Space docking interface based on electromagnetic driving

Abstract

The invention provides a space docking interface based on electromagnetic driving, and relates to the technical field of space launching technologies. Comprising a child star interface and a mother star interface, the child star interface comprises a child star interface body, a child star coil and a coil iron core are installed on the child star interface body in an embedded mode, and a locking rod extending outwards is installed on the lower portion of the child star interface body; the mother star interface comprises a mother star interface main body, a mother star coil is embedded in the mother star interface main body, and a locking assembly is arranged at the upper part of the mother star interface main body; the child star coil and the mother star coil are electrified, the lower end face of the child star interface makes contact with the upper end face of the mother star interface, and the locking rod is matched with the locking assembly. A locking scheme of an electromagnetic-locking assembly is adopted, so that fuel consumption and plume pollution are avoided; the current in the primary star coil is in a dynamic adjustment stage, the current of the secondary star coil is gradually reduced along with the reduction of the distance between the primary star and the secondary star, and the flexible butt joint is realized by good buffer performance; the pre-tightening rod is pressed downwards to drive a contact of the microswitch to act, and a locking signal is sent out while pre-tightening is achieved.

Description

TECHNICAL FIELD

[0001] The application relates to the technical field of space launch technology, and in particular to a space docking interface based on electromagnetic driving. BACKGROUND

[0002] At present, the connection of a traditional spacecraft mainly depends on the reaction force of a thruster, but there are inherent problems: fuel occupies precious load and limits the service life; the jet plume is easy to pollute optical instruments and sensitive devices; the final docking stage completely relies on inertial collision, which is difficult to realize flexible connection and may damage precision equipment. At the same time, the traditional mechanical fixing structure has a very high requirement on docking accuracy, which further increases the difficulty. SUMMARY

[0003] The application provides a space docking interface based on electromagnetic driving, and the prior art has the problems of fuel occupying precious load and limiting the service life; the jet plume is easy to pollute optical instruments and sensitive devices; the final docking stage completely relies on inertial collision, which is difficult to realize flexible connection and may damage precision equipment; and the docking accuracy requirement is extremely high, increasing the difficulty.

[0004] To solve the above-mentioned problems, the technical scheme provided by the application is as follows:

[0005] A space docking interface based on electromagnetic driving, comprising a child star interface and a parent star interface, the child star interface comprising a child star interface main body, a child star coil and a coil iron core being embedded and installed on the child star interface main body, and an outwardly extending locking rod being installed at the lower part of the child star main body; the parent star interface comprising a parent star interface main body, a parent star coil being embedded and installed on the parent star interface main body, and a locking assembly being arranged at the upper part of the parent star main body; the child star coil and the parent star coil being electrified, the lower end surface of the child star interface being in contact with the upper end surface of the parent star interface, and the locking rod being matched with the locking assembly.

[0006] Optionally, the locking assembly comprises a sleeve and an unlocking pin, the unlocking pin being slidingly sleeved on the outside of the sleeve, a steel ball being rotatably installed on the sleeve, the inside of the steel ball being exposed to the inside of the sleeve, and the outside of the steel ball being exposed to the parent star interface locking groove or the unlocking groove of the unlocking pin; the outside of the locking rod being provided with a child star locking groove, the locking rod being inserted into the sleeve, and the inside of the steel ball being pressed against the child star locking groove and the outside of the steel ball being pressed against the parent star interface locking groove.

[0007] Optionally, the locking assembly further comprises a magnet arranged on the inside of the sleeve, the bottom of the magnet being connected to one end of a pre-tightening spring, the other end of the pre-tightening spring being connected to the parent star interface main body, the top of the magnet being provided with a groove matched 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 circular arc, and the spherical part is matched with the groove.

[0009] Optionally, the female star interface further comprises a connecting plate connected with the unlocking pin, and a micro switch is mounted on the connecting plate.

[0010] Optionally, the female star interface body is provided with a pre-tightening rod mounting hole, a pre-tightening rod is slidingly mounted in the pre-tightening rod mounting hole, one end of a pre-tightening spring is connected with the pre-tightening rod, the other end of the pre-tightening spring is connected with the inside of the pre-tightening rod mounting hole, and the bottom of the pre-tightening rod extends outward and is connected with a micro switch located on the top of the connecting plate.

[0011] Optionally, the bottom of the female star interface body is provided with a cone, the upper part of the sleeve is provided with a guide hole, and the cone is matched with the guide hole.

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

[0013] Optionally, the cone further comprises a mounting frame, a locking rod is slidingly mounted in the mounting frame, one end of a guide rod spring is connected with the inner wall of the mounting frame, the other end of the guide rod spring is connected with the locking rod, the cone is provided with a through hole, and the locking rod extends outward from the through hole.

[0014] Optionally, the bottom of the female star interface body is provided with a push rod.

[0015] Compared with the prior art, the above technical solution has at least the following beneficial effects:

[0016] The above scheme adopts the locking scheme of the electromagnetic-locking assembly based on the electromagnetic driving space docking interface. In the docking process of the female star interface and the male star interface, no fuel is consumed and no plume pollution is caused. In the process of the male star interface approaching the female star interface, the current in the male star coil and the female star coil is in a dynamic adjustment stage. As the distance between the male star and the female star decreases, the current in the male star coil gradually decreases. The arrangement of the guide rod spring, the magnet spring and the pre-tightening spring enables the female star interface and the male star interface to have good buffering performance when they are docked, and flexible docking is achieved. The male star coil is arranged on the upper part of the female star interface body, the locking assembly is arranged on the middle and lower parts of the female star interface body, and the technical scheme of front male star coil and rear locking mechanism is adopted, so that the electromagnetic coil docking is maximized. When the pre-tightening rod is pressed down to drive the contact of the micro switch to move, the contact of the micro switch is closed, so that the pre-tightening is realized and the locking signal can be sent outward. BRIEF DESCRIPTION OF DRAWINGS

[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, The system includes a subsatellite interface and a mother satellite interface. The subsatellite interface includes a subsatellite interface body, on which a subsatellite coil and a coil core are embedded. An extended locking rod is installed at the lower part of the subsatellite interface 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 interface body. When the subsatellite coil and the mother satellite coil are energized, the lower end face of the subsatellite interface contacts the upper end face of the mother satellite interface, and the locking rod cooperates with the locking assembly.

2. The space docking interface based on electromagnetic drive according to claim 1, characterized in that, 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. 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.

3. The electromagnetically driven space docking interface according to claim 2, characterized in that, The locking assembly also includes a magnet disposed inside the sleeve. The bottom of the magnet is connected to one end of a pre-tensioning spring, and the other end of the pre-tensioning 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.

4. The electromagnetically driven space docking interface according to claim 3, 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.

5. The electromagnetically driven space docking interface according to claim 3, characterized in that, 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.

6. The electromagnetically driven space docking interface according to claim 1, characterized in that, 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.

7. The electromagnetically driven space docking interface according to claim 2, 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.

8. The electromagnetically driven space docking interface according to claim 7, 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.

9. The electromagnetically driven space docking interface according to claim 7, 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.

10. The electromagnetically driven space docking interface according to claim 7, characterized in that, A push rod is installed at the bottom of the main body of the mother planet interface.

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