Space Net System

Abstract

The present application relates to the field of aerospace equipment technology, and provides a space netting system. The space netting system comprises a spacecraft body, an elastic arm mounted on the spacecraft body, a netting device, and a connecting cable. The elastic arm can be stretched into a straight line to extend to the outside of the spacecraft body, and can be elastically deformed into a spiral coiled shape to be stored on the spacecraft body. The netting device comprises a locking mechanism mounted on the spacecraft body, a rotating arm rotatably connected to the locking mechanism, and a space net having a supporting frame, the supporting frame being connected to the rotating arm, and the rotating arm being capable of driving the space net to move from a locked position to a specified position. The connecting cable is connected between the supporting frame and the elastic arm. When the space net is in the specified position, the rotating arm is restricted from rotating relative to the spacecraft body, and the elastic arm is in an extended state to tension the connecting cable, so that the rotating arm and the connecting cable jointly define the orientation of the space net relative to the spacecraft body, thereby improving the orientation stability of the space net and enhancing the capture effect of the space net.

Description

Technical Field

[0001] The present application relates to the field of aerospace equipment technology, and in particular to a space network system. Background Art

[0002] With the continuous development of human space activities, the number of satellite and other spacecraft launched has increased year by year. While this has brought great convenience to many fields such as modern communications, navigation, and remote sensing, it has also brought about a serious problem of space debris. This high-speed movement and rotation of space debris not only consumes space orbital resources, hindering the normal launch and deployment of spacecraft, but also poses a collision risk to long-term space facilities in orbit, threatening the safety of space facilities and astronauts on board. To solve this problem, research on space debris removal technology is needed. Current space debris capture and removal technology mainly uses space rope nets for flexible capture and removal.

[0003] However, the space rope net is usually stored in a concentric cylindrical flexible rope net storage bag. A flexible rope connected to the satellite is set in the middle of the space rope net, and mass blocks are set at the edge of the space rope net. When the flying net is unfolded, the mass blocks are launched to drive the space rope net to fly out of the storage bag and unfold in space. The launch angle of the mass blocks and the flight speed of different mass blocks will affect the direction of the flying net, making it difficult to control the direction of the flying net when in use and affecting the capture effect. Summary of the Invention

[0004] In order to solve the above technical problems or at least partially solve the above technical problems, the present application provides a space net system.

[0005] This application provides a space network system, including:

[0006] Spacecraft body;

[0007] an elastic arm mounted on the spacecraft body, the elastic arm being capable of stretching into a straight line to extend to the outside of the spacecraft body and elastically deforming into a spiral coil to be accommodated on the spacecraft body;

[0008] A net device comprising a locking mechanism mounted on the spacecraft body, a rotating arm rotatably connected to the locking mechanism, and a space net having a supporting frame, wherein the supporting frame is connected to the rotating arm, and the rotating arm is capable of driving the space net to move from a locking position close to the spacecraft body to a designated position away from the spacecraft body;

[0009] A connecting rope connected between the supporting frame and the elastic arm;

[0010] When the space net is in the designated position, the rotating arm is restricted from rotating relative to the spacecraft body, and the elastic arm is in an extended state to tension the connecting cable, so that the rotating arm and the connecting cable jointly define the orientation of the space net relative to the spacecraft body.

[0011] Optionally, there are multiple elastic arms, a portion of the multiple elastic arms is arranged on the first side of the spacecraft body, and another portion is arranged on the second side of the spacecraft body, the first side and the second side are arranged opposite to each other, the mesh device is arranged between the first side and the second side, each of the elastic arms is connected to the supporting frame through one of the connecting cables, and the connection points of the multiple connecting cables and the supporting frame are spaced apart from each other;

[0012] When the space net is unfolded at the designated position, the plurality of connecting cables are all in a tensioned state.

[0013] Optionally, a storage device is provided on the spacecraft body, and the storage device includes a storage cylinder and a locking assembly;

[0014] One end of the elastic arm is connected to the bottom wall of the storage tube, and the other end is connected to the top plate; when the elastic arm is spirally coiled, it is stored in the storage tube; when the elastic arm is extended, the elastic arm extends out of the storage tube and drives the top plate to move away from the storage tube;

[0015] The locking assembly is mounted on the storage tube. When the locking assembly is locked, it is connected to the top plate to limit the extension of the elastic arm. When the locking assembly is unlocked, it is separated from the top plate to allow the elastic arm to extend and extend out of the storage tube.

[0016] The connecting rope is rotatably connected to the top plate.

[0017] Optionally, the locking assembly includes a locking rod, a base, and a pin puller; the locking rod is connected to the top plate, the base is mounted on the storage tube, the pin puller is mounted on the locking rod, and a positioning hole is provided on the locking rod;

[0018] The pin puller is provided with a retractable pin shaft end. When the locking assembly is locked, the pin shaft end is plugged into the positioning hole to limit the movement of the locking link relative to the base; when the locking assembly is unlocked, the pin shaft end is out of the positioning hole to allow the locking link to move in a direction away from the base.

[0019] Optionally, the storage device further comprises a rotating shaft, a damper and a cable, wherein the rotating shaft is rotatably disposed on the storage cylinder, the damper is connected to the rotating shaft so that the damper provides resistance to the rotation of the rotating shaft, and one end of the cable is connected to the rotating shaft, and the other end is connected to the top plate;

[0020] When the elastic arm is spirally wound, the cable is wound around the rotating shaft. When the elastic arm is stretched, the top plate can be moved in a direction away from the storage tube, so that the cable drives the rotating shaft to rotate.

[0021] Optionally, the storage device further includes a detector, which is mounted on the storage tube and electrically connected to the rotating shaft so that the detector can detect the rotation speed of the rotating shaft.

[0022] Optionally, the elastic arm includes at least three elastic longitudinal rods, each of which is connected between the bottom of the storage tube and the top plate, and the plurality of elastic longitudinal rods are spaced apart around the axis of the storage tube;

[0023] When the elastic arm is extended, the elastic longitudinal rod extends in the direction of the axis of the storage tube; each elastic longitudinal rod is elastically deformed around the axis of the storage tube, and multiple elastic longitudinal rods are bent in the same direction, so that each elastic longitudinal rod is spirally coiled after bending, and multiple elastic longitudinal rods are stacked in sequence in the axial direction of the storage tube.

[0024] Optionally, in the direction around the axis of the storage tube, an elastic cross bar is connected between every two adjacent elastic longitudinal bars, and the elastic cross bar can be elastically deformed when the elastic arms are coiled.

[0025] Optionally, the rotating arm includes a base, a rotating rod and an elastic member;

[0026] The base is mounted on the locking mechanism, the rotating rod is rotatably connected to the base, the edge of the space net is connected to the rotating rod, the elastic member is connected between the base and the rotating rod, and the elastic force of the elastic member drives the rotating rod to rotate in a direction away from the locking mechanism;

[0027] A positioning platform is formed on the top side of the base, and a positioning end is formed on one end of the rotating rod close to the base. When the space net is at the specified position, the positioning end abuts against the positioning platform to limit the rotation of the rotating rod relative to the base.

[0028] And / or, the base is provided with an arcuate portion, the arcuate portion is recessed to form a positioning groove, the rotating rod is provided with a limiting protrusion that can rotate relative to the rotating rod, a spring is connected between the limiting protrusion and the rotating rod, and the spring drives the limiting protrusion to abut against the arcuate portion;

[0029] When the space net is in the locking position, the limiting protrusion abuts against the arc surface and is spaced apart from the positioning groove. When the space net is in the specified position, the limiting protrusion is plugged into the positioning groove to limit the rotation of the rotating rod relative to the base.

[0030] Optionally, the locking mechanism includes a plate assembly and a limiter, the plate assembly is mounted on a surface side of the spacecraft body, the limiter is mounted on a side of the plate assembly away from the spacecraft body, and the rotating arm is mounted on the plate assembly;

[0031] When the space net is in the locked position, the space net is attached to a side of the plate assembly away from the spacecraft body;

[0032] The limiting member can switch between a limiting state and a disengaged state. When in the limiting state, the limiting member abuts against a side of the space net at the locked position facing away from the plate assembly to limit the movement of the space net in a direction away from the plate assembly.

[0033] When the limiting member is in the disengaged state, the limiting member is out of contact with the space net, so that the space net can move to the designated position.

[0034] The technical solution provided by this application has the following advantages compared with the existing technology:

[0035] The present application provides a space netting system, comprising a spacecraft body; an elastic arm installed on the spacecraft body, the elastic arm being able to stretch into a straight line to extend to the outside of the spacecraft body, and being able to elastically deform into a spiral coil to be stored on the spacecraft body; a net device comprising a locking mechanism installed on the spacecraft body, a rotating arm rotatably connected to the locking mechanism, and a space net having a supporting frame, the supporting frame being connected to the rotating arm, the rotating arm being able to drive the space net to move from a locking position close to the spacecraft body to a designated position away from the spacecraft body; a connecting rope connected between the supporting frame and the elastic arm; when the space net is at the designated position, the rotating arm is restricted from rotating relative to the spacecraft body, and the elastic arm is in an extended state to tension the connecting rope, so that the rotating arm and the connecting rope jointly define the orientation of the space net relative to the spacecraft body. The elastic arm, the net device and the connecting cable cooperate with each other so that when the space net is in a specified position, the elastic arm can exert force on the supporting frame of the space net through the connecting cable, and the rotating arm can support the supporting frame of the space net, so that the rotating arm and the connecting cable jointly limit the rotation of the space net relative to the main body of the spacecraft, thereby ensuring that the orientation of the space net remains stable and improving the capture effect of the space net. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present application and, together with the description, serve to explain the principles of the present application.

[0037] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, for ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0038] Figure 1 This is an exploded view of the space net system described in an embodiment of the present application;

[0039] Figure 2 This is a schematic diagram of the structure of the space network in the locked position according to an embodiment of the present application;

[0040] Figure 3 This is an assembly diagram of the space net, rotating arm and locking mechanism described in an embodiment of the present application;

[0041] Figure 4 This is an exploded view of the locking mechanism and the space network described in an embodiment of the present application;

[0042] Figure 5 This is a schematic structural diagram of the rotating arm according to an embodiment of the present application;

[0043] Figure 6 This is a schematic structural diagram of the elastic arm described in an embodiment of the present application;

[0044] Figure 7 This is an enlarged view of the local structure of the elastic arm described in the embodiment of the present application;

[0045] Figure 8 This is a schematic structural diagram of the hinge member described in an embodiment of the present application;

[0046] Figure 9 This is a schematic structural diagram of the receiving device described in an embodiment of the present application;

[0047] Figure 10 This is a schematic diagram of the structure of the storage tube according to an embodiment of the present application;

[0048] Figure 11 Schematic diagram of the front and back of the top plate according to the embodiment of the present application;

[0049] Figure 12 This is a schematic diagram of the locking assembly described in an embodiment of the present application;

[0050] Figure 13 This is an assembly diagram of the damper, rotating shaft, and cable according to an embodiment of the present application;

[0051] Figure 14 This is a schematic diagram of the partial structure of the elastic arm described in an embodiment of the present application;

[0052] Figure 15 This is a schematic diagram of the structure of the elastic arm when coiled according to an embodiment of the present application;

[0053] Figure 16 This is one of the process state diagrams of the elastic arm unfolding according to the embodiment of the present application;

[0054] Figure 17 This is the second state diagram of the process of unfolding the elastic arm according to the embodiment of the present application;

[0055] Figure 18 This is the third state diagram of the process of unfolding the elastic arm according to the embodiment of the present application

[0056] Figure 19 This is a schematic structural diagram of the elastic arm when it is unfolded according to an embodiment of the present application;

[0057] Figure 20 This is a schematic diagram of the space net system described in an embodiment of the present application when performing camouflage and confusion applications.

[0058] Among them, 1. Spacecraft body; 2. Storage equipment; 21. Storage cylinder; 22. Bottom plate; 23. Locking assembly; 231. Locking link; 232. Base; 233. Pin puller; 241. Rotating shaft; 242. Damper; 243. Cable; 244. Detector; 3. Elastic arm; 30. Top plate; 301. Main body; 302. Rotating part; 31. Elastic longitudinal rod; 32. Elastic cross rod; 33. Shaping cable; 34. Hinge; 341. Longitudinal rod connector; 342. Cross rod connector; 343. Mounting hole; 344. Cross rod hole; 345. Cable hole; 4. Locking mechanism; 41. Lower fixed plate; 42. Upper movable plate; 43. Driving spring; 44. Limiting member; 441. Lower pull rod; 442. Upper pressure rod; 443. Limiting seat; 444. Central axis; 45. Locking member; 451. Upper connecting member; 452. Lower connecting member; 453. Driver; 5. Rotating arm; 51. Base; 52. Rotating rod; 53. Elastic member; 54. Positioning end; 55. Positioning platform; 56. Limiting protrusion; 57. Arc portion; 6. Space net; 61. Support frame; 7. Connecting rope; 8. Target spacecraft; 9. Surveillance spacecraft. DETAILED DESCRIPTION

[0059] In order to more clearly understand the above-mentioned objectives, features and advantages of the present application, the scheme of the present application will be further described below. It should be noted that, in the absence of conflict, the embodiments of the present application and the features therein can be combined with each other.

[0060] In the following description, many specific details are set forth to facilitate a full understanding of the present application, but the present application can also be implemented in other ways different from those described herein; it is obvious that the embodiments in the specification are only part of the embodiments of the present application, not all of the embodiments.

[0061] Reference Figures 1 to 19 As shown, an embodiment of the present application provides a space netting system, including a spacecraft body 1, an elastic arm 3, a net device and a connecting rope 7; the elastic arm 3 is installed on the spacecraft body 1, and the elastic arm 3 can be stretched into a straight line to extend to the outside of the spacecraft body 1, and can be elastically deformed into a spiral coil to be stored on the spacecraft body 1; the net device includes a locking mechanism 4 installed on the spacecraft body 1, a rotating arm 5 rotatably connected to the locking mechanism 4 and a space net 6 with a supporting frame 61, the supporting frame 61 is connected to the rotating arm 5, and the rotating arm 5 can drive the space net 6 from a locking position close to the spacecraft body 1 to a specified position away from the spacecraft body 1; the connecting rope 7 is connected between the supporting frame 61 and the elastic arm 3; when the space net 6 is in the specified position, the rotating arm 5 is restricted from rotating relative to the spacecraft body 1, and the elastic arm 3 is in an extended state to tension the connecting rope 7, so that the rotating arm 5 and the connecting rope 7 jointly define the orientation of the space net 6 relative to the spacecraft body 1.

[0062] Specifically, the spacecraft body 1 is an orbiting satellite, and the containment device 2 and locking mechanism 4 can be optionally mounted on the surface of the spacecraft body 1. When the elastic arm 3 is extended, the elastic arm 3 extends beyond the containment device to the outside of the spacecraft body 1, causing the linear elastic arm 3 to protrude from the outside of the spacecraft body 1. When the space net 6 is in a designated position, the space net 6 is spaced apart from the spacecraft body 1, enabling the space net 6 to capture objects in space.

[0063] A cylindrical structure can be optionally provided on the surface side of the above-mentioned spacecraft body 1 to accommodate the spirally coiled elastic arm 3, and a movable buckle or movable protrusion can be optionally provided in the cylinder, so that the spirally coiled elastic arm 3 is connected with the movable buckle in the cylinder, and the movable protrusion abuts against the side of the spirally coiled elastic arm 3 away from the bottom of the cylinder, so that the spirally coiled elastic arm 3 can be stably stored in the cylinder. When the elastic arm 3 needs to be extended, the movable buckle is disconnected from the elastic arm 3, or the movable protrusion is disengaged from the abutment against the elastic arm 3, so that the elastic arm 3 is extended under its own elastic force.

[0064] Of course, a buckle can also be provided on the surface of the spacecraft body 1, and the spirally coiled elastic arm 3 is connected to the buckle. When the elastic arm 3 needs to be extended, the buckle is disconnected from the elastic arm 3, allowing the elastic arm 3 to extend.

[0065] One end of the elastic arm 3 is connected to the spacecraft body 1, and when in an extended state, it can be supported on the spacecraft body 1, so that the elastic arm 3 extends to the outside of the spacecraft body 1. The elastic arm 3 can be made of elastic metal or other elastic materials. When in the extended state, the elastic arm 3 is in a straight line state without elastic deformation. The elastic arm 3 is coiled around the linear axis to form a spirally coiled cylindrical structure. The elastic arm 3 elastically deforms when it is spirally coiled, so that the elastic arm 3 can automatically return to the extended straight line state due to its own elasticity.

[0066] The above-mentioned locking mechanism 4 can be selected to include a panel and a buckle, and the space net 6 can be connected to the buckle when it is in the locked position, so that the buckle limits the movement of the space net 6 relative to the panel, thereby making the space net 6 stably in the locked position; of course, the locking mechanism 4 can also be selected to include a panel and a buckle, and when the space net 6 is in the locked position, the buckle is connected to the rotating arm 5 to limit the rotation of the rotating arm 5, so that the space net 6 can be stably in the locked position.

[0067] The aforementioned rotating arm 5 may optionally include a rod and a motor, wherein the motor has a rotating end, the motor is mounted on the locking mechanism 4, the rod is connected to the rotating end, the edge of the space net 6 is connected to the rod, and the motor drives the rotating end to rotate, causing the rod to rotate in a direction away from the locking mechanism 4, so that the rod drives the space net 6 to move to a designated position. Of course, the rotating arm 5 may also include a rod and a spring, wherein the rod is rotationally connected to the locking mechanism 4, the spring is connected between the rod and the locking mechanism 4, and the elastic force of the spring drives the rod to rotate in a direction away from the locking mechanism 4, and the rod is connected to the edge of the space net 6, so that the rod can drive the space net 6 to move to a designated position.

[0068] Alternatively, an abutment protrusion may be provided on the locking mechanism 4 so that when the rotating arm 5 drives the space net 6 to move to a specified position, the rotating arm 5 abuts against the abutment protrusion on one side in the rotational direction, thereby limiting the rotation of the rotating arm 5 relative to the locking mechanism 4, thereby maintaining a stable relative position between the rotating arm 5 and the spacecraft body 1. Alternatively, an abutment protrusion may be provided on the rod body of the rotating arm 5 so that when the rotating arm 5 drives the space net 6 to move to a specified position, the abutment protrusion on the rotating arm 5 abuts against the locking mechanism 4, thereby limiting the rotation of the rotating arm 5 relative to the locking mechanism 4.

[0069] The rotating arm 5 can drive the space net 6 to move, and when the space net 6 is at a specified position, the rotating arm 5 is in a state of being restricted from rotating relative to the spacecraft body 1, so that the rotating arm 5 and the spacecraft body 1 are relatively stationary, so that the rotating arm 5 can support the supporting frame 61 on the spacecraft body 1, and then cooperate with the connecting rope 7 to limit the supporting frame 61, so as to control the orientation of the space net 6 relative to the spacecraft body 1.

[0070] The connecting rope 7 can be selected as a steel rope or a rope body of other materials. One end of the connecting rope 7 is connected to the edge of the space net 6, and the other end is connected to the elastic arm 3. The length of the connecting rope 7 is determined according to the actual situation. As long as the space net 6 is in the specified position, the elastic arm 3 stretches and can tension the connecting rope 7, so that the connecting rope 7 and the connection between the rotating arm 5 and the space net 6 can exert force on the space net 6. At this time, the rotating arm 5 is in a limited state, and the connection between the space net 6 and the rotating arm 5 is fixed relative to the spacecraft body 1. At this time, the connecting rope 7 is in a tensioned state, which can limit the direction of the space net 6 after it is unfolded.

[0071] The above-mentioned space net 6 has a supporting frame 61. When the space net 6 is unfolded into a planar state, the supporting frame 61 is in a planar state, which can keep the shape of the space net 6 stable. The orientation of the space net 6 is the relative angle between the normal of the plane where the supporting frame 61 is located and the spacecraft body 1 after the space net 6 is unfolded into a planar state.

[0072] The support frame 61 can be a fixed structure, and the rotating arm 5 drives the support frame 61 to rotate in space to move the space net 6 to a specified position. Of course, in order to save space, the support frame 61 can also be a foldable structure. For example, the support frame 61 can be elastic, and the support frame 61 of the space net 6 elastically deforms and folds to facilitate transportation of the support frame 61. The space net 6 can be unfolded at the specified position by the elastic force of the support frame 61 itself. Of course, the support frame 61 can also be selected to include multiple sub-frames, the multiple sub-frames are arranged in a ring, and two adjacent sub-frames are rotatably connected, and a limited position structure is formed between the two adjacent sub-frames, such as abutment protrusions are provided on the two adjacent sub-frames, or abutment surfaces are formed between the two adjacent sub-frames; the two adjacent sub-frames are rotated closer to each other to fold the space net 6. When the two adjacent sub-frames rotate to be in the same plane, the abutment surfaces or abutment protrusions of the two adjacent sub-frames abut each other and cannot continue to rotate, thereby keeping the multiple sub-frames in the same plane, so that the space net 6 can remain in a flat state.

[0073] The connection point between the above-mentioned rotating arm 5 and the supporting frame 61 is the first point, and the connection point between the connecting rope 7 and the supporting edge is the second point. The first point and the second point are spaced from each other, so that when the space net 6 is at a specified position, the first point and the second point both limit the relative position of the supporting frame 61 and the spacecraft body 1 to control the orientation of the space net 6 when it moves to the specified position.

[0074] When the space net system provided by the present application is used, the space net 6 is mounted on the rotating arm 5, the locking mechanism 4 limits the space net 6 to the locked position, and the elastic arm 3 is coiled to be stored in the storage device 2. When the spacecraft body 1 is launched into space and the space net 6 needs to be deployed, the locking mechanism 4 releases the lock on the space net 6, the rotating arm 5 drives the space net 6 to move to the designated position, the elastic arm 3 stretches to extend out of the storage device 2, and the elastic arm 3 extends in a straight line to the outside of the spacecraft body 1. When the space net 6 is in the designated position, the rotating arm 5 supports the space net 6, and the connecting cable 7 tightens the connecting cable, so that the space net 6 is limited by the rotating arm 5 and the connecting cable 7 and the direction of the space net 6 is indicated.

[0075] The space net system provided in the present application cooperates with the elastic arm 3, the net device and the connecting rope 7 so that when the space net 6 is in a specified position, the elastic arm 3 can apply a force to the supporting frame of the space net 6 through the connecting rope 7, and the rotating arm 5 can support the supporting frame 61 of the space net 6, so that the rotating arm 5 and the connecting rope 7 jointly limit the rotation of the space net 6 relative to the spacecraft body 1, thereby ensuring that the orientation of the space net 6 remains stable and improving the capture effect of the space net 6.

[0076] Reference Figure 1As shown, in some embodiments, there are multiple elastic arms 3, a portion of the multiple elastic arms 3 is arranged on the first side of the spacecraft body 1, and another portion is arranged on the second side of the spacecraft body 1, the first side and the second side are arranged opposite to each other, and the mesh device is arranged between the first side and the second side, each elastic arm 3 is connected to the support frame 61 through a connecting cable 7, and the connection points of the multiple connecting cables 7 and the support frame 61 are spaced apart from each other;

[0077] When the space net 6 is deployed at a designated position, the plurality of connecting cables 7 are all in a tensioned state. In this way, the plurality of connecting cables and the rotating arm 5 can together limit the space net 6 at a designated position, thereby improving the stability of the space net 6 at the designated position.

[0078] Specifically, the spacecraft body 1 is a rectangular parallelepiped structure, having at least two opposing sides, the two opposing sides of the spacecraft body 1 being a first side and a second side. Of course, the spacecraft body 1 may also be of other shapes, with the two sides of the spacecraft body 1 being the first side and the second side along a straight line.

[0079] The number of elastic arms 3 can be two, and the two elastic arms 3 are respectively provided on the first side and the second side. The two elastic arms 3 are correspondingly connected to the two connecting cables 7, so that the two elastic arms 3 are correspondingly connected to the support frame 61 through the two connecting cables 7. Of course, the number of elastic arms 3 can also be four, with two elastic arms 3 on the first side and the remaining two elastic arms 3 on the second side, and the four elastic arms 3 are connected to the four connecting cables 7 in a one-to-one correspondence.

[0080] The above-mentioned net device is between the first side and the second side, so that the connection point of the rotating arm 5 and the support frame 61 of the space net 6 is between the first side and the second side, and the multiple elastic arms 3 are spaced apart on the support frame 61 through the connection points of the connecting rope 7 and the support frame 61 and the connection points of the rotating arm 5 and the support frame 61, so as to enhance the limiting effect on the direction of the support frame 61.

[0081] When the support frame 61 is circular and two elastic arms 3 are provided on the spacecraft body 1, the connection points of the two elastic arms 3 and the support frame 61 can be selected as the first limit point and the second limit point respectively, and the connection point of the rotating arm 5 and the support frame 61 is the third limit point; the central angle corresponding to the arc between the first limit point and the third limit point is 90°, the central angle corresponding to the arc between the second limit point and the third limit point is 90°, and the central angle corresponding to the arc between the first limit point and the second limit point is 180°.

[0082] Reference Figures 9 to 13As shown, in some embodiments, a storage device 2 is provided on the spacecraft body 1, and the storage device 2 includes a storage tube 21 and a locking assembly 23; one end of the elastic arm 3 is connected to the bottom wall of the storage tube 21, and the other end is connected to the top plate 30; the elastic arm 3 is stored in the storage tube 21 when it is spirally coiled; when the elastic arm 3 is extended, the elastic arm 3 extends out of the storage tube 21 and drives the top plate 30 to move in a direction away from the storage tube 21; the locking assembly 23 is installed on the storage tube 21, and when the locking assembly 23 is locked, it is connected to the top plate 30 to limit the extension of the elastic arm 3, and when the locking assembly 23 is unlocked, it is separated from the top plate 30, so that the elastic arm 3 can extend and extend out of the storage tube 21; the connecting rope 7 is rotatably connected to the top plate 30.

[0083] With such a configuration, the storage tube 21 can store and protect the elastic arm 3 when the elastic arm 3 is spirally coiled, preventing external objects from colliding with the elastic arm 3; the locking component 23 conveniently controls the extension operation of the elastic arm 3 by unlocking and locking, and the locking component 23 can enable the spacecraft body 1 to extend the elastic arm 3 at the position where the object needs to be captured.

[0084] Specifically, the storage tube 21 is a hollow cylinder, and one end of the storage tube 21 is closed as the bottom of the tube, and the other end has an opening as the tube mouth. One end of the elastic arm 3 extends into the storage tube 21 and is connected to the bottom of the tube, and the other end is connected to the top plate 30. After the elastic arm 3 is spirally coiled, the top plate 30 can be selected to cover the tube mouth of the storage tube 21 to protect the elastic arm 3.

[0085] When the elastic arm 3 is extended, it drives the top plate 30 to rotate relative to the storage tube 21 and move away from the storage tube 21. After the elastic arm 3 is extended, the top plate 30 is located away from the spacecraft body 1 and spaced apart from the spacecraft body 1. The elastic arm 3 rotates when it is spirally coiled and extended. The connecting cable 7 is rotationally connected to the elastic arm 3, so that the rotation of the elastic arm 3 does not drive the connecting cable 7 to rotate, thereby preventing the connecting cable 7 from winding or being entangled with the elastic arm 3 when the elastic arm 3 is extended.

[0086] like Figure 11 and Figure 14 The top plate 30 can be selected as a circular plate body, and the top plate 30 can be selected to include a main plate body 301 and a rotating part 302. The main plate body 301 is connected to the elastic arm 3, and the rotating part 302 is rotatably connected to the side of the main plate body 301 facing away from the main plate body. The connecting rope 7 is connected to the rotating part 302.

[0087] The rotating part 302 can be selected as a plate structure, and the rotating part 302 is rotatably connected to the main body 301 by bolts or a rotating shaft. A through hole can be optionally set on the rotating part 302, and the connecting rope 7 is tied to the through hole. The main body 301 rotates with the extension of the elastic arm 3, and the rotating part 302 can rotate relative to the main body 301 with the extension of the elastic arm 3, so as to avoid the connecting rope 7 from being wound or wrapped around the elastic arm 3 when the elastic arm 3 is extended.

[0088] The locking assembly 23 can be a snap-fit ​​structure disposed on the outside or at the opening of the storage tube 21. When the elastic arm 3 is spirally coiled and stored in the storage tube 21, the top plate connects with the snap-fit ​​structure, locking the locking assembly 23. This prevents the top plate 30 from moving away from the storage tube 21, keeping the elastic arm 3 in the spirally coiled state. When the snap-fit ​​structure is opened and disconnected from the top plate 30, the elastic arm 3 can extend under its own elastic force.

[0089] Reference Figures 9 to 13 As shown, in some embodiments, the locking assembly 23 includes a locking link 231, a base 232 and a pin puller 233; the locking link 231 is connected to the top plate 30, the base 232 is installed on the storage tube 21, and the pin puller 233 is installed on the locking link 231, and a positioning hole is provided on the locking link 231; the pin puller 233 is provided with a retractable pin shaft end, and when the locking assembly 23 is locked, the pin shaft end is plugged into the positioning hole to limit the movement of the locking link 231 relative to the base 232; when the locking assembly 23 is unlocked, the pin shaft end is out of the positioning hole, so that the locking link 231 can move in a direction away from the base 232.

[0090] With this arrangement, the extension operation of the elastic arm 3 can be controlled by controlling the pin shaft end of the pin puller 233. The structure of the pin puller 233 and the positioning hole of the locking link 231 that cooperate with each other is simple and has low manufacturing cost, and the limiting state formed by the plug-in connection between the pin shaft end and the positioning hole has high stability.

[0091] Specifically, the locking link 231 can be selected as a rod body, and a positioning hole is provided at the end of the locking link 231 away from the top plate 30. The base 232 can be optionally set on the outside of the storage tube 21. The locking link 231 is set near the edge of the top plate 30. When the locking assembly 23 is locked, the locking link 231 has one end with a positioning hole at the base 232, so that the pin shaft end of the pin puller 233 can be extended to be inserted into the positioning hole.

[0092] The above-mentioned locking link 231 can also be optionally set in the center of the top plate 30, so that when the elastic arm 3 is spirally coiled to form a cylindrical structure, the locking link 231 is inside the cylindrical structure, and the base 232 and the pin puller 233 can be optionally set on the bottom wall of the storage tube 21, so that when the elastic arm 3 is spirally coiled, the positioning hole of the locking link 231 can be at the bottom wall of the storage tube 21, so that the pin shaft end of the pin puller 233 can be plugged into the positioning hole.

[0093] Of course, you can also choose to have a through hole in the bottom of the storage tube 21, and the base 232 and the pin puller 233 are on the outside of the storage tube 21 and at the bottom of the tube, so that when the elastic arm 3 is spirally coiled to form a cylindrical structure, the end of the locking link 231 with the positioning hole can pass through the through hole on the storage tube 21 and be located at the base 232, so that the pin shaft end of the pin puller 233 can be plugged into the positioning hole.

[0094] The above-mentioned pin puller 233 can be selected to include a telescopic motor, and the shaft body is connected to the telescopic end of the telescopic motor as the pin shaft end. Of course, the pin puller 233 can also be selected to include a main body and a pin shaft, and the pin shaft is movably arranged on the main body. Gunpowder is provided between the main body and the pin shaft. The driving force generated after the gunpowder is ignited can drive the pin shaft to move in the direction away from the positioning hole, so that the pin shaft end is out of the positioning hole.

[0095] Reference Figure 9 and Figure 13 As shown, in some embodiments, the storage device 2 also includes a rotating shaft 241, a damper 242 and a cable 243. The rotating shaft 241 is rotatably set on the storage tube 21, and the damper 242 is connected to the rotating shaft 241 so that the damper 242 provides resistance to the rotation of the rotating shaft 241. One end of the cable 243 is connected to the rotating shaft 241, and the other end is connected to the top plate 30; when the elastic arm 3 is spirally coiled, the cable 243 is wound on the rotating shaft 241, and the elastic arm 3 stretches to enable the top plate 30 to move in a direction away from the storage tube 21, so that the cable 243 drives the rotating shaft 241 to rotate.

[0096] With such a configuration, when the elastic arm 3 is extended, the rotating shaft 241 is driven to rotate by the cable 243, and the damper 242 slows down the rotation speed of the rotating shaft 241, thereby slowing down the extension of the elastic arm 3, so as to reduce the shaking of the elastic arm 3 when extended and improve the stability of the movement trajectory of the elastic arm 3 when extended.

[0097] Specifically, the rotating shaft 241 may include a rotating shaft and a base, the base being mounted on the storage tube 21, the rotating shaft being rotatably connected to the base, one end of the cable 243 being connected to the rotating shaft and the other end being connected to the locking link 231, and the rotating shaft rotating in one direction, causing the cable 243 to be wound around the rotating shaft. The damper 242 may be a friction plate disposed between the rotating shaft and the base, so that friction between the rotating shaft, the base, and the friction plate provides resistance when the rotating shaft 241 rotates. Alternatively, the damper 242 may include a stator and a rotor, the stator being connected to the base, and the rotor being connected to the rotating shaft so as to rotate therewith, with magnetic force between the stator and the rotor providing resistance when the rotor rotates relative to the stator.

[0098] The rotating shaft 241 can be optionally arranged at the bottom of the storage tube 21 , or can be optionally arranged at the side or the tube opening of the storage tube 21 .

[0099] The cable 243 can be connected to the top plate 30, or a locking link 231 can be provided on the top plate 30, and the cable 243 is connected to the locking link 231. As long as the elastic arm 3 is extended, the top plate 30 moves with the extension of the elastic arm 3, which can drive the cable 243 to move, thereby causing the cable 243 to drive the rotating shaft 241 to rotate.

[0100] When a through hole is provided at the bottom of the storage tube 21, and the locking link 231 can be passed through the through hole to connect with the pin puller 233, the rotating shaft 241 can be optionally provided on the outside of the storage tube 21 and at the bottom of the storage tube 21. In some embodiments, a bottom plate 22 is provided on the side of the storage tube 21 facing away from the top plate 30. The bottom plate 22 is spaced apart from the storage tube 21, and the bottom plate 22 and the storage tube 21 are connected by a bracket. The rotating shaft 241 is provided on the bottom plate 22, and the cable 243 is connected to the locking link 231. When the locking link 231 moves with the top plate 30, the cable 243 can pass through the through hole on the storage tube 21 along with the locking link 231, so that the cable 243 drives the rotating shaft 241 to rotate.

[0101] Reference Figure 13 As shown, in some embodiments, the storage device 2 further includes a detector, which is mounted on the storage tube 21 and electrically connected to the rotating shaft 241 so as to detect the rotation speed of the rotating shaft 241. In this configuration, the detector detects the speed of the rotating shaft 241 and can analyze and calculate the speed of the elastic arm 3 when it is extended, thereby conveniently monitoring the deployment of the elastic arm 3.

[0102] Specifically, the detector can be selected as an encoder, which is connected to the rotating shaft 241 and can detect the rotation speed of the rotating shaft 241, or the rotation weight of the rotating shaft 241 within a set time. Alternatively, the detector can be selected as a laser speed meter, or other speed measuring devices, so that the detector can detect the rotation speed of the rotating shaft 241.

[0103] When the elastic arm 3 is extended, the cable 243 moves along with the top plate 30 and drives the rotating shaft 241 to rotate. By detecting the rotation speed of the rotating shaft 241, the speed of the elastic arm 3 when extended can be obtained through analysis and calculation.

[0104] Reference Figure 6 、 Figure 8 、 Figures 14 to 19As shown, in some embodiments, the elastic arm 3 includes at least three elastic longitudinal rods 31, each elastic longitudinal rod 31 is connected between the bottom of the storage tube 21 and the top plate 30, and multiple elastic longitudinal rods 31 are arranged at intervals around the axis of the storage tube 21; when the elastic arm 3 is extended, the elastic longitudinal rod 31 extends along the direction of the axis of the storage tube 21; each elastic longitudinal rod 31 is elastically deformed around the axis of the storage tube 21, and multiple elastic longitudinal rods 31 are bent in the same direction, so that each elastic longitudinal rod 31 is spirally coiled after bending, and multiple elastic longitudinal rods 31 are stacked in sequence in the axial direction of the storage tube 21.

[0105] With such arrangement, the top plate 30 allows the plurality of elastic longitudinal rods 31 to bend and stretch synchronously. The plurality of elastic longitudinal rods 31 are coiled and stacked in sequence, so that the plurality of elastic longitudinal rods 31 do not interfere with each other when stretching.

[0106] Specifically, the elastic longitudinal rod 31 is a rod body made of elastic material. The number of elastic longitudinal rods 31 can be selected to be three. The three elastic longitudinal rods 31 are arranged at equal intervals around the axis of the storage tube 21. The three elastic longitudinal rods 31 are all connected to the top plate 30, so that when one elastic longitudinal rod 31 drives the top plate 30 to move, the movement of the top plate 30 causes the remaining two elastic longitudinal rods 31 to move, that is, the top plate 30 enables the three elastic longitudinal rods 31 to bend and stretch synchronously.

[0107] Of course, the number of the elastic longitudinal rods 31 may be greater than three, and the plurality of elastic longitudinal rods 31 may be arranged at equal intervals around the storage tube 21 , and the top plate 30 may enable the plurality of elastic longitudinal rods 31 to bend and stretch synchronously.

[0108] After the multiple elastic longitudinal rods 31 are spirally wound, they are always arranged in the same order in the axial direction of the storage tube 21, so that the three elastic longitudinal rods 31 will not cross each other and will not interfere with each other when the multiple elastic longitudinal rods 31 are stretched.

[0109] Reference Figure 6 、 Figure 8 、 Figures 14 to 19 As shown, in some embodiments, an elastic cross bar 32 is connected between each two adjacent elastic longitudinal bars 31 in the direction around the axis of the storage tube 21. The elastic cross bar 32 can elastically deform when the elastic arm 3 is coiled. This arrangement can improve the shape stability of the elastic arm 3 when the elastic arm 3 is extended; during the extension process of the elastic arm 3, the elastic force of the elastic cross bar 32 can help the elastic longitudinal bars 31 to extend to a straight state.

[0110] Specifically, the ends of the elastic crossbar 32 are connected to two adjacent elastic longitudinal bars 31. When the elastic arm 3 is extended, the elastic crossbar 32 is in a straight, undeformed state. This allows the multiple elastic crossbars 32 to support the multiple elastic longitudinal bars 31 in a direction around the axis of the storage tube 21, thereby improving the shape stability of the elastic arm 3 when extended. When the two adjacent elastic longitudinal bars 31 are spirally coiled, the bending of the elastic longitudinal bars 31 causes the elastic crossbar 32 to elastically deform. As the elastic longitudinal bars 31 extend, the elastic deformation of the elastic crossbar 32 is restored, allowing the elastic crossbar 32 to assist the elastic longitudinal bars 31 in extending to a straight state.

[0111] In some embodiments, when the elastic arm 3 is extended, in the axial direction of the storage tube 21, multiple elastic cross bars 32 are on a plane perpendicular to the axial direction of the storage tube 21 to form a cross bar group, and the number of cross bar groups is multiple, and multiple cross bar groups extend along the axial direction of the storage tube 21.

[0112] Specifically, when the elastic arm 3 is extended, the axial direction of the storage tube 21 is the height direction, and multiple elastic cross bars 32 at the same height form a cross bar group. The multiple cross bar groups can support multiple elastic longitudinal bars 31 at each position of the extended elastic arm 3, and the multiple elastic cross bars 32 in the cross bar group are in the same plane, which has a better supporting effect on the multiple elastic longitudinal bars 31 when the elastic arm 3 is extended; when the elastic longitudinal bar 31 is coiled, the deformation of the two adjacent elastic longitudinal bars 31 at the same height is consistent, so the distance between the two adjacent elastic longitudinal bars 31 at the same height is equal, and when the elastic arm 3 is coiled, the deformation of the multiple elastic cross bars 32 in the cross bar group can also be equal.

[0113] In some embodiments, a shaping cable 33 is connected between each two adjacent crossbar groups in the axial direction of the storage tube 21. When the elastic arm 3 is coiled, the shaping cable 33 is bent, and when the elastic arm 3 is stretched, the shaping cable is tightened.

[0114] Specifically, during the extension of the elastic arm 3, the extended elastic arm 3 can drive the shaping cable 33 to pull the unextended portion of the elastic arm 3, so that the shaping cable 33 assists the extension of the elastic arm 3. Furthermore, after the elastic arm 3 is extended, the shaping cable 33 can improve the relative stability between the two adjacent elastic longitudinal rods 31 and the relative stability between the two adjacent elastic transverse rods 32.

[0115] Reference Figure 8As shown, each elastic longitudinal rod 31 is provided with a plurality of hinges 34, and the plurality of hinges 34 correspond to the plurality of cross bar groups one by one; the hinges 34 include a cross bar connector 342 and a longitudinal rod connector 341, and the longitudinal rod connector 341 is provided with a mounting hole, and the elastic longitudinal rod 31 is passed through the mounting hole 343, and the two elastic cross bars 32 adjacent to the elastic longitudinal rod 31 in the mounting hole 343 are respectively connected to the cross bar connector 342; the cross bar connector 342 is rotatably connected to the longitudinal rod connector 341, and the rotation axis of the cross bar connector 342 and the longitudinal rod connector 341 is in the middle of the cross bar connector 342 and is perpendicular to the axis of the mounting hole 343. With such arrangement, the hinge 34 facilitates the mutual connection of multiple elastic longitudinal rods 31 and multiple elastic cross rods 32; when the elastic arm 3 is coiled, the elastic cross rod 32 will bend, and at this time the cross rod connector 342 can rotate relative to the longitudinal rod connector 341 when the elastic longitudinal rod 31 is coiled, so as to reduce the axial deformation of the elastic cross rod 32 in the storage tube 21, and avoid excessive bending of the elastic cross rod 32 when the elastic longitudinal rod 31 is coiled.

[0116] Specifically, two cross bar holes 344 can be optionally set at both ends of the cross bar connector 342, so that the two elastic cross bars 32 can be respectively plugged and connected in the two cross bar holes 344; when a shaping rope 33 is connected between each two adjacent elastic cross bars 32, there will be two shaping ropes 33 on both sides of a longitudinal rod connector 341, and two rope holes 345 can be optionally set at both ends of the cross bar connector 342, so that the two shaping ropes 33 can be respectively plugged and connected with the two rope holes 345.

[0117] The two ends of an elastic cross bar 32 are respectively plugged into the cross bar holes 344 of two hinged parts 34 adjacent to each other in the axial direction of the storage tube 21, and the two ends of a shaping rope 33 can be respectively plugged into the rope holes 345 of two hinged parts 34 adjacent to each other along the axial direction of the storage tube 21.

[0118] The cross bar connector 342 can be selectively connected to the longitudinal bar connector 341 by bolts or rotation. Since the elastic longitudinal bar 31 will drive the elastic cross bar 32 to bend axially in the storage tube 21 and elastically deform when it is coiled, the cross bar connector 342 can rotate relative to the longitudinal bar connector 341 when the elastic longitudinal bar 31 is coiled, so as to reduce the axial deformation of the elastic cross bar 32 in the storage tube 21 and avoid excessive bending of the elastic cross bar 32 when the elastic longitudinal bar 31 is coiled.

[0119] like Figures 15 to 19 FIG. 1 is a schematic diagram showing the process of the elastic arm 3 extending from a spirally coiled state to a straight extended state. Figure 15 The elastic arm 3 is in a spirally coiled state. Figure 19 The elastic arm 3 is in a straight line stretched state. Figure 15 、 Figure 16 、 Figure 17 、 Figure 18 and Figure 19 Arranged in the order of time when the elastic arm 3 is extended.

[0120] Figure 15 is a schematic diagram of the elastic arm 3 in a spirally coiled state, Figure 16 The middle elastic arm 3 begins to stretch, and the part of the elastic arm 3 close to the bottom wall of the storage tube 21 stretches. The elastic deformation of the elastic longitudinal rod 31 recovers and gradually stretches toward a straight line. The deformation of the elastic cross bar 32 in the bottom cross bar group gradually recovers to assist the elastic longitudinal rod 31 to gradually straighten.

[0121] Figure 17 In the schematic diagram of the further extension of the elastic longitudinal rod 31, the bottom portion of the elastic longitudinal rod 31 is basically in a straight line state, and the multiple elastic cross bars 32 of the cross bar group at the bottom are basically in an extended straight line state.

[0122] Figure 18 The elastic longitudinal rod 31 of the middle elastic arm 3 continues to stretch, most of the elastic longitudinal rod 31 is stretched, the portion of the elastic longitudinal rod 31 near the top is in a bent state, and the multiple elastic cross bars 32 in most cross bar groups are in a stretched straight state.

[0123] Figure 19 3 is a schematic structural diagram of the elastic arm 3 when it is extended. Each elastic longitudinal rod 31 is extended to a straight state, and each elastic transverse rod 32 is extended to a straight state.

[0124] Reference Figures 2 to 5 As shown, in some embodiments, the rotating arm 5 includes a base 51, a rotating rod 52 and an elastic member 53; the base 51 is installed on the locking mechanism 4, the rotating rod 52 is rotatably connected to the base 51, the edge of the space net 6 is connected to the rotating rod 52, and the elastic member 53 is connected between the base 51 and the rotating rod 52. The elastic force of the elastic member 53 drives the rotating rod 52 to rotate in a direction away from the locking mechanism 4; a positioning platform 55 is formed on the top side of the base 51, and a positioning end 54 is formed at one end of the rotating rod close to the base. When the space net 6 is at a specified position, the positioning end 54 abuts against the positioning platform 55 to limit the rotation of the rotating rod 52 relative to the base 51.

[0125] With this arrangement, the rotating rod 52 can drive the space net 6 to move to the specified position through the elastic force of the elastic member 53, and when the space net 6 is at the specified position, the positioning end 54 abuts against the positioning platform 55 to limit the rotating rod 52 from continuing to rotate relative to the base 51, so that the rotating rod 52 maintains a stable position.

[0126] Specifically, the base 51 can be installed on the locking mechanism 4, and the elastic member 53 can be a spring or an elastic metal sheet. The elastic member 53 is connected between the base 51 and the rotating rod 52. When the space net 6 is in the locked position, the rotating rod 52 is close to the locking mechanism 4, and the elastic force of the elastic member 53 can drive the rotating rod 52 to move away from the locking mechanism 4. In this way, the rotating rod 52 can drive the space net 6 to move to a specified position.

[0127] The end of the base 51 away from the locking mechanism 4 is the top side of the base 51. A planar structure is formed on the top side of the base 51 to serve as a positioning platform 55. A positioning end 54 is provided at the end of the rotating rod 52 near the base 51. When the space net 6 is in the locked position, the rotating rod 52 is near the locking mechanism 4, and the positioning end 54 and the positioning platform 55 are spaced apart. When the space net 6 is moved toward the designated position, the rotating rod 52 rotates away from the locking mechanism 4, and the positioning end 54 moves with the rotating rod 52 toward the positioning platform 55. When the space net 6 moves to the designated position, the positioning end 54 abuts the positioning platform 55, thereby limiting the rotating rod 52 from further rotating relative to the base 51.

[0128] Reference Figures 2 to 5 As shown, in some embodiments, the rotating arm 5 includes a base 51, a rotating rod 52 and an elastic member 53; the base 51 is installed on the locking mechanism 4, the rotating rod 52 is rotatably connected to the base 51, the edge of the space net 6 is connected to the rotating rod 52, and the elastic member 53 is connected between the base 51 and the rotating rod 52, and the elastic force of the elastic member 53 drives the rotating rod 52 to rotate in the direction away from the locking mechanism 4; an arc surface 57 is provided on the base 51, and a positioning groove is formed on the arc surface 57. A limiting protrusion 56 that can rotate relative to the rotating rod 52 is provided on the rotating rod 52, and a spring is connected between the limiting protrusion 56 and the rotating rod 52, and the spring drives the limiting protrusion 56 to abut against the arc surface 57; when the space net 6 is in the locked position, the limiting protrusion 56 abuts against the arc surface 57 and is spaced from the positioning groove. When the space net 6 is in the specified position, the limiting protrusion 56 is inserted into the positioning groove to limit the rotation of the rotating rod 52 relative to the base 51. With this arrangement, the limiting protrusion 56 and the positioning groove cooperate with each other, so that the rotating rod 52 can stop rotating after rotating to a certain angle, so that the position of the rotating rod 52 remains stable to form a limit for the space net 6.

[0129] Specifically, the arc surface portion 57 can be selected as a cylindrical block, the axial direction of the cylindrical block is in the same direction as the rotation axis of the rotating rod 52 and the base 51, the end of the limiting protrusion 56 abuts against the arc surface portion 57, and the positioning groove is formed in a recessed position at one end of the arc surface portion 57 away from the lower locking mechanism 4. The limiting protrusion 56 can be movably connected to the rotating rod 52 through a slide rail, or the limiting protrusion 56 can be movably connected to the rotating rod 52 through an elastic rod.

[0130] When the space net 6 is in the locked position, the rotating rod 52 is located near the locking mechanism 4, and the limiting protrusion 56 is located on the side of the positioning slot near the locking mechanism 4. When the space net 6 moves toward the designated position, the rotating rod 52 rotates away from the locking mechanism 4. The limiting protrusion 56, under the action of the abutment spring, maintains contact with the arcuate surface 57, thereby moving the limiting protrusion 56 along the arcuate surface 57 toward the positioning slot. When the space net 6 moves to the designated position, the limiting protrusion 56 engages with the positioning slot, and the rotation of the rotating rod 52 relative to the locking mechanism 4 is restricted.

[0131] As the aforementioned rotating rod 52 rotates in a direction away from the locking mechanism 4, the distance between the end of the rotating rod 52 away from the base 51 and the locking mechanism 4 gradually increases until the rotating rod 52 is perpendicular to the plane of the base 51 on which the locking mechanism 4 is mounted, at which point the distance between the end of the rotating rod 52 away from the base 51 and the locking mechanism 4 reaches a maximum value. If the rotating rod 52 continues to rotate, the distance between the end of the rotating rod 52 away from the base 51 and the locking mechanism 4 begins to decrease. When the limiting protrusion 56 is engaged with the positioning groove, the rotating rod 52 can be positioned perpendicular to the plane of the base 51 on which the locking mechanism 4 is mounted, so that the spacing between the spatial net 6 and the locking mechanism 4 is maximized when the spatial net 6 is in a designated position.

[0132] The above-mentioned rotating rod 52 can be optionally provided with a limiting protrusion 56 and a positioning end 54, and the base 51 is provided with a positioning platform 55 and an arc surface portion 57. When the space net 6 is at the specified position, the limiting protrusion 56 is plugged into the positioning groove on the arc surface portion 57, and the positioning end 54 abuts against the positioning platform 55 to improve the position stability of the rotating rod 52.

[0133] Reference Figure 2 and Figure 3 As shown, in some embodiments, the locking mechanism 4 includes a plate assembly and a limiter 44, the plate assembly is installed on the surface side of the spacecraft body 1, the limiter 44 is installed on the side of the plate assembly away from the spacecraft body 1, and the rotating arm 5 is installed on the plate assembly; when the space net 6 is in the locked position, the space net 6 is attached to the side of the plate assembly away from the spacecraft body 1; the limiter 44 can switch between a limiting state and a disengaged state, when the limiter 44 is in the limiting state, the limiter 44 abuts against the side of the space net 6 in the locking position facing away from the plate assembly to limit the movement of the space net 6 in the direction away from the plate assembly; when the limiter 44 is in the disengaged state, the limiter 44 is out of contact with the space net 6, so that the space net 6 can move to the specified position.

[0134] With such arrangement, the limiter 44 can limit the space net 6 so that the space net 6 will not move to the specified position under the drive of the rotating arm 5, thereby realizing the operation of controlling whether the space net 6 moves to the specified position through the limiter 44.

[0135] Specifically, the plate assembly is mounted on the surface of the spacecraft body 1, and the rotating arm 5 can be rotated relative to the plate assembly to drive the space net 6 to move to a designated position away from the spacecraft body 1. The side of the space net 6 facing away from the plate assembly in the locked position is the top side.

[0136] The limiting member 44 may optionally include a rotatable abutment arm, which can rotate relative to the plate assembly. When the abutment arm is rotated toward the plate assembly, it can abut against the space net 6 on the plate assembly, so that the limiting member 44 limits the space net 6. When the abutment arm is rotated in a direction away from the plate assembly, it can disengage from the space net 6, allowing the space net 6 to move to a specified position. The abutment arm plate assembly is tilted so that when the abutment arm can abut the top side of the space net 6, the limiting member 44 is in a limited state. When the abutment arm is perpendicular to the plate assembly so that the abutment arm cannot abut the top side of the space net 6, the limiting member 44 is in a disengaged state.

[0137] Of course, the limiting member 44 can also be a snap-fit ​​structure, which is arranged on the top side of the plate assembly. When the snap-fit ​​structure is snap-fitted to the space net 6, it can limit the movement of the space net 6 in the direction away from the plate assembly. When the snap-fit ​​structure is opened to disengage the space net 6, the space net 6 can move to the designated position. When the snap-fit ​​structure is snap-fitted to the space net 6 in the locked position, the limiting member 44 is in the limited position; when the snap-fit ​​structure is disengaged from the space net 6 in the locked position, the limiting member 44 is in the disengaged position.

[0138] In some embodiments, the plate assembly includes an upper movable plate 42, a lower fixed plate 41 arranged on the bottom side of the upper movable plate 42, a driving spring 43 installed between the upper movable plate 42 and the lower fixed plate 41, and a locking member 45 installed between the upper movable plate 42 and the lower fixed plate 41; the space net 6 is attached to the top side of the upper movable plate 42 in the locked position, and is connected to the limit member 44 to limit the space net 6 from being out of contact with the upper movable plate 42; a through hole is provided on the upper movable plate 42, and the rotating member is installed on the lower fixed plate 41 and is connected to the space net 6 through the through hole, and the elastic force of the driving spring 43 drives the upper movable plate 42 and the lower fixed plate 41 away from each other, so that the upper movable plate 42 shown is used as a moving part; when the locking member 45 is locked, it limits the relative movement of the upper movable plate 42 and the lower fixed plate 41; when the locking member 45 is unlocked, the upper movable plate 42 and the lower fixed plate 41 can be driven by the driving spring 43 to move away from each other, and the limit member 44 can be synchronously disconnected from the space net 6.

[0139] Specifically, the upper movable plate 42 and the lower fixed plate 41 move away from each other to push the space net 6 in the locked position to move, thereby assisting the space net 6 to move toward the designated position.

[0140] The locking member 45 may optionally include two mounting members and a pin puller, one mounting member being connected to the upper movable plate 42, and the other being connected to the lower fixed plate 41, the two mounting members being connected to each other via a movably plugged pin, the pin being connected to the pin puller, the pin puller being able to drive the pin to move, causing the pin mounting member to be disconnected, and when the pin is disconnected from any mounting member, the two mounting members can be separated from each other, so that the elastic force of the drive spring 43 drives the upper movable plate 42 to move in a direction away from the lower fixed plate 41.

[0141] Of course, the two mounting members can also be connected to each other via a buckle. When the buckle is engaged, the two mounting members are connected to each other, so that the upper movable plate 42 and the lower fixed plate 41 remain connected to each other, preventing the upper movable plate 42 from moving away from the lower fixed plate 41. When the buckle is unlocked, the two mounting members can be separated from each other, allowing the elastic force of the drive spring 43 to drive the upper movable plate 42 to move away from the lower fixed plate 41. The buckle of the locking member 45 can optionally be provided with a control motor, which can control the opening and closing of the buckle, thereby controlling the locking and unlocking of the locking member 45.

[0142] The limit member 44 can optionally be provided with a motor to control the position of the abutment arm or the opening and closing of the buckle. The motor of the limit member 44 is electrically connected to the pin puller or control motor of the locking member 45, so that the motor of the limit member 44 and the pin puller or control motor of the locking member 45 are started synchronously, so that when the locking member 45 is unlocked, the limit member 44 can be disconnected from the space network 6.

[0143] In some embodiments, the locking member 45 includes an upper connecting member 451, a lower connecting member 452 and a driver 453; the upper connecting member 451 is connected to the upper movable plate 42, the lower connecting member 452 is connected to the lower fixed plate 41, and the driver 453 has a retractable limiting shaft; when the locking member 45 is locked, the limiting shaft extends to connect with the upper connecting member 451 and the lower connecting member 452, so that the limiting shaft limits the upper connecting member 451 and the lower connecting member 452 to move away from each other; when the locking member 45 is unlocked, the positioning shaft retracts to disconnect from at least one of the upper connecting member 451 and the lower connecting member 452, so that the upper connecting member 451 and the lower connecting member 452 can move away from each other.

[0144] Specifically, a first through hole is provided on the upper connecting member 451, and a second through hole is provided on the lower connecting member 452. The first through hole and the second through hole are coaxially arranged, and the limiting shaft is movably inserted in the first through hole and the second through hole to connect the upper connecting member 451 and the lower connecting member 452 to each other, thereby limiting the upper connecting member 451 and the lower connecting member 452 from moving away from each other. At this time, the locking member 45 is in a locked state, and the upper movable plate 42 and the lower fixed plate 41 cannot move in a direction away from each other.

[0145] The driver 453 drives the limiting shaft to retract, so that the limiting shaft is connected to the upper connecting member 451. When the limiting shaft is disconnected from the lower connecting member 452, the upper connecting member 451 and the lower connecting member 452 can be disconnected and move in a direction away from each other. Alternatively, the driver 453 drives the limiting shaft to retract, so that the limiting shaft is disconnected from the upper connecting member 451. When the limiting shaft is connected to the lower connecting member 452, the upper connecting member 451 and the lower connecting member 452 can be disconnected and move in a direction away from each other. Alternatively, and not limited to, the driver 453 drives the limiting shaft to retract, so that the limiting shaft is disconnected from the upper connecting member 451. When the limiting shaft is disconnected from the lower connecting member 452, the upper connecting member 451 and the lower connecting member 452 can be disconnected and move in a direction away from each other.

[0146] The driver 453 can be selected as a telescopic motor, and the limit shaft is set at the telescopic end of the telescopic motor. Of course, the driver 453 can be selected as a telescopic cylinder, and the limit shaft is set on the telescopic end of the telescopic cylinder.

[0147] In some embodiments, the limit member 44 includes an upper pressure rod 442 and a lower pull rod 441, at least a portion of the lower pull rod 441 is on the top side of the upper movable plate 42, the upper pressure rod 442 is on the top side of the upper movable plate 42 and is rotatably connected to the lower pull rod 441, and the upper pressure rod 442 can rotate relative to the lower pull rod 441 to switch between the abutment position and the avoidance position; when the upper pressure rod 442 is in the abutment position, it is tilted relative to the lower pull rod 441 toward the upper movable plate 42, and the avoidance position is back to the abutment position. One side of the upper movable plate 42; when the locking piece 45 is locked, the upper pressure rod 442 can abut against the top side of the space net 6 in the locking position at the abutting position to limit the space net 6 from disengaging from the locking position. When the upper pressure rod 442 is in the abutting position, the limiting piece 44 is in the limiting state; when the locking piece 45 is unlocked, the upper pressure rod 442 can switch to the avoidance position to disengage from the abutment with the space net 6, so that the space net 6 can move to the specified position. When the upper pressure rod 442 is in the avoidance position, the limiting piece 44 is in the disengaged state.

[0148] Specifically, the upper pressure rod 442 can be rotatably connected to the top end of the lower pull rod 441, and the lower pull rod 441 can be located at the outside or inside of the space net 6 in the locked position. The upper pressure rod 442 can be located perpendicular to the lower pull rod 441, and the upper pressure rod 442 is located at the contact position, so that a portion of the upper pressure rod 442 can contact the top side of the support frame 61 of the space net 6 in the locked position, so that the space net 6 in the locked position is clamped on the upper movable plate 42. The upper pressure rod 442 is rotated in a direction away from the upper movable plate 42, so that the upper pressure rod 442 moves toward the avoidance position. The upper pressure rod 442 can be located parallel to the lower pull rod 441, and the upper pressure rod 442 is located at the avoidance position, at which time the space net 6 can break away from the limit of the limit member 44 and move to the specified position.

[0149] A rotating motor can be optionally provided between the above-mentioned upper pressure rod 442 and the lower pull rod 441. The rotating motor drives the upper pressure rod 442 to rotate relative to the lower pull rod 441, so that the rotating motor can drive the upper pressure rod 442 to rotate between the abutment position and the avoidance position. The rotating motor can be electrically connected to the driver 453 of the locking member 45, so that the driver 453 and the rotating motor work synchronously, that is, when the driver 453 pulls out the limit shaft, the rotating motor rotates the upper pressure rod 442 to the avoidance position, and when the upper movable plate 42 moves toward and away from the lower fixed plate 41, the upper pressure rod 442 is disengaged from the support frame 61 of the space net 6, so that the space net 6 can subsequently move to the specified position.

[0150] In some embodiments, the limit member 44 also includes a limit seat 443, a baffle and a center axis 444. A connecting hole is provided on the upper movable plate 42. The lower pull rod 441 is connected to the lower fixed plate 41 through the connecting hole. The baffle is arranged between the lower pull rod 441 and the supporting frame 61 of the space net 6. A sliding groove and an abutment platform are provided on the lower pull rod 441. The sliding groove is located on the upper side of the abutment platform. The center axis 444 is passed through the sliding groove and is connected to the limit seat 443. The upper pressure rod 442 and the lower pull rod 441 are rotatably connected through the center axis 444.

[0151] When the locking piece 45 is locked, the upper pressure rod 442 is tilted or vertically arranged relative to the lower pull rod 441 toward the support frame 61 of the space net 6 to be in the abutting position, and the center axis 444 is spaced apart from the top of the sliding groove. At this time, the side surface of one end of the upper pressure rod 442 abuts the support frame 61 of the space net 6, and the side surface of the other end abuts the top side of the abutting platform, and the center axis 444 is between the end surfaces of the two ends of the upper pressure rod 442; the plane that the upper pressure rod 442 and the abutting platform abut each other has a certain area, so that at least a part of the abutting plane is on the side of the center axis 444 away from the space net 6, and the abutting platform can provide a supporting force for the upper pressure rod 442, so that the upper pressure rod 442 is parallel to the hands at both ends of the center axis 444, so that the upper pressure rod 442 will not rotate, and the upper pressure rod 442 is restricted from rotating relative to the lower pull rod 441 in the direction away from the upper movable plate 42, so that the upper pressure rod 442 can abut the support frame 61 of the space net 6 against the top side of the upper movable plate 42.

[0152] When the locking piece 45 is unlocked, the upper movable plate 42 moves upward relative to the lower pull rod 441, and the limit seat 443 moves together with the upper movable plate 42, so that the central axis 444 moves toward the top of the sliding groove, and the upper pressure rod 442 is spaced from the top side of the abutment platform, so that the upper pressure rod 442 can rotate relative to the lower pull rod 441, and the baffle follows the upper movable plate 42 to move upward, so that the baffle pushes the upper pressure rod 442 to move in the direction away from the upper movable plate 42, so that the upper pressure rod 442 moves to the avoidance position.

[0153] The lower pull rod 441 is connected to the lower fixed plate 41 through the connecting hole, so that the upper movable plate 42 moves away from the lower fixed plate 41 and pushes the upper pressing rod 442 to rotate. The linkage between the limit member 44 and the upper movable plate 42 is completed through a simple structure.

[0154] This application also provides an on-orbit scenario application of the space network system. The spacecraft in the space network system runs between the target spacecraft and the opponent's monitoring spacecraft. By opening the space network 6, it simulates its own large spacecraft, disguises and confuses the opponent's situational awareness system, and reduces the attention of the opponent's monitoring spacecraft to its target spacecraft.

[0155] For example Figure 20 As shown, when ground reconnaissance facilities or target spacecraft 8 detect that surveillance spacecraft 9 poses a reconnaissance threat to target spacecraft 8, target spacecraft 8 releases spacecraft body 1, which then maneuvers through orbit to a mid-position on the same orbit as surveillance spacecraft 9 and target spacecraft 8. Spacecraft body 1, through the interaction of elastic arms 3, the mesh assembly, and connecting cables 7, moves space net 6 to a designated position. Space net 6 is positioned toward surveillance spacecraft 9, with the plane of space net 6 perpendicular to the mesh plane of space net 6 in its deployed state and perpendicular to the field of view of the situational awareness system of surveillance spacecraft 9, achieving camouflage and deception in scenarios.

[0156] When the space net system provided herein is in use, the space net 6 is attached to the upper movable plate 42. The upper pressure rod 442 of the limiter 44 abuts the support frame 61 of the space net 6 at the abutment position, maintaining the space net 6 in the locked position and the locking member 45 in the locked state. The multiple elastic longitudinal rods 31 of the elastic arm 3 are spirally coiled, the locking link 231 is connected to the pin end of the pin puller 233 on the base 232, and the top plate 30 covers the tube opening of the storage tube 21.

[0157] After the spacecraft body 1 is launched into space and enters orbit, when the spacecraft body 1 needs to be captured, the pin puller 233 drives the pin shaft to disengage from the positioning hole of the locking link 231, and the driver 453 drives the limit shaft to disconnect from the upper connecting member 451 or the lower connecting member 452, so that the upper movable plate 42 moves in the direction away from the lower fixed plate 41. The movement of the upper movable plate 42 causes the baffle to push the upper pressure rod 442 to move to the avoidance position, so that the elastic member 53 drives the rotating rod 52 to rotate in the direction away from the upper movable plate 42, so that the rotating rod 52 drives the space net 6 to move to the specified position.

[0158] In the process of the space net 6 moving to the specified position, the elastic arm 3 is synchronously extended to a straight state. When the elastic arm 3 is extended, the top plate 30 moves in the direction away from the storage tube 21 as the elastic arm 3 extends, so that the top plate 30 drives the cable 243 to move, and the cable 243 drives the rotating shaft 241 to rotate, and the detector 244 detects the rotation speed of the rotating shaft 241.

[0159] When the space net 6 is in the designated position, the limiting protrusion 56 on the rotating rod 52 engages with the positioning groove on the curved surface 57, and the positioning end 54 abuts the positioning platform 55, allowing the rotating rod 52 to support the support frame 61 of the space net 6. When the space net 6 is deployed in the designated position, the elastic arms 3 simultaneously extend to a straight position. The connecting cables 7 on the two elastic arms 3 of the spacecraft body 1 are connected to the support frame 61 of the space net 6, and both connecting cables 7 are in a tensioned state. The two connecting cables 7 and the rotating rod 52 jointly define the position of the support frame 61 relative to the spacecraft body 1.

[0160] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "comprises," "comprising," or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, article, or device comprising a series of elements includes not only those elements, but also other elements not explicitly listed, or elements inherent to such process, method, article, or device. In the absence of further limitations, an element defined by the phrase "comprising a ..." does not exclude the presence of other identical elements in the process, method, article, or device comprising the element.

[0161] The foregoing description is intended only to provide specific embodiments of the present application, which will enable those skilled in the art to understand and implement the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application is not limited to the embodiments described herein, but is intended to be construed in the broadest manner consistent with the principles and novel features disclosed herein.

Claims

1. A space net system, characterized in that: include: Spacecraft body (1); An elastic arm (3) is mounted on the spacecraft body (1), wherein the elastic arm (3) can be stretched into a straight line to extend to the outside of the spacecraft body (1), and can be elastically deformed into a spiral coil to be accommodated on the spacecraft body (1); A net device comprises a locking mechanism (4) mounted on the spacecraft body (1), a rotating arm (5) rotatably connected to the locking mechanism (4), and a space net (6) having a supporting frame (61), wherein the supporting frame (61) is connected to the rotating arm (5), and the rotating arm (5) can drive the space net (6) to move from a locking position close to the spacecraft body (1) to a designated position away from the spacecraft body (1); A connecting rope (7) connected between the supporting frame (61) and the elastic arm (3); When the space net (6) is at the designated position, the rotating arm (5) is restricted from rotating relative to the spacecraft body (1), and the elastic arm (3) is in an extended state to tension the connecting cable (7), so that the rotating arm (5) and the connecting cable (7) jointly define the orientation of the space net (6) relative to the spacecraft body (1).

2. The space net system according to claim 1, characterized in that: There are a plurality of elastic arms (3), a portion of the plurality of elastic arms (3) is arranged on a first side of the spacecraft body (1), and another portion is arranged on a second side of the spacecraft body (1), the first side and the second side are arranged opposite to each other, the mesh device is arranged between the first side and the second side, each of the elastic arms (3) is connected to the support frame (61) via a connecting cable (7), and the connection points of the plurality of connecting cables (7) and the support frame (61) are spaced apart from each other; When the space net (6) is unfolded at the designated position, the plurality of connecting cables (7) are all in a tensioned state.

3. The space net system according to claim 1, characterized in that: The spacecraft body (1) is provided with a storage device (2), and the storage device (2) comprises a storage cylinder (21) and a locking assembly (23); One end of the elastic arm (3) is connected to the bottom wall of the storage tube (21), and the other end is connected to the top plate (30); when the elastic arm (3) is spirally wound, it is stored in the storage tube (21); when the elastic arm (3) is extended, the elastic arm (3) extends out of the storage tube (21) and drives the top plate (30) to move in a direction away from the storage tube (21); The locking assembly (23) is mounted on the storage tube (21). When the locking assembly (23) is locked, it is connected to the top plate (30) to limit the extension of the elastic arm (3). When the locking assembly (23) is unlocked, it is separated from the top plate (30) to allow the elastic arm (3) to extend and extend out of the storage tube (21). The connecting rope (7) is rotatably connected to the top plate (30).

4. The space net system according to claim 3, characterized in that: The locking assembly (23) includes a locking link (231), a base (232) and a pin puller (233); the locking link (231) is connected to the top plate (30), the base (232) is mounted on the storage tube (21), the pin puller (233) is mounted on the locking link (231), and a positioning hole is provided on the locking link (231); The pin puller (233) is provided with a retractable pin shaft end. When the locking assembly (23) is locked, the pin shaft end is plug-connected with the positioning hole to limit the movement of the locking link (231) relative to the base (232); when the locking assembly (23) is unlocked, the pin shaft end is released from the positioning hole to enable the locking link (231) to move in a direction away from the base (232).

5. The space net system according to claim 3, characterized in that: The storage device (2) further includes a rotating shaft (241), a damper (242) and a cable (243), wherein the rotating shaft (241) is rotatably disposed on the storage cylinder (21), the damper (242) is connected to the rotating shaft (241) so that the damper (242) provides resistance to the rotation of the rotating shaft (241), and one end of the cable (243) is connected to the rotating shaft (241), and the other end is connected to the top plate (30); When the elastic arm (3) is spirally wound, the cable (243) is wound around the rotating shaft (241), and the elastic arm (3) stretches to move the top plate (30) in a direction away from the storage tube (21), so that the cable (243) drives the rotating shaft (241) to rotate.

6. The space net system according to claim 5, characterized in that: The storage device (2) further comprises a detector, which is mounted on the storage cylinder (21) and is electrically connected to the rotating shaft (241) so that the detector can detect the rotation speed of the rotating shaft (241).

7. The space net system according to claim 3, characterized in that: The elastic arm (3) includes at least three elastic longitudinal rods (31), each of the elastic longitudinal rods (31) is connected between the bottom of the storage tube (21) and the top plate (30), and the plurality of elastic longitudinal rods (31) are spaced apart around the axis of the storage tube (21); When the elastic arm (3) is extended, the elastic longitudinal rod (31) extends in the direction of the axis of the storage tube (21); each elastic longitudinal rod (31) is elastically deformed around the axis of the storage tube (21), and the plurality of elastic longitudinal rods (31) are bent in the same direction so that each elastic longitudinal rod (31) is spirally coiled after being bent, and the plurality of elastic longitudinal rods (31) are stacked in sequence in the axial direction of the storage tube (21).

8. The space net system according to claim 7, characterized in that: In the direction of the axis of the storage cylinder (21), an elastic cross bar (32) is connected between each two adjacent elastic longitudinal bars (31), and the elastic cross bar (32) can be elastically deformed when the elastic arm (3) is coiled.

9. The space net system according to claim 1, characterized in that: The rotating arm (5) comprises a base (51), a rotating rod (52) and an elastic member (53); The base (51) is mounted on the locking mechanism (4), the rotating rod (52) is rotatably connected to the base (51), the edge of the space net (6) is connected to the rotating rod (52), the elastic member (53) is connected between the base (51) and the rotating rod (52), and the elastic force of the elastic member (53) drives the rotating rod (52) to rotate in a direction away from the locking mechanism (4); A positioning platform (55) is formed on the top side of the base (51), and a positioning end (54) is formed on one end of the rotating rod close to the base. When the space net (6) is at the specified position, the positioning end (54) abuts against the positioning platform (55) to limit the rotation of the rotating rod (52) relative to the base (51); And / or, the base (51) is provided with an arc surface (57), the arc surface (57) is recessed to form a positioning groove, the rotating rod (52) is provided with a limiting protrusion (56) that can rotate relative to the rotating rod (52), a spring is connected between the limiting protrusion (56) and the rotating rod (52), and the spring drives the limiting protrusion (56) to abut against the arc surface (57); When the space net (6) is in the locking position, the limiting protrusion (56) abuts against the arc surface (57) and is spaced from the positioning groove. When the space net (6) is in the designated position, the limiting protrusion (56) is plugged into the positioning groove to limit the rotation of the rotating rod (52) relative to the base (51).

10. The space net system according to claim 1, characterized in that: The locking mechanism (4) comprises a plate assembly and a limiting member (44), the plate assembly being mounted on the surface side of the spacecraft body (1), the limiting member (44) being mounted on a side of the plate assembly away from the spacecraft body (1), and the rotating arm (5) being mounted on the plate assembly; When the space net (6) is in the locked position, the space net (6) is attached to a side of the plate assembly away from the spacecraft body (1); The limiting member (44) can be switched between a limiting state and a disengaged state. When the limiting member (44) is in the limiting state, the limiting member (44) abuts against a side of the space net (6) at the locked position facing away from the plate assembly to limit the movement of the space net (6) in a direction away from the plate assembly. When the limiting member (44) is in the disengaged state, the limiting member (44) is out of contact with the space net (6), so that the space net (6) can move to the designated position.

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