Floating connector for on-orbit docking of satellites

Abstract

The application discloses a floating connector for satellite on-orbit docking, and relates to the technical field of connectors. The floating connector comprises a plug module and a socket module. The plug module and the socket module are respectively arranged at the docking positions of two satellites for docking. The plug module comprises a mounting base fixed on a satellite and a floating plug movably arranged on the mounting base. A limiting assembly for limiting the movement of the floating plug is arranged on the mounting base. The socket module comprises a shell fixed on a satellite and a connecting socket fixed in the shell. A docking port for the floating plug to enter is arranged on the shell. A plurality of correction blocks are arranged on the shell and distributed along the circumference of the docking port. A driving assembly for driving the correction blocks to simultaneously slide in the direction of approaching or moving away from each other is arranged on the shell. The application has the effect that when the on-orbit docking of the satellites deviates and is within a certain deviation range, the plug and the socket of the connector can still be accurately plugged.

Description

Technical Field

[0001] This application relates to the technical field of connectors, and in particular to a floating connector for satellite on-orbit docking. Background Technology

[0002] A space satellite is an artificial satellite that orbits the Earth in space. Its main working environment is in outer space. Artificial satellites generally orbit the Earth according to the laws of celestial mechanics. As the most numerous, widely used, and fastest-growing spacecraft, artificial satellites can be mainly divided into three categories: scientific satellites, technological experimental satellites, and application satellites. Their functions include space physics exploration satellites and astronomical satellites, which are used to study the atmosphere, radiation belts, magnetosphere, cosmic rays, and solar radiation of a planet, and can also be used to observe other celestial bodies.

[0003] The use of space satellites has a certain periodicity. Under normal circumstances, some spacecraft, even when their main structure and components can still work normally after completing their scheduled missions or reaching the end of their lifespan, often become space debris or are left to crash due to a lack of functional expansion and subsequent maintenance. In order to reduce launch costs, satellites are gradually developing towards miniaturization and modularization, while introducing on-orbit service technology to realize subsequent maintenance work.

[0004] Currently, when maintaining and servicing satellites in orbit, it is necessary to send the satellite for maintenance and servicing into outer space and dock it with the satellite in orbit that needs maintenance, thereby enabling electrical transmission between small satellites. At present, the connectors used in satellite docking ports mainly adopt a combination of plug and socket. However, satellites in different orbits are affected by the non-spherical gravitational field of the Earth, atmospheric drag, solar gravity, lunar gravity, and light pressure, and their actual motion is very complex. During docking, satellites are very prone to deviation, which can cause the plug and socket of the connector to fail to fit accurately. At this time, it is necessary to continuously adjust the relative position between the two satellites, resulting in a large amount of satellite fuel consumption. Summary of the Invention

[0005] To address the problems existing in the prior art, this application provides a floating connector for satellite on-orbit docking, which can still achieve accurate mating of the connector plug and socket when there is a deviation in the on-orbit docking of the satellite, but within a certain deviation range.

[0006] This application provides a floating connector for satellite on-orbit docking, which adopts the following technical solution:

[0007] A floating connector for satellite on-orbit docking includes a plug module and a socket module, which are respectively installed at the docking positions of two satellites for docking. The plug module includes a mounting base fixedly mounted on the satellite and a floating plug movably mounted on the mounting base. The mounting base is provided with a limiting component for restricting the movement of the floating plug. The socket module includes a housing fixedly mounted on the satellite and a connecting socket fixedly mounted inside the housing. The housing has a mating interface for the floating plug to enter, and the floating plug is adapted to the connecting socket. Multiple calibration blocks are distributed on the housing and along the circumference of the mating interface. Each calibration block is slidably engaged with the housing. The housing is provided with a driving component for driving each calibration block to slide simultaneously in a direction that moves closer to or further away from each other.

[0008] By adopting the above technical solution, during satellite docking, the floating plug is first inserted into the docking interface of the housing. Then, the driving component drives the calibration blocks to move closer to each other, thereby correcting the position of the floating plug so that it is aligned with the connector socket. After that, the limiting component restricts the movement of the floating plug. As the two satellites dock, the floating plug is inserted into the connector socket. Thus, even if there is a deviation in the on-orbit docking of the satellites, but it is within a certain deviation range, the floating plug of the connector and the connector socket can still be accurately engaged without readjusting the relative position between the two satellites, thereby avoiding a large amount of satellite fuel consumption.

[0009] Optionally, a mounting ring is rotatably mounted on the mounting base, a connecting rod is fixedly mounted inside the mounting ring, a mounting block is slidably mounted on the connecting rod along its length, the floating plug is mounted on the mounting block, and the rotation axis of the mounting ring is parallel to the length direction of the floating plug, while the length direction of the connecting rod is perpendicular to the length direction of the floating plug.

[0010] Optionally, a reset spring is provided inside the mounting ring, one end of which is fixedly connected to the inner wall of the mounting ring, and the other end of which is fixedly connected to the mounting block.

[0011] Optionally, a rubber sealing sleeve is fixedly provided inside the mounting ring, the mounting block penetrates the rubber sealing sleeve, and the mounting block is fixedly connected to the rubber sealing sleeve.

[0012] Optionally, a telescopic rod is slidably disposed on the mounting block along the length direction of the floating plug, the floating plug is fixedly disposed on the telescopic rod, and a first elastic element is disposed on the mounting block for driving the telescopic rod to slide away from the mounting base.

[0013] By adopting the above technical solution, in addition to misalignment during satellite docking, the angles of the two satellites will also deviate to a certain extent. As the two satellites dock, their angles will gradually be corrected. Through the setting of the telescopic rod and the first elastic element, when the angle of the two satellites deviates, the telescopic rod will slide on the mounting block and compress the first elastic element during the insertion of the floating plug into the connector socket due to the reverse thrust of the connector socket. After the relative angle between the two satellites is corrected, the floating plug will be inserted into the connector socket under the elastic force of the first elastic element. This effectively avoids the floating plug from deforming during the docking of the two satellites, which would prevent the floating plug from being inserted into the connector socket smoothly.

[0014] Optionally, the limiting component includes a friction disc slidably disposed on the mounting base and a first driving member for driving the friction disc to slide, wherein the mounting block is provided with a friction surface and the friction disc is used to abut against the friction surface on the mounting block.

[0015] Optionally, the driving assembly includes a limiting sleeve, a second elastic element, and a second driving element. The limiting sleeve is slidably sleeved on the housing. Multiple guide slopes are provided on the inner sidewall of the limiting sleeve. Each guide slope corresponds to a correction block, and each guide slope gradually approaches the correction block away from the correction block. Multiple second elastic elements are provided and correspond to the correction blocks one by one. The second elastic elements are used to drive the corresponding correction blocks to slide away from the housing. The second driving element is used to drive the limiting sleeve to slide.

[0016] Optionally, each of the correction blocks is rotatably provided with a roller at one end that is far apart from each other. The roller is used to abut against the corresponding guide slope and roll in connection with the guide slope.

[0017] Optionally, each of the calibration blocks has a ball bearing rotatably mounted at one end that is close to the other. The ball bearing is used to abut against the floating plug and to be rotatably connected to the floating plug.

[0018] Optionally, the sidewall of the floating plug is provided with a socket for inserting a calibration block along the circumference of the floating plug.

[0019] In summary, this application includes at least one of the following beneficial technical effects:

[0020] 1. During satellite docking, the floating plug is first inserted into the docking interface of the housing. Then, the drive component drives the calibration blocks to move closer to each other, thereby correcting the position of the floating plug so that it is aligned with the connector socket. After that, the limit component restricts the movement of the floating plug. As the two satellites dock, the floating plug is inserted into the connector socket. Thus, even if there is a deviation in the on-orbit docking of the satellites, as long as it is within a certain deviation range, the floating plug of the connector can still accurately engage with the connector socket without having to readjust the relative position between the two satellites, thereby avoiding a large amount of satellite fuel consumption.

[0021] 2. During satellite docking, in addition to misalignment, the angles of the two satellites may also deviate. These angles are gradually corrected as the satellites dock. Through the telescopic rod and the first elastic element, when the satellite angles shift, the telescopic rod, under the reverse thrust of the connector, slides on the mounting block and compresses the first elastic element during insertion of the floating plug into the connector socket. Once the relative angle between the two satellites is corrected, the floating plug inserts into the connector socket under the elastic force of the first elastic element. This effectively prevents the floating plug from deforming during docking, thus avoiding the inability to insert smoothly into the connector socket. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the overall structure of an embodiment of this application;

[0023] Figure 2 This is a schematic diagram illustrating the structure of the plug module according to an embodiment of this application;

[0024] Figure 3 yes Figure 2 Enlarged view of section A;

[0025] Figure 4 This is a schematic diagram illustrating the structure of the socket module according to an embodiment of this application;

[0026] Figure 5 yes Figure 4 A magnified view of section B.

[0027] Explanation of reference numerals in the attached drawings: 1. Plug module; 11. Mounting base; 111. Friction disc; 112. First driving component; 12. Floating plug; 121. Plug slot; 2. Socket module; 21. Housing; 211. Connecting interface; 212. Mounting port; 213. Alignment block; 2131. Roller; 2132. Ball bearing; 214. Limiting block; 215. Limiting groove; 216. Limiting sleeve; 2161. Guide slope; 217. Second elastic element; 218. Second driving component; 22. Connecting socket; 3. Mounting ring; 31. Connecting rod; 32. Mounting block; 33. Telescopic rod; 331. Anti-detachment block; 34. First elastic element; 35. Return spring; 36. Rubber sealing sleeve. Detailed Implementation

[0028] The following is in conjunction with the appendix Figure 1-5 This application will be described in further detail.

[0029] This application discloses a floating connector for on-orbit docking of satellites. (Refer to...) Figure 1 The system includes a plug module 1 and a socket module 2, which are respectively installed at the docking positions of two satellites for docking. The plug module 1 includes a mounting base 11 fixedly mounted on the satellite and a floating plug 12 movably mounted on the mounting base 11. The socket module 2 includes a housing 21 fixedly mounted on the satellite and a connection socket 22 fixedly mounted inside the housing 21. Both the floating plug 12 and the connection socket 22 are electrically connected to cables, and the floating plug 12 is compatible with the connection socket 22.

[0030] Reference Figure 2 , 3 A mounting ring 3 is rotatably mounted on the mounting base 11. A connecting rod 31 is fixedly mounted inside the mounting ring 3. The length direction of the connecting rod 31 is perpendicular to the center line of the mounting ring 3. A mounting block 32 is slidably mounted on the connecting rod 31. A mounting hole is opened along the axial direction of the mounting ring 3 at the end of the mounting block 32 away from the mounting base 11. A telescopic rod 33 slides through the mounting hole. A floating plug 12 is fixedly mounted at the end of the telescopic rod 33 away from the mounting base 11, and the length direction of the floating plug 12 is parallel to the central axis of the mounting ring 3. An anti-detachment block 331 is fixedly mounted at the end of the telescopic rod 33 away from the floating plug 12. The cable connected to the floating plug 12 passes through the telescopic rod 33 and the anti-detachment block 331. When the floating plug 12 is connected to the connecting socket 22, by rotating the mounting ring 3 and sliding the mounting block 32 on the connecting rod 31, the floating plug 12 can be moved to any position within the range of the mounting ring 3, thereby facilitating the insertion of the floating plug 12 into the connecting socket 22.

[0031] Reference Figure 3The mounting block 32 is provided with a first elastic element 34 for driving the telescopic rod 33 to slide away from the mounting base 11. The first elastic element 34 includes a first compression spring, which is sleeved on the telescopic rod 33. One end of the first compression spring abuts against the mounting block 32, and the other end of the first compression spring abuts against the floating plug 12. When the satellites dock, in addition to misalignment, there will also be a certain deviation in the angle between the two satellites. As the two satellites dock, the angle between the two satellites will be gradually corrected. Through the setting of the telescopic rod 33 and the first compression spring, when the angle of the satellites deviates, during the process of the floating plug 12 being inserted into the connecting socket 22, the telescopic rod 33 will be pushed by the reverse force of the connecting socket 22, and will first slide on the mounting block 32 and compress the first compression spring. After the relative angle between the two satellites is corrected, the floating plug 12 is inserted into the connecting socket 22 under the elastic force of the first compression spring, thereby effectively preventing the floating plug 12 from deforming during the docking of the two satellites, which would prevent the floating plug 12 from being inserted into the connecting socket 22 smoothly.

[0032] Reference Figure 2 , 3 Multiple return springs 35 are provided inside the mounting ring 3. The multiple return springs 35 are distributed around the circumference of the mounting ring 3. One end of the return spring 35 is fixedly connected to the inner wall of the mounting ring 3, and the other end of the return spring 35 is fixedly connected to the mounting block 32. When the floating plug 12 is not yet inserted into the connecting socket 22, the floating plug 12 is located in the middle position of the mounting ring 3 under the elastic force of each return spring 35, thereby playing a certain limiting effect on the floating plug 12 and facilitating the positioning of the floating plug 12.

[0033] Reference Figure 2 A rubber sealing sleeve 36 is fixedly installed inside the mounting ring 3. The rubber sealing sleeve 36 is located on the side of the reset spring 35 away from the mounting base 11. The mounting block 32 passes through the rubber sealing sleeve 36 and is fixedly connected to the rubber sealing sleeve 36. The rubber sealing sleeve 36 shields the reset spring 35 and the connecting rod 31 to prevent foreign objects from getting stuck in the mounting ring 3 and causing the floating plug 12 to get stuck in the mounting ring 3.

[0034] Reference Figure 2 , 3The mounting base 11 is provided with a limiting component for restricting the movement of the floating plug 12. The limiting component includes a friction disc 111 and a first driving member 112. The mounting base 11 has a receiving groove along the length direction of the floating plug 12 at one end near the floating plug 12. The friction disc 111 is slidably disposed in the receiving groove along the length direction of the floating plug 12, and the length direction of the floating plug 12 is perpendicular to the friction disc 111. The mounting block 32 has a friction surface at one end near the mounting base 11, and the friction surface is parallel to the friction disc 111. The first driving member 112 includes a first cylinder, which is fixedly disposed in the receiving groove, and the piston rod of the first cylinder is fixedly connected to the friction disc 111. By driving the friction disc 111 to slide towards the mounting block 32 and abut against the friction surface on the mounting block 32, the mounting block 32 can be limited.

[0035] Reference Figure 4 The housing 21 has an interface 211 for the floating plug 12 to enter. The side wall of the housing 21 has multiple mounting ports 212 that communicate with the interior of the housing 21. The mounting ports 212 are evenly distributed along the circumference of the housing 21. A correction block 213 is slidably disposed in each mounting port 212. Each correction block 213 slides in a direction that is closer to or further away from each other, and the sliding direction of the correction block 213 is perpendicular to the central axis of the connecting socket 22. A limit block 214 is fixedly disposed on the side wall of the correction block 213. A limit groove 215 is formed on the side wall of the mounting port 212 along the sliding direction of the corresponding correction block 213. The limit block 214 is slidably disposed in the limit groove 215.

[0036] Reference Figure 4 , 5 The housing 21 is provided with a drive assembly for driving each correction block 213 to slide simultaneously in a direction that moves closer or further away from each other. The drive assembly includes a limiting sleeve 216, a second elastic element 217, and a second drive element 218. Multiple second elastic elements 217 are provided and correspond one-to-one with each correction block 213. Each second elastic element 217 includes a second compression spring. The second compression spring is disposed in the corresponding limiting groove 215. One end of the second compression spring abuts against the side wall of the limiting groove 215 near the connecting socket 22, and the other end of the second compression spring abuts against the limiting block 214.

[0037] Reference Figure 4 , 5 The limiting sleeve 216 is slidably sleeved on the housing 21. Multiple guide slopes 2161 are provided on the inner side wall of the limiting sleeve 216. Each guide slope 2161 is distributed at equal intervals along the circumference of the limiting sleeve 216, and each guide slope 2161 corresponds to a correction block 213. Each guide slope 2161 gradually approaches the correction block 213 in the direction away from the correction block 213. The second driving member 218 includes a second cylinder, which is fixedly mounted on the housing 21. The piston rod of the second cylinder is fixedly connected to the limiting sleeve 216.

[0038] During satellite docking, the floating plug 12 is first inserted into the mating interface 211 of the housing 21. Then, the second cylinder drives the limiting sleeve 216 to slide closer to the calibration block 213. Each calibration block 213 abuts against its corresponding guide slope 2161 in the limiting sleeve 216. Guided by the guide slope 2161, the calibration blocks 213 move closer to each other, thereby correcting the position of the floating plug 12 so that the floating plug 12 is aligned with the connecting socket 22. Then, the friction plate 111 restricts the movement of the floating plug 12. As the two satellites dock, the floating plug 12 is inserted into the connecting socket 22, completing the mating of the connector floating plug 12 and the connecting socket 22.

[0039] Reference Figure 5 Each correction block 213 has a roller 2131 rotatably mounted at one of its opposite ends. The correction block 213 abuts against the guide slope 2161 on the limiting sleeve 216 via the roller 2131. As the limiting sleeve 216 slides, the roller 2131 rolls on the guide slope 2161, thereby reducing the friction between the correction block 213 and the guide slope 2161 on the limiting sleeve 216, and making the limiting sleeve 216 smoother when driving the correction block 213 to slide.

[0040] Reference Figure 5 Each calibration block 213 has a ball bearing 2132 rotatably mounted on one end close to the other. When the calibration block 213 calibrates the floating plug 12, the ball bearing 2132 on the calibration block 213 abuts against the side wall of the floating plug 12. As the floating plug 12 is inserted into the connector socket 22, the ball bearing 2132 rolls and connects with the side wall of the floating plug 12, thereby preventing the calibration block 213 from scratching the side wall of the floating plug 12 and thus affecting the data transmission between the floating plug 12 and the connector socket 22.

[0041] Reference Figure 4 The side wall of the floating plug 12 is also provided with a insertion slot 121 for the insertion of the calibration block 213 along the circumference of the floating plug 12. When the floating plug 12 is fully inserted into the connection socket 22, each calibration block 213 is directly opposite the insertion slot 121 on the floating plug 12. The limiting sleeve 216 then drives each calibration block 213 to slide a certain distance in the direction of mutual approach, so that each calibration block 213 is inserted into the insertion slot 121 on the floating plug 12, thereby effectively preventing the connection between the floating plug 12 and the connection socket 22 from becoming loose.

[0042] The implementation principle of a floating connector for satellite on-orbit docking in this application embodiment is as follows: During satellite docking, the floating plug 12 is first inserted into the mating interface 211 of the housing 21. Then, the limiting sleeve 216 is driven by the second cylinder to slide towards the calibration block 213. Each calibration block 213 abuts against its corresponding guide slope 2161 inside the limiting sleeve 216, and under the guidance of the guide slope 2161, the calibration blocks 213 are driven to move closer to each other, thereby correcting the position of the floating plug 12, so that the floating plug 12 and the connecting... With the connector socket 22 aligned, the first cylinder drives the friction disc 111 to slide towards the mounting block 32 and press against the friction surface on the mounting block 32, thus limiting the mounting block 32. As the two satellites dock, the floating plug 12 is inserted into the connector socket 22. Therefore, even if there is a deviation in the on-orbit docking of the satellites, within a certain deviation range, the connector floating plug 12 can still accurately engage with the connector socket 22 without needing to readjust the relative position between the two satellites, thereby avoiding a large consumption of satellite fuel.

[0043] The above are all preferred embodiments of this application, and are not intended to limit the scope of protection of this application. Therefore, all equivalent changes made in accordance with the structure, shape and principle of this application should be covered within the scope of protection of this application.

Claims

1. A floating connector for satellite on-orbit docking, characterized in that: It includes a plug module (1) and a socket module (2), which are respectively installed at the docking positions of two satellites for docking. The plug module (1) includes a mounting base (11) fixedly installed on the satellite and a floating plug (12) movably installed on the mounting base (11). The mounting base (11) is provided with a limiting component for restricting the movement of the floating plug (12). The socket module (2) includes a housing (21) fixedly mounted on the satellite and a connection socket (22) fixedly mounted inside the housing (21). The housing (21) has a mating interface (211) for a floating plug (12) to enter, and the floating plug (12) is compatible with the connection socket (22). Multiple correction blocks (213) are distributed on the housing (21) and along the circumference of the interface (211). Each correction block (213) is slidably engaged with the housing (21). The housing (21) is provided with a drive assembly for driving each correction block (213) to slide simultaneously in a direction that moves closer to or further away from each other. An installation ring (3) is rotatably mounted on the mounting base (11). A connecting rod (31) is fixedly mounted inside the installation ring (3). An installation block (32) is slidably mounted on the connecting rod (31) along the length direction of the connecting rod (31). The floating plug (12) is mounted on the installation block (32). The rotation axis of the installation ring (3) is parallel to the length direction of the floating plug (12), and the length direction of the connecting rod (31) is perpendicular to the length direction of the floating plug (12).

2. The floating connector for satellite on-orbit docking according to claim 1, characterized in that: A reset spring (35) is provided inside the mounting ring (3). One end of the reset spring (35) is fixedly connected to the inner wall of the mounting ring (3), and the other end of the reset spring (35) is fixedly connected to the mounting block (32).

3. A floating connector for satellite on-orbit docking according to claim 1, characterized in that: A rubber sealing sleeve (36) is fixedly installed inside the mounting ring (3), and the mounting block (32) penetrates the rubber sealing sleeve (36), and the mounting block (32) is fixedly connected to the rubber sealing sleeve (36).

4. A floating connector for satellite on-orbit docking according to claim 1, characterized in that: A telescopic rod (33) is slidably disposed on the mounting block (32) along the length direction of the floating plug (12). The floating plug (12) is fixedly disposed on the telescopic rod (33). A first elastic element (34) is disposed on the mounting block (32) for driving the telescopic rod (33) to slide away from the mounting base (11).

5. A floating connector for satellite on-orbit docking according to claim 1, characterized in that: The limiting component includes a friction disk (111) slidably disposed on the mounting base (11) and a first driving member (112) for driving the friction disk (111) to slide. The mounting block (32) is provided with a friction surface, and the friction disk (111) is used to abut against the friction surface on the mounting block (32).

6. A floating connector for satellite on-orbit docking according to claim 1, characterized in that: The driving assembly includes a limiting sleeve (216), a second elastic element (217), and a second driving element (218). The limiting sleeve (216) is slidably sleeved on the housing (21). Multiple guide slopes (2161) are provided on the inner sidewall of the limiting sleeve (216). Each guide slope (2161) corresponds to a correction block (213), and each guide slope (2161) gradually approaches the correction block (213) in a direction away from the correction block (213). Multiple second elastic elements (217) are provided and correspond to each correction block (213). The second elastic element (217) is used to drive the corresponding correction block (213) to slide away from the housing (21). The second driving element (218) is used to drive the limiting sleeve (216) to slide.

7. A floating connector for satellite on-orbit docking according to claim 6, characterized in that: Each of the correction blocks (213) has a roller (2131) rotatably provided at one end away from each other. The roller (2131) is used to abut against the corresponding guide slope (2161) and is in rolling connection with the guide slope (2161).

8. A floating connector for satellite on-orbit docking according to claim 6, characterized in that: Each of the correction blocks (213) has a ball bearing (2132) rotatably mounted at one end close to the other. The ball bearing (2132) is used to abut against the floating plug (12) and is rotatably connected to the floating plug (12).

9. A floating connector for satellite on-orbit docking according to claim 1, characterized in that: The sidewall of the floating plug (12) is provided with a plug groove (121) for inserting the correction block (213) along the circumference of the floating plug (12).

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