, due to the adoption of the above technical solution, the beneficial effects of the present invention are:

[0017] 1. The rapid docking and separation structure of the present application has low production cost, simple structure, short cycle, and can be mass-produced; it has high reliability, strong bearing capacity, and low energy consumption; through the docking and separation between the parent body and the child body, the docking and separation speed of the present structure is fast, the assembly efficiency is high, and it can be repeatedly and quickly disassembled; it can meet the needs of docking and separation, assembly, transportation, testing and other processes of various products, facilities and instruments in space, at sea and on land, and has a wide range of uses; the present application adopts a magnetic array structure with no matrix design, which will not produce magnetic effects on surrounding components. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 A schematic diagram of the main structure of a satellite module rapid docking and separation structure provided in accordance with an embodiment of the present invention is shown;

[0019] Figure 2 A schematic structural diagram of a magnet array provided according to an embodiment of the present invention is shown.

[0020] Legend:

[0021] 1. Adapter block 1; 2. Magnet array; 3. Heating plate; 4. Positioning bolt; 5. Adapter block 2; 6. Iron-nickel block; 7. Groove 1; 8. Groove 2; 9. Groove 3. DETAILED DESCRIPTION

[0022] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making any creative efforts shall fall within the scope of protection of the present invention.

[0023] See also Figure 1-2 , the present invention provides a technical solution:

[0024] A satellite module rapid docking and separation structure includes a mother body and a daughter body. The mother body is provided with a transfer block 1, a magnet array 2, a heating plate 3, and a positioning bolt 4. The end of the transfer block 1 near the daughter body is provided with a truncated cone-shaped groove 7, and the narrower end of the groove 7 is provided with a rectangular parallelepiped groove 2 8. The heating plate 3 and the magnet array 2 are embedded in the groove 2 8. The positioning bolt 4 is located at the end of the transfer block 1 near the daughter body. The positioning bolt 4 is made of a relatively rigid material and is used to prevent the mother body and daughter body from falling off after docking.

[0025] The sub-body is provided with a transfer block 2 5 and an iron-nickel block 6. The transfer block 2 5 is in the shape of a truncated cone on the side close to the mother body, which matches the groove 1 7. The transfer block 2 5 is in the shape of a cylinder on the side away from the mother body. The diameter of one end of the cylinder is smaller than the diameter of the large circular surface of the truncated cone, which is conducive to the installation of the mother body positioning bolt 4. The transfer block 2 5 is provided with a rectangular groove 3 9 on the end close to the mother body, and the iron-nickel block 6 is embedded in the groove 3 9.

[0026] Specifically, such as Figure 2 As shown, the magnet array 2 is provided with five rectangular parallelepiped magnetic blocks, which are in the same orientation and bonded sequentially from left to right. The magnetization directions of the five magnetic blocks are top, left, bottom, right, and top from left to right.

[0027] Specifically, such as Figure 1 and Figure 2As shown, the mother body is connected to the satellite through the adapter block 1, and the daughter body is connected to the docking module through the adapter block 2 5; the shape of the adapter block 1 can be customized as needed, and is generally a rectangular parallelepiped;

[0028] The heating sheet 3 is made of a thin sheet of material with heat conduction function. One side of the heating sheet 3 is bonded to the magnet array 2, and the other side is passed with current.

[0029] The iron-nickel block 6 is made of an alloy material of iron and nickel and has magnetic attraction;

[0030] The method for using the quick docking and separation structure includes the following steps:

[0031] S1. Connect the mother body's adapter block 1 to the satellite, with the groove 7 facing the daughter body, and connect the daughter body's adapter block 2 5 to the docking module, with the side inlaid with the iron-nickel block 6 facing the mother body;

[0032] S2. Open the positioning bolt 4 on the parent body, and dock the end of the child body close to the parent body with the groove 7 on the parent body. After the parent body and the child body are attracted and closed, close the positioning bolt 7 on the parent body to complete the docking;

[0033] S3. Use the heating plate 3 on the mother body to heat the magnet array 2, and open the positioning bolt 7 at the same time. When the magnet array 2 is heated to a predetermined temperature, the magnetic attraction is lost, and the daughter body automatically falls off, completing the separation.

[0034] The rapid docking and separation structure of the present application has low production cost, simple structure, short cycle, and can be mass-produced; it has high reliability, strong bearing capacity, and low energy consumption; through the docking and separation between the parent body and the child body, the docking and separation speed of the present structure is fast, the assembly efficiency is high, and it can be repeatedly and quickly disassembled; it can meet the needs of docking and separation, assembly, transportation, testing and other processes of various products, facilities and instruments in space, at sea and on land, and has a wide range of uses; the present application adopts a magnetic array structure with no matrix design, which will not produce magnetic effects on surrounding components.

[0035] The above description of the embodiments is intended to enable one skilled in the art to implement or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention is not limited to the embodiments shown herein but is intended to conform to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A satellite module rapid docking and separation structure, characterized in that: The invention comprises a mother body and a daughter body, wherein the mother body is provided with a transfer block 1 (1), a magnet array (2), a heating plate (3) and a positioning bolt (4); the transfer block 1 (1) is provided with a truncated cone-shaped groove 1 (7) at one end close to the daughter body, and the narrower end of the groove 1 (7) is provided with a rectangular parallelepiped-shaped groove 2 (8); the heating plate (3) and the magnet array (2) are embedded in the groove 2 (8); and the positioning bolt (4) is located at the end of the transfer block 1 (1) close to the daughter body; The sub-body is provided with a transfer block 2 (5) and an iron-nickel block (6). The transfer block 2 (5) is in a truncated cone shape on the side close to the mother body and matches the groove 1 (7). The transfer block 2 (5) is in a cylindrical shape on the side away from the mother body. The transfer block 2 (5) is provided with a rectangular groove 3 (9) on one end close to the mother body, and the iron-nickel block (6) is embedded in the groove 3 (9). The magnet array (2) is provided with five rectangular parallelepiped magnetic blocks, the five magnetic blocks are in the same orientation and bonded sequentially from left to right, and the magnetization directions of the five magnetic blocks are top, left, bottom, right, and top sequentially from left to right.

2. A satellite module rapid docking and separation structure according to claim 1, characterized in that: The mother body is connected to the satellite via the adapter block 1 (1), and the daughter body is connected to the docking module via the adapter block 2 (5).

3. The satellite module rapid docking and separation structure according to claim 1, characterized in that: The heating sheet (3) is made of a thin sheet of material with heat conduction function. One side of the heating sheet (3) is bonded to the magnet array (2), and the other side is passed with current.

4. The satellite module rapid docking and separation structure according to claim 1, characterized in that: The iron-nickel block (6) is made of an alloy material of iron and nickel and has magnetic attraction.

5. The satellite module rapid docking and separation structure according to claim 1, characterized in that: The method for using the quick docking and separation structure comprises the following steps: S1. Connect the adapter block 1 (1) of the mother body to the satellite, with the groove 1 (7) facing the daughter body, and connect the adapter block 2 (5) of the daughter body to the docking module, with the side inlaid with the iron-nickel block (6) facing the mother body; S2, open the positioning bolt (4) on the mother body, dock the end of the child body close to the mother body with the groove (7) on the mother body, and after the mother body and the child body are attracted and closed, close the positioning bolt (4) on the mother body to complete the docking; S3. Utilize the heating plate (3) on the mother body to heat the magnet array (2), and simultaneously open the positioning bolt (4). When the magnet array (2) is heated to a predetermined temperature, the magnetic attraction is lost, and the daughter body automatically falls off, completing the separation.

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