Space docking interface based on electromagnetic drive

Abstract

This invention provides an electromagnetically driven space docking interface, relating to the field of space launch technology. It includes a satellite interface and a mother satellite interface. The satellite interface includes a main body with a satellite coil and coil core embedded in it, and an extended locking rod at the lower part of the main body. The mother satellite interface includes a main body with a mother satellite coil embedded in it, and a locking assembly at the upper part of the main body. Both the satellite and mother satellite coils are energized, with the lower end face of the satellite interface contacting the upper end face of the mother satellite interface, and the locking rod engaging with the locking assembly. This electromagnetic-locking assembly locking scheme results in no fuel consumption and no plume pollution. The current in the mother satellite coil is dynamically adjusted; as the distance between the satellite and mother satellite decreases, the current gradually decreases, providing excellent buffering performance and enabling flexible docking. The pre-tightening rod presses down, actuating the contacts of a microswitch, simultaneously achieving pre-tightening and sending a locking signal.

Description

Technical Field

[0001] This invention relates to the field of space launch technology, and in particular to a space docking interface based on electromagnetic drive. Background Technology

[0002] Currently, traditional spacecraft docking relies primarily on thruster reaction forces, but this method has inherent problems: fuel consumes valuable payload space and limits mission lifespan; jet plumes can contaminate optical instruments and sensitive components; and the final docking phase relies entirely on inertial collisions, resulting in large impacts, difficulty in achieving flexible connections, and potential damage to precision equipment. Furthermore, traditional mechanical fixing structures require extremely high docking precision, further increasing the difficulty. Summary of the Invention

[0003] This invention provides a space docking interface based on electromagnetic drive. Existing technologies suffer from problems such as fuel consumption of valuable payload and limitation of mission life; jet plumes that easily contaminate optical instruments and sensitive devices; the final docking stage relying entirely on inertial collisions, resulting in large impacts, difficulty in achieving flexible connections, and potential damage to precision equipment; and extremely high docking accuracy requirements, which increase the difficulty.

[0004] To address the aforementioned problems, the present invention provides the following technical solution:

[0005] A type of electromagnetically driven space docking interface includes a sub-satellite interface and a mother-satellite interface. The sub-satellite interface includes a sub-satellite interface body, on which a sub-satellite coil and a coil core are embedded. An extended locking rod is installed at the lower part of the sub-satellite body. The mother-satellite interface includes a mother-satellite interface body, on which a mother-satellite coil is embedded. A locking assembly is provided at the upper part of the mother-satellite body. When the sub-satellite coil and the mother-satellite coil are energized, the lower end face of the sub-satellite interface contacts the upper end face of the mother-satellite interface, and the locking rod cooperates with the locking assembly.

[0006] Optionally, the locking assembly includes a sleeve and an unlocking pin mounted on the main body of the mother satellite interface. The unlocking pin is slidably sleeved on the outside of the sleeve. A steel ball is rotatably mounted on the sleeve. The inner side of the steel ball is exposed on the inner side of the sleeve, and the outer side of the steel ball is exposed in the mother satellite interface locking groove or unlocking groove of the unlocking pin. A daughter satellite locking groove is provided on the outer side of the locking rod. The locking rod is inserted into the sleeve, and the inner side of the steel ball presses against the daughter satellite locking groove and the outer side presses against the mother satellite interface locking groove.

[0007] Optionally, the locking assembly further includes a magnet disposed inside the sleeve, the bottom of the magnet being connected to one end of a magnet spring, the other end of the magnet spring being connected to the mothership interface body, and the top of the magnet being provided with a groove that engages with the bottom of the locking rod.

[0008] Optionally, the bottom of the locking rod is provided with a spherical part, the spherical part is spherical, the groove of the magnet is arc-shaped, and the spherical part is adapted to the groove.

[0009] Optionally, the mothership interface further includes a connecting plate, which is connected to the unlocking pin, and a micro switch is installed on the connecting plate.

[0010] Optionally, the main body of the mother satellite interface is provided with a pre-tightening rod mounting hole, the pre-tightening rod is slidably installed in the pre-tightening rod mounting hole, one end of the pre-tightening spring is connected to the pre-tightening rod and the other end is connected to the inside of the pre-tightening rod mounting hole, and the bottom of the pre-tightening rod extends outward and is connected to a micro switch located on the top of the connecting plate.

[0011] Optionally, a cone is installed at the bottom of the sub-satellite interface body, the lower part of the cone is provided with a tapered portion, and the upper part of the sleeve is provided with a guide hole, the tapered portion being adapted to the guide hole.

[0012] Optionally, the cone is further provided with a column, and the top of the mother star interface body is provided with a guide groove, so that the column can be inserted into the guide groove.

[0013] Optionally, the cone further includes a mounting bracket, in which a locking rod is slidably mounted. One end of the guide rod spring is connected to the inner wall of the mounting bracket, and the other end is connected to the locking rod. A through hole is provided on the cone, and the locking rod extends out of the through hole.

[0014] Optionally, a push rod is installed at the bottom of the mothership interface body.

[0015] The above technical solution has at least the following advantages compared with the existing technology:

[0016] The above scheme, based on the electromagnetically driven space docking interface, adopts an electromagnetic-locking component locking scheme. During the entire docking process between the satellite and mother satellite interfaces, there is no fuel consumption or plume pollution. As the satellite interface approaches the mother satellite interface, the current in the satellite and mother satellite coils is dynamically adjusted. The current in the satellite coil gradually decreases as the distance between the satellite and mother satellite decreases. Furthermore, the placement of guide rod springs, magnetic springs, and pre-tensioning springs provides excellent buffering performance during docking, achieving flexible docking. The mother satellite coil is located at the top of the mother satellite interface body, while the locking component is located in the middle and lower parts of the mother satellite interface body. This adopts a front-mounted mother satellite coil and rear-mounted locking mechanism, maximizing the use of electromagnetic coils for electromagnetic docking. When the pre-tensioning rod is pressed down, it actuates the contacts of the microswitch, closing the contacts and simultaneously sending a locking signal. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 This is a perspective view of the electromagnetically driven space docking interface of the present invention.

[0019] Figure 2 This is a schematic diagram of the sub-star interface of the electromagnetically driven space docking interface of the present invention.

[0020] Figure 3 This is a schematic diagram of the home planet interface of the electromagnetically driven space docking interface of the present invention.

[0021] Figure 4 This is a schematic diagram of the sub-satellite interface and the mother-satellite interface of the electromagnetically driven space docking interface of the present invention when they are not locked.

[0022] Figure 5 This is a schematic diagram of the structure of the slave star interface and the mother star interface of the electromagnetically driven space docking interface of the present invention when locked.

[0023] The annotations in the attached figures are explained as follows:

[0024] 1. Locking rod; 111. Sub-star interface locking groove; 112. Spherical part; 2. Cone; 201. Through hole; 202. Mounting bracket; 3. Column; 4. Sub-star coil; 5. Coil core; 6. Guide rod spring; 7. Copper bushing; 8. Push rod; 9. Magnetic spring; 10. Magnet; 101. Groove; 11. Steel ball; 12. Sleeve; 121. Guide hole; 13. Unlocking pin; 131. Unlocking groove; 132. Mother star interface locking groove; 14. Micro switch; 15. Preload spring; 16. Mother star coil; 17. Preload rod; 171. Preload rod mounting hole; 18. Connecting plate; 19. Sub-star interface body; 20. Mother star interface body; 21. Sub-star interface; 22. Mother star interface. Detailed Implementation

[0025] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. All other embodiments obtained by those skilled in the art based on the described embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0026] Unless otherwise defined, the technical or scientific terms used in this invention shall have the ordinary meaning understood by one of ordinary skill in the art to which this invention pertains. The terms “first,” “second,” and similar terms used in this invention do not indicate any order, quantity, or importance, but are merely used to distinguish different components. Similarly, the terms “an,” “a,” or “the,” and similar terms do not indicate a quantity limitation, but rather indicate the presence of at least one. The terms “comprising,” “including,” or “including,” and similar terms mean that the element or object preceding the word encompasses the element or object listed following the word and its equivalents, without excluding other elements or objects. The terms “connected,” “linked,” or “connected,” and similar terms are not limited to physical or mechanical connections, but can include electrical connections, whether direct or indirect.

[0027] It should be noted that the terms "up", "down", "left", "right", "front", and "back" used in this invention are only used to indicate relative positional relationships. When the absolute position of the object being described changes, the relative positional relationship may also change accordingly.

[0028] like Figures 1-5 As shown, this embodiment provides an electromagnetically driven space docking interface, which can be used for docking and locking processes when recovering satellites or other payloads (hereinafter collectively referred to as sub-satellite interface 21) in microgravity or zero-gravity environments. It includes a sub-satellite interface 21 and a mother satellite interface 22. The sub-satellite interface 21 includes a sub-satellite interface body 19, on which a sub-satellite coil 4 and a coil core 5 are embedded. An extended locking rod 1 is installed at the lower part of the sub-satellite interface body 19. The mother satellite interface 22 includes a mother satellite interface body 20, on which a mother satellite coil 16 is embedded. A locking assembly is provided at the upper part of the mother satellite interface body 20. When the sub-satellite coil 4 and the mother satellite coil 16 are energized, the lower end face of the sub-satellite interface 21 contacts the upper end face of the mother satellite interface 22, and the locking rod 1 cooperates with the locking assembly.

[0029] like Figure 3As shown, the locking assembly includes a sleeve 12 and an unlocking pin 13 mounted on the main body 20 of the mother satellite interface. The unlocking pin 13 is slidably sleeved on the outside of the sleeve 12. A steel ball 11 is rotatably mounted on the sleeve 12, with the inner side of the steel ball 11 exposed to the inner side of the sleeve 12, and the outer side of the steel ball 11 exposed in the mother satellite locking groove 132 or unlocking groove 131 of the unlocking pin 13. Specifically, the mother satellite locking groove 132 is conical, and the unlocking groove 131 is cylindrical. A daughter satellite locking groove 111 is provided on the outer side of the locking rod 1. The locking rod 1 is inserted into the sleeve 12, with the inner side of the steel ball 11 pressing against the daughter satellite locking groove 111 and the outer side pressing against the mother satellite locking groove 132. Specifically, the upper part of the daughter satellite locking groove 111 is conical, and the lower part is arc-shaped. The locking assembly also includes a magnet 10 disposed inside the sleeve 12. The bottom of the magnet 10 is connected to one end of a preload spring 15, and the other end of the preload spring 15 is connected to the mother-star interface body 20. The top of the magnet 10 is provided with a groove 101, which mates with the bottom of the locking rod 1. The bottom of the locking rod 1 is provided with a spherical part 112, which is spherical. The groove 101 of the magnet 10 is arc-shaped, and the spherical part 112 is adapted to the groove 101.

[0030] like Figure 3 As shown, the mothership interface 22 also includes a connecting plate 18, which is connected to the unlocking pin 13. A micro switch 14 is installed on the connecting plate 18. The mothership body 20 is provided with a pre-tensioning rod mounting hole 171. The pre-tensioning rod 17 is slidably installed in the pre-tensioning rod mounting hole 171. One end of the pre-tensioning spring 15 is connected to the pre-tensioning rod 17, and the other end is connected to the inside of the pre-tensioning rod mounting hole 171. The bottom of the pre-tensioning rod 17 extends outward and is connected to the micro switch 14 located on the top of the connecting plate 18. A push rod 8 is installed at the bottom of the mothership interface body 20.

[0031] like Figure 2 and Figure 4 As shown, a cone 2 is mounted on the bottom of the sub-satellite body 19. The lower part of the cone 2 has a tapered section, and the upper part of the sleeve 12 has a guide hole 121, which is adapted to the tapered section. A column 3 is also provided on the cone 2, and a guide groove is provided on the top of the mother satellite interface body 20, allowing the column 3 to be inserted into the guide groove. Specifically, there are three columns 3 to prevent the sub-satellite interface 21 from rotating when it is docked with the mother satellite interface structure. The cone 2 also includes a mounting bracket 202, in which a locking rod 1 is slidably mounted. One end of the guide rod spring 6 is connected to the inner wall of the mounting bracket 202, and the other end is connected to the locking rod 1. A through hole 201 is provided on the tapered section, and the locking rod 1 extends out of the through hole 201.

[0032] In this embodiment, the daughter star coil 4 and the mother star coil 16 are electromagnetic coils.

[0033] The working process of the electromagnetically driven space docking interface in this embodiment is as follows:

[0034] When the sub-satellite interface 21 flies to a position approximately 600mm from the parent satellite, the sub-satellite coil 4 of the sub-satellite interface 21 and the parent satellite coil 16 of the parent satellite interface 22 are energized, generating electromagnetic traction, causing the sub-satellite interface 21 to approach the parent satellite interface 22 (e.g., Figure 4 (As shown); before the lower end face of the sub-satellite body 19 contacts the pre-tightening rod 17, the unlocking pin 13 and the connecting plate 18 move upward under the action of electromagnetic force. At this time, the steel ball 11 is exposed in the cylindrical groove of the unlocking groove 131, and the steel ball 11 can rotate freely; the sub-satellite interface body 19 continues to approach the mother satellite interface body 20, and the locking rod 1 is inserted into the guide hole 121 of the sleeve 12. The locking rod 1 and the sleeve 12 play a guiding role; the sub-satellite interface 21 continues to approach the mother satellite interface 22, and the cone of the cone 2... After the part is inserted into the guide hole 121, it continues to move downward along the sleeve 12. During this process, the lower end face of the sub-star body 19 presses against the pre-tightening rod 17, and the pre-tightening rod 17 presses against the micro switch 14, thereby pushing the connecting plate 18 and the unlocking pin 13 to move downward until the sub-star locking groove 111 of the locking rod 1 presses against the inner side of the steel ball 11, and the outer side of the steel ball 11 presses against the mother star locking groove 132. The groove 101 of the magnet 10 pushes the spherical part 112 of the locking rod 1 upward, thereby realizing the locking of the locking rod 1 and the locking assembly (e.g., Figure 5 As shown in the figure, this enables the locking of the sub-star interface 21 with the parent star structure.

[0035] During the above process, the preload rod 17 presses down, causing the contacts of the micro switch 14 to actuate. The contacts of the micro switch 14 close, sending a locking signal outward. The arrangement of the guide rod spring 6, the magnet spring 9, and the preload spring 15 provides excellent buffering performance when the slave interface 21 and the mother interface 22 are docked.

[0036] During the process of the daughter star interface 21 approaching the mother star interface 22, the current in the mother star coil is in a dynamic adjustment stage. As the distance between the mother and daughter stars decreases, the current in the daughter star coil 4 gradually decreases. With the use of springs, flexible docking is achieved, which is highly efficient and pollution-free.

[0037] The mothership coil 16 is arranged on the upper part of the mothership interface body 20, and the locking components are arranged in the middle and lower parts of the mothership interface body 20. The technical solution of front-mounted mothership coil 16 and rear-mounted locking mechanism is adopted to maximize the use of electromagnetic coil to connect electromagnetic.

[0038] The daughter satellite coil 4 and the mother satellite coil 16 can be used for daughter satellite recovery docking, as well as for locking daughter satellite interface 21 and mother satellite interface 22, ensuring the reliability of the device and saving space occupancy.

[0039] The space docking interface of this invention boasts advantages such as short production cycle and low cost, enabling low-cost connection and separation of the daughter star interface 21 and the mother star interface 22. This can serve cutting-edge applications such as large-aperture space telescopes and high-resolution reconnaissance imaging systems. Simultaneously, the use of permanent magnets allows for close-range assisted docking, reducing accuracy and energy consumption requirements and improving docking fault tolerance.

[0040] The above are merely specific embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. The scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A space docking interface based on electromagnetic drive, characterized in that, It includes a sub-satellite interface and a mother-satellite interface. The sub-satellite interface includes a sub-satellite interface body, on which a sub-satellite coil and a coil core are embedded. An outward locking rod is installed at the lower part of the sub-satellite interface body. The mothership interface includes a mothership interface body, on which a mothership coil is embedded. A locking assembly is provided on the upper part of the mothership interface body. The daughtership coil and the mothership coil are energized, and the lower end face of the daughtership interface contacts the upper end face of the mothership interface. The locking rod cooperates with the locking assembly. The locking assembly includes a sleeve and an unlocking pin installed on the mothership interface body. The unlocking pin is slidably sleeved on the outside of the sleeve. A steel ball is rotatably installed on the sleeve. The inner side of the steel ball is exposed on the inner side of the sleeve, and the outer side of the steel ball is exposed in the mothership interface locking groove or unlocking groove of the unlocking pin. A daughtership locking groove is provided on the outer side of the locking rod. The locking rod is inserted into the sleeve, and the inner side of the steel ball presses against the daughtership locking groove and the outer side presses against the mothership interface locking groove. The locking assembly also includes a magnet disposed inside the sleeve. The bottom of the magnet is connected to one end of a magnet spring, and the other end of the magnet spring is connected to the mother satellite interface body. The top of the magnet is provided with a groove, which cooperates with the bottom of the locking rod. The mothership interface also includes a connecting plate, which is connected to the unlocking pin, and a micro switch is installed on the connecting plate; The main body of the mothership interface is provided with a pre-tightening rod mounting hole. The pre-tightening rod is slidably installed in the pre-tightening rod mounting hole. One end of the pre-tightening spring is connected to the pre-tightening rod and the other end is connected to the inside of the pre-tightening rod mounting hole. The bottom of the pre-tightening rod extends outward and is connected to a micro switch located on the top of the connecting plate. As the daughter satellite interface approaches the mother satellite interface, the current in the daughter and mother satellite coils is in a dynamic adjustment phase. As the distance between the daughter and mother satellites decreases, the current in the daughter satellite coil gradually decreases.

2. The space docking interface based on electromagnetic drive according to claim 1, characterized in that, The bottom of the locking rod is provided with a spherical part, which is spherical in shape, and the groove of the magnet is arc-shaped, with the spherical part fitting into the groove.

3. The electromagnetically driven space docking interface according to claim 1, characterized in that, The bottom of the sub-satellite interface body is equipped with a cone, the lower part of the cone is provided with a tapered portion, and the upper part of the sleeve is provided with a guide hole, the tapered portion being adapted to the guide hole.

4. The electromagnetically driven space docking interface according to claim 3, characterized in that, The cone is also provided with a column, and the top of the main body of the mother star interface is provided with a guide groove, so that the column can be inserted into the guide groove.

5. The electromagnetically driven space docking interface according to claim 3, characterized in that, The cone also includes a mounting bracket, in which a locking rod is slidably mounted. One end of a guide rod spring is connected to the inner wall of the mounting bracket, and the other end is connected to the locking rod. A through hole is provided on the cone, and the locking rod extends out of the through hole.

6. The electromagnetically driven space docking interface according to claim 3, characterized in that, A push rod is installed at the bottom of the main body of the mother planet interface.

Images