An electromagnetic docking device for on-orbit combination of micro-nano satellites

Abstract

The present invention discloses an electromagnetic docking device for an on-orbit assembly of a micro-nano satellite, comprising a rear plate and a docking ring, wherein a screw is threadedly inserted on one side of the rear plate close to the docking ring, one end of the screw is fixedly connected to the docking ring, an iron plate is slidably sleeved on the screw, a rear cover is provided between the iron plate and the rear plate, a threaded opening corresponding to the screw is provided on the rear cover, and an electromagnet is fixedly connected on the side of the docking ring away from the rear plate; a spring is sleeved on the screw, and the two ends of the spring are respectively against the iron plate and the docking ring, a disc spring is inserted in the rear cover, and the two ends of the disc spring are respectively fixedly connected to the rear cover and the iron plate. The docking device of the present invention has the advantages of simple structure, no plume pollution, weak impact, etc., solves the problems of long and slow response of space scientific research and combat mission processes, and can realize the function of repeated rapid docking and separation on orbit, meeting the complex, flexible and changeable mission requirements with timeliness.

Description

Technical Field

[0001] The present invention relates to the technical field of aerospace equipment, and in particular to an electromagnetic docking device for on-orbit assembly of micro-nano satellites. Background Art

[0002] In recent years, many small and micro-nano satellites have adopted the concept of "modular design, on-orbit formation, and on-demand application" to address the increasing diversification and complexity of space missions. This approach allows spacecraft to be assembled, supplemented, replaced, expanded, and upgraded on-orbit. This approach uses modular, reconfigurable methods to dock and combine multiple micro-nano satellites into spacecraft platforms with diverse operational configurations. The application of on-orbit micro-nano satellite assembly will significantly reduce development time and costs, reduce spacecraft structural complexity, increase mission diversity and flexibility, and provide a solution for reducing the number of spacecraft that fail on-orbit.

[0003] In-orbit combination requires multi-body combination and flexible configuration of micro-nano satellites to complete complex space missions and scientific research goals. Therefore, the connection method between satellites will be a particularly important part.

[0004] However, the existing docking devices for micro-nano satellites are very immature, large in size, and have poor reliability in docking locking or unlocking. They cannot repeatedly and quickly dock and separate, and cannot meet the needs of complex, flexible and changeable tasks. Summary of the Invention

[0005] 1. Technical problems to be solved

[0006] The purpose of the present invention is to solve the problems in the prior art that the docking devices are very immature, the docking devices are large in size, the reliability of their docking locking or unlocking is poor, and they cannot be repeatedly and quickly docked and separated. An electromagnetic docking device for the in-orbit assembly of micro-nano satellites is proposed.

[0007] 2. Technical solution

[0008] In order to achieve the above object, the present invention adopts the following technical solutions:

[0009] An electromagnetic docking device for an on-orbit assembly of a micro-nano satellite comprises a rear plate and a docking ring. A screw is threadedly inserted into a side of the rear plate close to the docking ring. One end of the screw is fixedly connected to the docking ring. An iron plate is slidably sleeved on the screw. A rear cover is provided between the iron plate and the rear plate. The rear cover is provided with a threaded opening corresponding to the screw. An electromagnet is fixedly connected to a side of the docking ring away from the rear plate.

[0010] A spring is sleeved on the screw rod, and the two ends of the spring are respectively against the iron plate and the docking ring. A disc spring is inserted into the rear cover, and the two ends of the disc spring are respectively fixedly connected to the rear cover and the iron plate;

[0011] The four sides of the rear plate are rotatably connected with a plurality of connecting blocks by pins, and the end of the connecting block away from the rear plate is slidably connected with a hook claw, and the hook claw is fixedly connected to the connecting shaft. The rear plate is provided with an arc guide groove corresponding to the connecting shaft, and both ends of the connecting shaft are rotatably connected with a rocker arm, and the end of the rocker arm away from the connecting shaft is rotatably connected to the first connecting rod and the second connecting rod through the rotating shaft, the end of the first connecting rod away from the connecting shaft is rotatably connected to the docking ring, and the second connecting rod is rotatably connected to the iron plate.

[0012] Preferably, a plurality of outer flaps are provided around the side of the docking ring close to the electromagnet, and grooves corresponding to the hook claws are provided on the outer flaps and the docking ring.

[0013] Preferably, the connecting block is provided with a guide groove corresponding to the hook claw.

[0014] Preferably, the rear plate is hollow.

[0015] Preferably, the docking ring is surrounded by a first rotation groove corresponding to the first connecting rod.

[0016] Preferably, the iron plate is surrounded by a second rotation groove corresponding to the second connecting rod.

[0017] Preferably, a plurality of fastening openings are provided on a side of the rear plate away from the docking ring.

[0018] 3. Beneficial effects

[0019] Compared with the prior art, the advantages of the present invention are:

[0020] (1) In the present invention, the docking device has the advantages of simple structure, no plume pollution, weak impact, etc., which can solve the problems of long and slow response in space scientific research and combat mission processes, and can realize the function of repeated rapid docking and separation in orbit, meeting the complex, flexible and changeable mission requirements with timeliness.

[0021] (2) In the present invention, the docking device has the characteristics of modularity and lightness, and different modules launched into orbit multiple times have the same mechanical interface; the docking is repeatable, meeting the requirements of multiple docking, and its locking and unlocking should have high reliability.

[0022] (3) In the present invention, the docking device adopts a simple shape and structure; after docking, it can provide sufficient locking force to ensure inertial characteristics and positioning accuracy, so that the attitude control system, optical instruments, etc. on it will not produce large errors. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 This is a schematic diagram of the docking structure of an electromagnetic docking device for on-orbit assembly of micro-nano satellites proposed by the present invention;

[0024] Figure 2 This is a schematic diagram of the three-dimensional structure of an electromagnetic docking device for in-orbit assembly of micro-nano satellites proposed by the present invention;

[0025] Figure 3 This is a schematic diagram of the exploded structure of an electromagnetic docking device for on-orbit assembly of micro-nano satellites proposed by the present invention;

[0026] Figure 4 This is a schematic diagram of the hook structure of an electromagnetic docking device for on-orbit assembly of micro-nano satellites proposed by the present invention;

[0027] Figure 5 This is a schematic diagram of the rear plate structure of an electromagnetic docking device for on-orbit assembly of micro-nano satellites proposed by the present invention.

[0028] In the figure: 1 rear plate, 2 docking ring, 3 screw, 4 iron plate, 5 rear cover, 6 electromagnet, 7 spring, 8 disc spring, 9 pin, 10 connecting block, 11 hook, 12 connecting shaft, 13 arc guide groove, 14 rocker, 15 rotating shaft, 16 first connecting rod, 17 second connecting rod, 18 outer flap. DETAILED DESCRIPTION

[0029] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0030] Example 1:

[0031] Reference Figure 1-5 An electromagnetic docking device for in-orbit assembly of micro-nano satellites includes a rear plate 1 and a docking ring 2. The rear plate 1 is hollow and has multiple fastening openings on the side of the rear plate 1 away from the docking ring 2. The docking ring 2 is used for guiding and limiting the two satellites during docking. A screw 3 is threadedly inserted on the side of the rear plate 1 close to the docking ring 2, and one end of the screw 3 is fixedly connected to the docking ring 2.

[0032] In the present invention, an iron plate 4 is slidably sleeved on the screw 3, a rear cover 5 is provided between the iron plate 4 and the rear plate 1, and a threaded opening corresponding to the screw 3 is provided on the rear cover 5. An electromagnet 6 is fixedly connected to the side of the docking ring 2 away from the rear plate 1;

[0033] In the present invention, a spring 7 is sleeved on the screw rod 3, and the two ends of the spring 7 are respectively against the iron plate 4 and the docking ring 2. A disc spring 8 is inserted into the rear cover 5, and the two ends of the disc spring 8 are respectively fixedly connected to the rear cover 5 and the iron plate 4. After the docking is completed, the hook 11 squeezes the rear cover 5, compressing the disc spring 8 to apply a pre-tightening force;

[0034] In the present invention, a plurality of connecting blocks 10 are rotatably connected to the four sides of the rear plate 1 by means of a pin 9. A hook 11 is slidably connected to the end of the connecting block 10 away from the rear plate 1 for holding the rear cover 5. A guide groove corresponding to the hook 11 is provided on the connecting block 10. A plurality of outer flaps 18 are provided around the side of the docking ring 2 close to the electromagnet 6 for generating a guiding effect and correcting the relative displacement and angular deviation of the two satellites. A groove corresponding to the hook 11 is provided on the outer flap 18 and the docking ring 2.

[0035] In the present invention, a connecting shaft 12 is fixedly connected to the hook 11, and an arc-shaped guide groove 13 corresponding to the connecting shaft 12 is provided on the rear plate 1. Both ends of the connecting shaft 12 are rotatably connected to a rocker 14. The end of the rocker 14 away from the connecting shaft 12 is rotatably connected to a first connecting rod 16 and a second connecting rod 17 through a rotating shaft 15.

[0036] In the present invention, a first rotation groove corresponding to the first connecting rod 16 is provided around the docking ring 2, and a second rotation groove corresponding to the second connecting rod 17 is provided around the iron plate 4. The end of the first connecting rod 16 away from the connecting shaft 12 is rotatably connected to the docking ring 2, and the second connecting rod 17 is rotatably connected to the iron plate 4.

[0037] In the present invention, the two satellites move to the docking position under the action of traditional propulsion means or inertia. At this time, the electromagnetic device is not powered, there is no attraction between the two satellites, and the claws are in an initial embraced state.

[0038] After reaching the effective docking position, the electromagnetic device is energized, and an electromagnetic force is generated between the two satellites to attract each other. At the same time, the iron disk 4 is attracted by the electromagnets 6 of the two satellites, driving the connecting rod mechanism to open the hook 11, and the docking process begins.

[0039] Then the electromagnetic device is continuously powered on. Due to the slight deviation of the initial position and attitude, the outer flaps 18 of the two docking rings 2 partially contact and produce a guiding effect, correcting the relative displacement and angular deviation of the two satellites.

[0040] During the docking process, if the docking speed is too fast, in order to avoid excessive docking impact and mechanical damage to the electromagnetic docking device and the micro-nano satellite, the electromagnetic device at one end can be powered in reverse to obtain the opposite electromagnetic thrust, and reverse acceleration can be used to reduce the docking speed. When the distance is close, the power can be applied in the forward direction to allow the two satellites to adhere to each other.

[0041] After the fit, the locking operation begins. The electromagnetic device reduces the current, and the iron disk 4 is pulled back by the spring 7. At the same time, the connecting rod mechanism is driven to engage the hook 11. Due to the limitation of the arc guide groove 13 in the connecting rod mechanism, the hook 11 will continue to retract after engagement until it hooks the rear cover 5 and applies a pre-tightening force on the disc spring 8. At this time, the connecting rod mechanism is in the self-locking position, the docking and locking are completed, the two satellites can be regarded as a whole, and the mission operation can be carried out.

[0042] The unlocking and separation methods are basically the same as the docking process. First, the electromagnetic device is energized to make the two satellites attract each other so that the claw 11 is unlocked. The claw 11 opens under the action of the iron disk 4 and the connecting rod mechanism. Then the electromagnetic device at one end is energized in the reverse direction to provide electromagnetic repulsion to push the two satellites apart. Then the electromagnetic device is powered off, and the two satellites each complete their respective tasks or conduct another docking.

[0043] In the present invention, the docking device has the advantages of simple structure, no plume pollution, weak impact, etc., which solves the problems of long and slow response in space scientific research and combat mission processes. It can realize the function of repeated rapid docking and separation in orbit, and meet the complex, flexible and changeable mission requirements with timeliness.

[0044] The above description is only a preferred specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any technician familiar with the technical field, within the technical scope disclosed by the present invention, who makes equivalent replacements or changes based on the technical solution and inventive concept of the present invention, should be covered by the scope of protection of the present invention.

Claims

1. An electromagnetic docking device for an on-orbit assembly of a micro-nano satellite, comprising a rear plate (1) and a docking ring (2), characterized in that: A screw rod (3) is threadedly inserted on one side of the rear plate (1) close to the docking ring (2), one end of the screw rod (3) is fixedly connected to the docking ring (2), an iron plate (4) is slidably sleeved on the screw rod (3), a rear cover (5) is provided between the iron plate (4) and the rear plate (1), and a threaded opening corresponding to the screw rod (3) is provided on the rear cover (5), and an electromagnet (6) is fixedly connected to the side of the docking ring (2) away from the rear plate (1); A spring (7) is sleeved on the screw rod (3), and the two ends of the spring (7) are respectively against the iron plate (4) and the docking ring (2); a disc spring (8) is inserted into the rear cover (5), and the two ends of the disc spring (8) are respectively fixedly connected to the rear cover (5) and the iron plate (4); The rear plate (1) is rotatably connected to a plurality of connecting blocks (10) around the periphery via pins (9); the connecting block (10) is slidably connected to a hook (11) at one end away from the rear plate (1); the hook (11) is fixedly connected to a connecting shaft (12); an arc guide groove (13) corresponding to the connecting shaft (12) is provided on the rear plate (1); both ends of the connecting shaft (12) are rotatably connected to rockers (14); the end of the rocker (14) away from the connecting shaft (12) is rotatably connected to a first connecting rod (16) and a second connecting rod (17) via a rotating shaft (15); the end of the first connecting rod (16) away from the connecting shaft (12) is rotatably connected to the docking ring (2); and the second connecting rod (17) is rotatably connected to the iron plate (4).

2. The electromagnetic docking device for in-orbit assembly of micro-nano satellites according to claim 1, characterized in that: A plurality of outer flaps (18) are provided around one side of the docking ring (2) close to the electromagnet (6), and grooves corresponding to the hook claws (11) are provided on both the outer flaps (18) and the docking ring (2).

3. The electromagnetic docking device for in-orbit assembly of micro-nano satellites according to claim 1, characterized in that: The connecting block (10) is provided with a guide groove corresponding to the hook claw (11).

4. The electromagnetic docking device for in-orbit assembly of micro-nano satellites according to claim 1, characterized in that: The rear plate (1) is hollow.

5. The electromagnetic docking device for in-orbit assembly of micro-nano satellites according to claim 1, characterized in that: The docking ring (2) is surrounded by a first rotation groove corresponding to the first connecting rod (16).

6. The electromagnetic docking device for in-orbit assembly of micro-nano satellites according to claim 1, characterized in that: The iron plate (4) is surrounded by a second rotation groove corresponding to the second connecting rod (17).

7. The electromagnetic docking device for in-orbit assembly of micro-nano satellites according to claim 1, characterized in that: A plurality of fastening openings are provided on a side of the rear plate (1) away from the docking ring (2).

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