Spacecraft space rendezvous and docking structure and spacecraft

Abstract

The utility model provides a spacecraft space rendezvous and docking structure and a spacecraft, and relates to the technical field of spacecraft parts, the spacecraft space rendezvous and docking structure comprises a first docking piece, a second docking piece, a guide structure and a buffer structure, the first docking piece is used for being installed on a spacecraft body, and the second docking piece is used for being installed on the spacecraft body. The second butt joint piece is used for being installed on a body of another spacecraft. The first butt-joint piece is provided with a butt-joint part, the guide structure is arranged on the edge of the butt-joint part, and when the second butt-joint piece is close to the first butt-joint piece, the guide structure abuts against the edge of the second butt-joint piece so that the second butt-joint piece can move along the guide structure; the buffer structure is installed on the butt joint part, and when the second butt joint piece is close to the first butt joint piece, the buffer structure abuts against the second butt joint piece and is used for being pressed and shrunk. According to the spacecraft space rendezvous and docking structure, the guiding function and the buffering function can be achieved through the guiding structure and the buffering structure respectively, and the stability of a spacecraft in the space interaction docking process is effectively guaranteed.

Description

Technical Field

[0001] The utility model relates to the technical field of spacecraft parts, and in particular to a spacecraft space rendezvous and docking structure and a spacecraft. Background Art

[0002] Space rendezvous and docking is the process of spacecraft achieving orbital rendezvous and completing docking. It is a prerequisite for realizing on-orbit services such as space assembly, recovery, replenishment, maintenance, astronaut exchange and rescue of space stations, space shuttles, space platforms and space transportation systems. Space rendezvous and docking technology is also one of the three basic technologies for manned space activities.

[0003] Currently, spacecraft are equipped with docking devices to facilitate docking, connection, and separation between spacecraft. These devices connect the mechanical, electrical, and hydraulic circuits of two spacecraft, making their structures relatively sophisticated. However, when the docking devices of two spacecraft approach each other, inertial forces can easily generate impact forces between them, which can damage the delicate structures of the docking devices and affect the stability of the spacecraft during the interactive docking process. Utility Model Content

[0004] The problem solved by the utility model is how to ensure the stability of a spacecraft during space rendezvous and docking.

[0005] In order to solve the above problems, the utility model provides a spacecraft space rendezvous and docking structure and a spacecraft.

[0006] In the first aspect, the utility model provides a spacecraft space rendezvous and docking structure, including a first docking member, a second docking member, a guide structure and a buffer structure, the first docking member is used to be installed on the body of a spacecraft, and the second docking member is used to be installed on the body of another spacecraft; the first docking member is provided with a docking portion, and the guide structure is provided at the edge of the docking portion, and when the second docking member approaches the first docking member, the guide structure is abutted against the edge of the second docking member to enable the second docking member to move along the guide structure; the buffer structure is installed on the docking portion, and when the second docking member approaches the first docking member, the buffer structure is abutted against the second docking member and is used to shrink under pressure.

[0007] Optionally, the first docking member and the second docking member are both annular structures, the docking portion includes an annular groove, the annular groove is provided on the end surface of the first docking member facing the second docking member, the buffer structure is installed in the annular groove, the guide structure is located at the opening edge of the annular groove, and the second docking member is used to move into the annular groove and fit with the groove wall of the annular groove.

[0008] Optionally, an elastic member is provided on the second docking member, and the elastic member is provided on the end surface of the second docking member facing the first docking member. When the second docking member moves into the annular groove, the elastic member and the buffer structure are alternately arranged along the circumference of the annular groove.

[0009] Optionally, the guide structure has a plurality of guide plates, which are arranged at intervals along the circumference of the annular groove, and the guide plates have a first end and a second end that are opposite to each other, the first end is movably connected to the first docking piece, and the second end is used to deflect toward or away from the central axis of the annular groove relative to the first end.

[0010] Optionally, the buffer structure includes a protective shell, a force-bearing seat, a moving rod, a first magnetic member and a second magnetic member. A moving groove is provided in the protective shell, the first magnetic member is slidably installed in the moving groove, and the second magnetic member is fixedly installed in the moving groove. The first magnetic member and the second magnetic member repel each other. The force-bearing seat is located outside the protective shell and is connected to the moving rod. The moving rod penetrates the protective shell and is connected to the first magnetic member. The force-bearing seat is used to resist the second docking member to receive force through the moving rod to drive the first magnetic member to move toward the second magnetic member.

[0011] Optionally, the first magnetic member and the second magnetic member have the same magnetism at two ends close to each other and the same magnetism at two ends facing away from each other; a movable hole is provided through the second magnetic member, and the first magnetic member is used to receive force and pass through the movable hole.

[0012] Optionally, the buffer structure also includes a reset member, which is installed in the movable groove and is located on the side of the second magnetic member facing away from the first magnetic member. When the first magnetic member is forced to pass through the movable hole, the reset member is used to drive the first magnetic member to move toward the movable hole and pass through the movable hole.

[0013] Optionally, there are multiple buffer structures, and the multiple buffer structures are evenly distributed on the docking portion.

[0014] Optionally, the buffer structure has multiple groups, each group has multiple buffer structures, and the multiple groups of buffer structures are evenly distributed on the docking part. The multiple buffer structures in the same group are stacked along the direction from the first docking piece to the second docking piece.

[0015] In a second aspect, the present invention provides a spacecraft, including a spacecraft space rendezvous and docking structure as described above.

[0016] The beneficial effects of the spacecraft space rendezvous and docking structure of the present utility model are as follows: a first docking member, a second docking member, a guide structure and a buffer structure are provided to form a spacecraft space rendezvous and docking structure, wherein the first docking member can be installed on the body of one spacecraft, and the second docking member can be installed on the body of another spacecraft, and when the two spacecraft approach each other, the first docking member and the second docking member approach each other, and at the same time, the guide structure is provided on the edge of the docking portion of the first docking member, and when the first docking member and the second docking member approach each other, the guide structure can be abutted against the edge of the second docking member, and the guide structure can be used to guide the second docking member to move toward the docking portion, thereby making the second docking member The second docking part can be moved to the docking part to complete the docking of the two spacecraft accurately, and the second docking part can be moved to the docking part to complete the docking of the two spacecraft, thereby ensuring the accuracy of the spacecraft during space rendezvous and docking; on this basis, the buffer structure is installed on the docking part, and when the second docking part approaches the first docking part, the buffer structure can be offset against the second docking part, and the buffer structure can be contracted under force. The buffer structure can absorb the impact force when the second docking part moves toward the first docking part by contraction, thereby avoiding damage to the precision structure of the docking part when the two spacecraft are docked. At the same time, the contraction of the buffer structure avoids obstruction to the movement of the second docking part, thereby effectively ensuring the stability of the spacecraft during the interactive docking process in space. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a schematic diagram of the docking of a spacecraft in an embodiment of the present utility model;

[0018] Figure 2 This is a schematic diagram of the docking of the first docking member and the second docking member in an embodiment of the present utility model;

[0019] Figure 3 This is a structural diagram of the first docking member in the embodiment of the present utility model when docking is completed;

[0020] Figure 4 Schematic diagram of the structure of the buffer structure in the embodiment of the present utility model.

[0021] Description of reference numerals:

[0022] 1. First docking member; 11. Docking portion; 2. Second docking member; 21. Elastic member; 3. Guide structure; 4. Buffer structure; 41. Protective shell; 411. Moving groove; 42. Force seat; 43. Moving rod; 44. First magnetic member; 45. Second magnetic member; 451. Moving hole; 46. Reset member; 5. Main body. DETAILED DESCRIPTION

[0023] To make the above-mentioned objects, features, and advantages of the present invention more clearly understood, specific embodiments of the present invention are described in detail below with reference to the accompanying drawings. Although certain embodiments of the present invention are shown in the accompanying drawings, it should be understood that the present invention can be implemented in various forms and should not be construed as being limited to the embodiments described herein. Instead, these embodiments are provided to provide a more thorough and complete understanding of the present invention. It should be understood that the drawings and embodiments of the present invention are for illustrative purposes only and are not intended to limit the scope of protection of the present invention.

[0024] The term "including" and its variations used in this document are open inclusions, that is, "including but not limited to"; the term "based on" means "at least partially based on"; the term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one other embodiment"; the term "some embodiments" means "at least some embodiments"; the term "optionally" means "optional embodiments". The relevant definitions of other terms will be given in the following description. It should be noted that the concepts of "first", "second", etc. mentioned in this utility model are only used to distinguish different devices, modules or units, and are not used to limit the order or interdependence of the functions performed by these devices, modules or units.

[0025] It should be noted that the modifications of "one" and "multiple" mentioned in the present invention are illustrative rather than restrictive. Those skilled in the art should understand that unless otherwise clearly indicated in the context, it should be understood as "one or more".

[0026] like Figure 1 、 Figure 2 and Figure 3 As shown, an embodiment of the utility model provides a spacecraft space rendezvous and docking structure, including a first docking member 1, a second docking member 2, a guide structure 3 and a buffer structure 4. The first docking member 1 is used to be installed on the body 5 of a spacecraft, and the second docking member 2 is used to be installed on the body 5 of another spacecraft; the first docking member 1 is provided with a docking portion 11, and the guide structure 3 is provided at the edge of the docking portion 11. When the second docking member 2 approaches the first docking member 1, the guide structure 3 abuts against the edge of the second docking member 2 to enable the second docking member 2 to move along the guide structure 3; the buffer structure 4 is installed on the docking portion 11. When the second docking member 2 approaches the first docking member 1, the buffer structure 4 abuts against the second docking member 2 and is used to shrink under pressure.

[0027] Specifically, the buffer structure 4 can be a mechanical buffer device, such as a spring buffer, which can use the elastic deformation of the spring to absorb and buffer the collision energy; it can also be a hydraulic damper, which can absorb energy through the flow and compression of hydraulic oil inside the damper; it can also be an airbag buffer device, such as an airbag buffer, which can use the expansion and compression of the inflatable airbag during a collision to absorb energy; it can also be a magnetorheological and electrorheological buffer device, such as a magnetorheological damper, which can use the viscosity change of magnetorheological fluid under the action of a magnetic field to achieve damping force adjustment and energy absorption.

[0028] In this embodiment, Figure 2 As shown, a first docking member 1, a second docking member 2, a guide structure 3 and a buffer structure 4 are provided to form a spacecraft space rendezvous and docking structure, wherein, as Figure 1 As shown, the first docking member 1 can be installed on the body 5 of one spacecraft, and the second docking member 2 can be installed on the body 5 of another spacecraft. In this arrangement, when the two spacecraft approach each other, the first docking member 1 and the second docking member 2 approach each other. At the same time, the guide structure 3 is provided on the edge of the docking portion 11 on the first docking member 1. When the first docking member 1 and the second docking member 2 approach each other, the guide structure 3 can abut against the edge of the second docking member 2. In this arrangement, Figure 2 and Figure 3 As shown, the guide structure 3 can be used to guide the second docking member 2 to move toward the docking portion 11, so that the second docking member 2 can accurately approach the docking portion 11, and finally the docking of the two spacecraft is completed when the second docking member 2 moves to the docking portion 11, thereby ensuring the accuracy of the spacecraft during space rendezvous and docking; on this basis, the buffer structure 4 is installed on the docking portion 11, and when the second docking member 2 approaches the first docking member 1, the buffer structure 4 can be offset against the second docking member 2, and the buffer structure 4 can be forced to shrink. In this way, the buffer structure 4 can absorb the impact force when the second docking member 2 moves toward the first docking member 1 by shrinking, thereby avoiding damage to the precision structure of the docking point when the two spacecraft dock. At the same time, the contraction of the buffer structure 4 avoids obstruction to the movement of the second docking member 2, effectively ensuring the stability of the spacecraft during the interactive docking process in space.

[0029] Alternatively, as Figure 2 As shown, the first docking member 1 and the second docking member 2 are both annular structures, the docking portion 11 includes an annular groove, the annular groove is provided on the end face of the first docking member 1 facing the second docking member 2, the buffer structure 4 is installed in the annular groove, the guide structure 3 is located at the opening edge of the annular groove, and the second docking member 2 is used to move into the annular groove and fit with the groove wall of the annular groove.

[0030] Specifically, if Figure 2As shown, the cross-sectional profile shapes of the annular structures of the first docking member 1 and the second docking member 2 are both circular. Of course, the cross-sectional profile shapes of the annular structures of the first docking member 1 and the second docking member 2 can also be polygonal; the cross-sectional profile shape of the annular groove is the same as the cross-sectional profile shape of the second docking member 2, that is, both are circular. At this time, the bottom wall and side wall of the annular groove are both in contact with the second docking member 2, or they can be different. For example, if the cross-sectional profile shape of the annular groove is polygonal, it is only necessary to ensure that the second docking member 2 can be moved into the annular groove. At this time, the bottom wall of the annular groove is in contact with the second docking member 2; the annular groove is coaxially arranged with the first docking member 1, and a center hole is provided in the middle of the first docking member 1, and the edge of the center hole is recessed to form an annular groove. Of course, the annular groove can also be coaxially arranged with the first docking member 1, as long as it is ensured that the first docking member 1 faces the end surface of the second docking member 2.

[0031] In this optional embodiment, if Figure 2 As shown, in order to ensure the stable alignment of the first butt joint member 1 and the second butt joint member 2, the first butt joint member 1 and the second butt joint member 2 are set as an annular structure. In this way, when the first butt joint member 1 and the second butt joint member 2 approach each other, the direction of movement can be controlled to be parallel to the central axis of the annular structure, ensuring that the contact area of ​​the first butt joint member 1 and the second butt joint member 2 when they abut against each other is large, thereby improving the stability of the alignment of the two. On this basis, the butt joint portion 11 of the first butt joint member 1 is set as an annular groove, which is on the end surface of the first butt joint member 1 facing the second butt joint member 2, and the second butt joint member 2 can be moved into the annular groove and then fit into the groove wall of the annular groove. In this way, in the first butt joint member 1, the second butt joint member 2 can be moved into the annular groove and then fit into the groove wall of the annular groove. After one docking part 1 approaches the second docking part 2, it can be directly placed in the annular groove. The groove wall of the annular groove is used to limit the movement of the second docking part 2 to ensure that it is moved into place and to avoid offset, thereby improving the accuracy of the alignment; at the same time, the buffer structure 4 is installed in the annular groove, and the guide structure 3 is located at the opening edge of the annular groove. In this way, before the second docking part 2 moves into the annular groove, the guidance of the guide structure 3 can ensure that the second docking part 2 can be accurately moved into the annular groove, and after the second docking part 2 moves into the annular groove, the compression buffering of the buffer structure 4 can be used to reduce the impact force of the second docking part 2, thereby ensuring the stability of the spacecraft during the interactive docking process in space.

[0032] Alternatively, as Figure 2 and Figure 3 As shown, the second docking member 2 is provided with an elastic member 21, which is provided on the end surface of the second docking member 2 facing the first docking member 1. When the second docking member 2 moves into the annular groove, the elastic member 21 and the buffer structure 4 are alternately arranged along the circumference of the annular groove.

[0033] Specifically, the elastic member 21 may be elastic rubber, or a spring or the like; Figure 2As shown, the elastic member 21 can be arranged in an arc shape around the axial direction of the second docking member 2, or can be distributed in a block shape on the second docking member 2. Of course, the buffer structure 4 can also be arranged in an arc shape around the axial direction of the first docking member 1, or can be distributed in a block shape in the annular groove. It only needs to ensure that when the second docking member 2 moves into the annular groove, the elastic member 21 and the buffer structure 4 are staggered.

[0034] In this optional embodiment, an elastic member 21 is provided on the second docking member 2, and the elastic member 21 can be compressed, wherein the elastic member 21 is provided on the end surface of the second docking member 2 facing the first docking member 1, so that when the second docking member 2 moves into the annular groove, the elastic member 21 can be pressed against the groove wall of the annular groove and compressed, and the elastic member 21 can effectively absorb the impact energy of the second docking member 2 while being compressed, thereby effectively reducing the impact force of the second docking member 2 and improving the stability of the spacecraft during the space interactive docking process; at the same time, when the second docking member 2 moves into the annular groove, the elastic member 21 and the buffer structure 4 are alternately arranged along the circumference of the annular groove. In this way, since the elastic member 21 can be pressed against the groove bottom wall of the annular groove Therefore, the elastic member 21 can cooperate with the buffer structure 4 to cover the bottom wall of the annular groove, and then the buffer structure 4 and the elastic member 21 can cooperate to buffer the second docking member 2, further reducing the impact force of the second docking member 2, and effectively improving the stability of the spacecraft during the space interactive docking process; on this basis, preferably, when the elastic member 21 is compressed, the height of the elastic member 21 is the same as the height of the compressed and contracted buffer structure 4. After the second docking member 2 moves into place, the elastic member 21 and the buffer structure 4 can also be fully compressed into place to ensure the buffering effect, while facilitating the second docking member 2 to move smoothly into the annular groove, avoiding the tilt of the second docking member 2 due to uneven distribution of buffering force.

[0035] Alternatively, as Figure 2 and Figure 3 As shown, the guide structure 3 has a plurality of guide plates, which are arranged at intervals along the circumference of the annular groove. The guide plates have a first end and a second end that are opposite to each other. The first end is movably connected to the first docking member 1, and the second end is used to deflect toward or away from the central axis of the annular groove relative to the first end.

[0036] Specifically, if Figure 2 and Figure 3 As shown, along the axial direction of the first docking member 1 , that is, the center axis direction of the annular groove, the dimension of the guide plate close to the first docking member 1 is smaller than the dimension away from the first docking member 1 .

[0037] In this optional embodiment, if Figure 2 and Figure 3As shown, a plurality of guide plates are provided to form a guide structure 3, wherein the plurality of guide plates are arranged at intervals along the circumference of the annular groove. In this way, when the second docking piece 2 approaches the first docking piece 1, multiple edges of the second docking piece 2 can respectively abut against the plurality of guide plates, and move toward the docking portion 11 under the guidance of the plurality of guide plates, thereby avoiding misalignment when the second docking piece 2 approaches the first docking piece 1, effectively improving the guiding effect of the guide structure 3, and ensuring the accuracy of the docking of the first docking piece 1 and the second docking piece 2; on this basis, the guide plate has a first end and a second end that are separated from each other, wherein the first end is movably connected to the first docking piece 1, and the second end can be deflected toward or away from the central axis of the annular groove relative to the first end. In this way, before the second docking piece 2 moves into the annular groove, the second end can be deflected away from the central axis of the annular groove relative to the first end, and the guide structure 3 formed by the plurality of guide plates distributed in an annular manner opens, and when the second docking piece 2 approaches When approaching the first docking member 1, the area of ​​the guide area enclosed by the second end of the guide plate is larger than the area enclosed by the first end, which can effectively reduce the difficulty of aligning and moving the second docking member 2 into the guide area, thereby improving the convenience when the second docking member 2 is docked with the first docking member 1, and can also guide the movement of the second docking member 2 by the inclined guide plate toward the wall surface of the central axis of the annular groove, thereby playing a stable guiding role; at the same time, when the second docking member 2 moves into the annular groove, the second end can be deflected toward the central axis of the annular groove relative to the first end, that is, after the second docking member 2 moves into the annular groove, the guide structure 3 composed of multiple guide plates distributed in an annular shape changes from open to closed. At this time, the area enclosed by the second end is smaller than the area enclosed by the first end, and the second docking member 2 can be restricted by the wall surface of the inclined guide plate toward the central axis of the annular groove to prevent the second docking member 2 from moving toward the direction of the first docking member 1 and accidentally detaching from the first docking member 1.

[0038] Alternatively, as Figure 4 As shown, the buffer structure 4 includes a protective shell 41, a force-bearing seat 42, a moving rod 43, a first magnetic member 44 and a second magnetic member 45. A moving groove 411 is provided in the protective shell 41. The first magnetic member 44 is slidably installed in the moving groove 411, and the second magnetic member 45 is fixedly installed in the moving groove 411. The first magnetic member 44 and the second magnetic member 45 repel each other. The force-bearing seat 42 is located outside the protective shell 41 and is connected to the moving rod 43. The moving rod 43 penetrates the protective shell 41 and is connected to the first magnetic member 44. The force-bearing seat 42 is used to resist the second docking member 2, so as to receive force through the moving rod 43 to drive the first magnetic member 44 toward the second magnetic member 45.

[0039] Specifically, if Figure 4As shown, the cross-sectional shapes of the protective shell 41, the force-bearing seat 42, the movable rod 43, the first magnetic member 44 and the second magnetic member 45 are all circular; the first magnetic member 44 and the second magnetic member 45 are both magnets; the first magnetic member 44 and the second magnetic member 45 repel each other, and the magnetic polarity of the end of the first magnetic member 44 facing the second magnetic member 45 can be the same as the magnetic polarity of the end of the second magnetic member 45 facing the first magnetic member 44, for example, both are N poles or both are S poles, and the magnetic induction intensity of the first magnetic member 44 and the second magnetic member 45 can be adjusted, thereby adjusting the magnitude of the repulsive force between the first magnetic member 44 and the second magnetic member 45.

[0040] In this optional embodiment, if Figure 4 As shown, a protective shell 41, a force-bearing seat 42, a moving rod 43, a first magnetic member 44 and a second magnetic member 45 are provided to form a buffer structure 4, wherein a moving groove 411 is provided in the protective shell 41, and the first magnetic member 44 is slidably installed in the moving groove 411, and the second magnetic member 45 is fixedly installed in the moving groove 411, and the first magnetic member 44 and the second magnetic member 45 repel each other. In this way, when the first magnetic member 44 and the second magnetic member 45 approach each other, the impact force transmitted by the second docking member 2 that drives the two to approach each other needs to overcome the repulsive force between the two to do work, and then convert it into potential stored between the two. On this basis, the force-bearing seat 42 is located outside the protective shell 41 and is connected to the moving rod 43. The moving rod 43 penetrates the protective shell 41 and is connected to the first magnetic member 44. The force-bearing seat 42 is used to resist the second docking member 2, so as to drive the first magnetic member 44 toward the second magnetic member 45 through the moving rod 43. With this arrangement, when the buffer structure 4 is compressed and contracted, the first magnetic member 44 can move toward the second magnetic member 45, thereby absorbing the impact force transmitted to the buffer structure 4 by the second docking member 2, thereby ensuring the stability of the spacecraft during the interactive docking process in space.

[0041] Alternatively, as Figure 4 As shown, the first magnetic member 44 and the second magnetic member 45 have the same magnetism at the two ends close to each other and the same magnetism at the two ends facing away from each other. A movable hole 451 is provided through the second magnetic member 45, and the first magnetic member 44 is used to receive force and pass through the movable hole 451.

[0042] Specifically, the first magnetic member 44 and the second magnetic member 45 are magnets with opposite magnetic poles at both ends. The upper end of the first magnetic member 44 is an N pole and the lower end is an S pole, while the upper end of the second magnetic member 45 is an S pole and the lower end is an N pole.

[0043] In this optional embodiment, if Figure 4As shown, the two ends of the first magnetic member 44 and the second magnetic member 45 that are close to each other have the same magnetic properties. In this way, when the second docking member 2 moves and pushes the first magnetic member 44 toward the second magnetic member 45, the impact force transmitted to the buffer structure 4 by the second docking member 2 overcomes the repulsive force and does work and is converted into potential energy between the first magnetic member 44 and the second magnetic member 45. As the second docking member 2 continues to move, the first magnetic member 44 penetrates the moving hole 451 on the second magnetic member 45. At this time, the potential energy stored between the first magnetic member 44 and the second magnetic member 45 reaches the maximum, and the buffering effect on the second docking member 2 is optimal. The purpose of buffering has been achieved. If the second docking member 2 continues to move and the first magnetic member When 44 passes through the movable hole 451, since the magnetism of the two opposite ends of the first magnetic part 44 is opposite, and the magnetism of the two opposite ends of the second magnetic part 45 is opposite, the first magnetic part 44 continues to move downward under the action of the impact force of the second docking part 2 and the repulsive force of the second magnetic part 45. At this time, the potential energy stored between the first magnetic part 44 and the second magnetic part 45 is released to the first docking part 1, avoiding the storage of the potential energy from having an adverse effect on the structure of the buffer structure 4, ensuring the service life of the buffer structure 4, and during the later maintenance of the buffer structure 4, it is only necessary to move the first magnetic part 44 through the movable hole 451 again to the initial position to restore the buffer function of the buffer structure 4, and the maintenance convenience is better.

[0044] Alternatively, as Figure 4 As shown, the buffer structure 4 also includes a reset member 46, which is installed in the movable groove 411 and is located on the side of the second magnetic member 45 away from the first magnetic member 44. When the first magnetic member 44 is forced to pass through the movable hole 451, the reset member 46 is used to drive the first magnetic member 44 to move toward the movable hole 451 and pass through the movable hole 451.

[0045] Specifically, the reset element 46 can be an airbag that is driven by expanding and deflating through inflation and deflation, or it can be a magnetic element that drives the first magnetic element 44 by causing magnetism to disappear and recover through power on and off.

[0046] In this optional embodiment, a reset member 46 is provided in the protective shell 41 of the buffer structure 4. The reset member 46 is installed in the movable groove 411 and is located on the side of the second magnetic member 45 away from the first magnetic member 44. When the first magnetic member 44 is forced to pass through the movable hole 451, the reset member 46 can drive the first magnetic member 44 to move toward the movable hole 451 and pass through the movable hole 451. In this arrangement, during the later maintenance of the buffer structure 4, it is only necessary to turn on the driving function of the reset member 46 to drive the first magnetic member 44 to pass through the movable hole 451 again to the initial position to restore the buffer function of the buffer structure 4, thereby further improving the maintenance convenience of the buffer structure 4.

[0047] Alternatively, as Figure 2As shown, there are multiple buffer structures 4 , and the multiple buffer structures 4 are evenly distributed on the docking portion 11 .

[0048] Specifically, if Figure 2 As shown, there are three buffer structures 4 , which are evenly spaced around the center of the docking portion 11 .

[0049] In this optional embodiment, a plurality of buffer structures 4 are provided, thereby further improving the buffering effect on the second docking member 2 by increasing the number of buffer structures 4; on this basis, a plurality of buffer structures 4 are evenly distributed on the docking portion 11. Such a setting can ensure the uniformity of buffering the second docking member 2, thereby ensuring the stability of the movement of the second docking member 2 and avoiding the second docking member 2 from tilting.

[0050] Alternatively, as Figure 2 As shown, there are multiple groups of buffer structures 4, each group has multiple buffer structures 4, and the multiple groups of buffer structures 4 are evenly distributed on the docking portion 11. The multiple buffer structures 4 in the same group are stacked along the direction from the first docking piece 1 to the second docking piece 2.

[0051] Specifically, if Figure 2 As shown, there are three groups of buffer structures 4 , which are evenly spaced around the center of the docking portion 11 , and each group of buffer structures 4 has at least two buffer structures 4 .

[0052] In this optional embodiment, if Figure 2 As shown, the buffer structures 4 are arranged into multiple groups, and each group has multiple buffer structures 4. This arrangement can ensure the buffering performance of each group of buffer structures 4; on this basis, multiple groups of buffer structures 4 are evenly distributed on the docking part 11, and multiple buffer structures 4 of the same group are stacked along the direction from the first docking part 1 to the second docking part 2. This arrangement can ensure the buffering performance of each group of buffer structures 4 while ensuring the uniformity of buffering the second docking part 2, thereby ensuring the stability of the movement of the second docking part 2 and avoiding the second docking part 2 from tilting.

[0053] An embodiment of the present utility model further provides a spacecraft, comprising a body 5 and the above-mentioned spacecraft space rendezvous and docking structure.

[0054] The beneficial effects of the spacecraft of this embodiment relative to the prior art are the same as those of the above-mentioned spacecraft space rendezvous and docking structure, and will not be described in detail here.

[0055] Although the present invention is disclosed as above, the protection scope of the present invention is not limited thereto. Those skilled in the art may make various changes and modifications without departing from the spirit and scope of the present invention, and these changes and modifications will fall within the protection scope of the present invention.

Claims

1. A spacecraft space rendezvous and docking structure, characterized in that: The invention comprises a first docking member (1), a second docking member (2), a guide structure (3) and a buffer structure (4), wherein the first docking member (1) is used to be installed on a body (5) of a spacecraft, and the second docking member (2) is used to be installed on the body (5) of another spacecraft; the first docking member (1) is provided with a docking portion (11), the guide structure (3) is provided at the edge of the docking portion (11), and when the second docking member (2) approaches the first docking member (1), the guide structure (3) abuts against the edge of the second docking member (2) so that the second docking member (2) moves along the guide structure (3); the buffer structure (4) is installed on the docking portion (11), and when the second docking member (2) approaches the first docking member (1), the buffer structure (4) abuts against the second docking member (2) and is used to shrink under pressure.

2. The spacecraft space rendezvous and docking structure according to claim 1, characterized in that: The first docking member (1) and the second docking member (2) are both annular structures. The docking portion (11) includes an annular groove, which is provided on the end surface of the first docking member (1) facing the second docking member (2). The buffer structure (4) is installed in the annular groove. The guide structure (3) is located at the opening edge of the annular groove. The second docking member (2) is used to move into the annular groove and fit with the groove wall of the annular groove.

3. The spacecraft space rendezvous and docking structure according to claim 2, characterized in that: An elastic member (21) is provided on the second docking member (2), and the elastic member (21) is provided on the end surface of the second docking member (2) facing the first docking member (1). When the second docking member (2) moves into the annular groove, the elastic member (21) and the buffer structure (4) are alternately arranged along the circumference of the annular groove.

4. The spacecraft space rendezvous and docking structure according to claim 2, characterized in that: The guide structure (3) has a plurality of guide plates, which are arranged at intervals along the circumference of the annular groove. The guide plates have a first end and a second end that are separated from each other. The first end is movably connected to the first docking member (1), and the second end is used to deflect toward or away from the central axis of the annular groove relative to the first end.

5. The spacecraft space rendezvous and docking structure according to any one of claims 1 to 4, characterized in that: The buffer structure (4) includes a protective shell (41), a force-bearing seat (42), a moving rod (43), a first magnetic member (44) and a second magnetic member (45). A moving groove (411) is provided in the protective shell (41). The first magnetic member (44) is slidably installed in the moving groove (411). The second magnetic member (45) is fixedly installed in the moving groove (411). The first magnetic member (44) and the second magnetic member (45) repel each other. The force-bearing seat (42) is located outside the protective shell (41) and is connected to the moving rod (43). The moving rod (43) penetrates the protective shell (41) and is connected to the first magnetic member (44). The force-bearing seat (42) is used to resist the second docking member (2) so as to receive force through the moving rod (43) to drive the first magnetic member (44) to move toward the second magnetic member (45).

6. The spacecraft space rendezvous and docking structure according to claim 5, characterized in that: The first magnetic member (44) and the second magnetic member (45) have the same magnetism at two ends close to each other and the same magnetism at two ends facing away from each other. A movable hole (451) is provided through the second magnetic member (45), and the first magnetic member (44) is used to receive force and pass through the movable hole (451).

7. The spacecraft space rendezvous and docking structure according to claim 6, characterized in that: The buffer structure (4) further includes a reset member (46), which is installed in the movable groove (411) and is located on the side of the second magnetic member (45) facing away from the first magnetic member (44). When the first magnetic member (44) is forced to pass through the movable hole (451), the reset member (46) is used to drive the first magnetic member (44) to move toward the movable hole (451) and pass through the movable hole (451).

8. The spacecraft space rendezvous and docking structure according to any one of claims 1 to 4, characterized in that: There are multiple buffer structures (4), and the multiple buffer structures (4) are evenly distributed on the docking portion (11).

9. The spacecraft space rendezvous and docking structure according to any one of claims 1 to 4, characterized in that: The buffer structures (4) have multiple groups, each group having multiple buffer structures (4), and the multiple groups of buffer structures (4) are evenly distributed on the docking portion (11). The multiple buffer structures (4) in the same group are stacked and arranged in a direction from the first docking piece (1) to the second docking piece (2).

10. A spacecraft, characterized in that: The spacecraft space rendezvous and docking structure comprises a body (5) as described in any one of claims 1 to 8.

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