Satellite-rocket separation device

Abstract

The present invention provides a satellite-rocket separation device, comprising: a first connecting body and a second connecting body, the first connecting body is connected to the satellite, the second connecting body is connected to the rocket, and the first connecting body and the second connecting body are separably connected; a locking mechanism, the locking mechanism is arranged on the second connecting body, wherein the locking mechanism has a locking position and a separation position, when the locking mechanism is in the locking position, the first connecting body is locked on the second connecting body, and when the locking mechanism is in the separation position, the first connecting body is separated from the second connecting body; a driving mechanism, the driving mechanism is connected to the locking mechanism to drive the locking mechanism to move between the locking position and the separation position, wherein the driving mechanism comprises a driving motor and a cam assembly, the driving motor is drivingly connected to the cam assembly to control the movement of the locking mechanism through the cam assembly. The satellite-rocket separation device of the present invention solves the problems of insecurity and environmental unfriendliness of the satellite-rocket separation device in the prior art.

Description

Technical Field

[0001] The present invention relates to the field of space technology, and more particularly, to a satellite-rocket separation device. Background Art

[0002] Satellite-rocket separation devices are mainly divided into: pyrotechnic separation devices, pyrotechnic belt separation devices, non-pyrotechnic belt separation devices, and pyrotechnic belt separation devices. Due to the different shapes of satellites, the designs of satellite-rocket separation devices are also different. Their common feature is that most of them use spring ejection separation, and the separation driving methods are mainly explosive bolts, motor drive, resistance wire fusing, electromagnetic drive, etc.

[0003] The design of satellite-rocket separation devices needs to comprehensively consider requirements such as simple structure, light weight, separation accuracy, anti-interference ability, small separation pollution, and high reliability. Currently, there are various satellite-rocket separation devices. Traditional satellite-rocket separation systems use pyrotechnic separation devices, and their disadvantages are that the safety of explosive bolts is unknown and the explosion shock is large. Therefore, the safety is poor and the impact load is large. Non-pyrotechnic belt separation devices come in various forms, but they have disadvantages such as expensive belts and the belts are prone to jamming the satellite during separation. Currently, non-belt satellite-rocket analysis devices are mostly used. Among them, the separation drive is mainly divided into forms of electric drive, electromagnetic drive, and direct drive by resistance fusing. After being energized, they will generate a certain magnetic field, which affects the operation of some precision satellite instruments and is unreliable. Summary of the Invention

[0004] The main object of the present invention is to provide a satellite-rocket separation device to solve the problems of insecurity and environmental unfriendliness of existing satellite-rocket separation devices.

[0005] To achieve the above object, according to one aspect of the present invention, there is provided a satellite-rocket separation device, including: a first connecting body and a second connecting body, the first connecting body is connected to the satellite, the second connecting body is connected to the rocket, and the first connecting body and the second connecting body are separably connected; a locking mechanism, the locking mechanism is arranged on the second connecting body, wherein the locking mechanism has a locking position and a separation position. When the locking mechanism is in the locking position, the first connecting body is locked to the second connecting body, and when the locking mechanism is in the separation position, the first connecting body is separated from the second connecting body; a driving mechanism, the driving mechanism is connected to the locking mechanism to drive the locking mechanism to move between the locking position and the separation position, wherein the driving mechanism includes a driving motor and a cam assembly, and the driving motor is drivingly connected to the cam assembly to control the movement of the locking mechanism through the cam assembly.

[0006] Further, the locking mechanism includes: a claw assembly, the claw assembly is arranged on the second connecting body so that the second connecting body is detachably connected to the first connecting body through the claw assembly.

[0007] Further, the jaw assembly includes: a plurality of jaws, which are spaced apart and arranged on the second connecting body to form an annular structure. Among them, each jaw is arranged to be contractible in the radial direction of the annular structure so as to move towards each other simultaneously to the separation position or move away from each other simultaneously to the locking position.

[0008] Further, a positioning protrusion is provided on the jaw, and a positioning hole is provided on the first connecting body. When the locking mechanism moves to the locking position, the positioning protrusion is inserted into the positioning hole to fix the first connecting body and the jaw together. When the locking mechanism moves to the separation position, the positioning protrusion disengages from the positioning hole to separate the first connecting body and the jaw.

[0009] Further, the satellite-rocket separation device further includes: a snap ring assembly, which is connected to each of the plurality of jaws. Among them, the driving mechanism drives the plurality of jaws to move simultaneously through the snap ring assembly.

[0010] Further, the snap ring assembly includes a snap ring, which is sleeved outside the jaw assembly. Among them, the snap ring is an unclosed annular structure, and the snap ring has a first driving end and a second driving end. The driving mechanism drives the first driving end and the second driving end to move closer to or away from each other simultaneously, so as to drive the plurality of jaws to move closer to or away from each other simultaneously.

[0011] Further, the satellite-rocket separation device further includes a slider mechanism, which is arranged on the second connecting body. Among them, the slider mechanism includes: a slide rail assembly, which is arranged on the second connecting body; a locking block, which is movably arranged on the slide rail assembly and is simultaneously drivingly connected to the first driving end and the second driving end; among them, the driving mechanism is drivingly connected to the locking block, and the locking block has a first position and a second position, so as to drive the first driving end and the second driving end to move closer to each other when the locking block moves to the first position, and drive the first driving end and the second driving end to move away from each other when the locking block moves to the second position.

[0012] Further, the satellite-rocket separation device further includes: an ejection mechanism, which is arranged on the second connecting body and is drivingly connected to the first connecting body to drive the first connecting body and the second connecting body to separate when the locking mechanism moves to the separation position.

[0013] Further, the ejection mechanism includes: a plurality of springs, which are evenly distributed on the second connecting body to be respectively connected to different positions of the first connecting body. Among them, each spring is in a compressed state to push the first connecting body to move when the locking mechanism moves to the separation position.

[0014] The satellite-rocket separation device applying the technical solution of the present invention is mainly used to control the separation of the satellite and the rocket when they are separated. Specifically, the first connecting body of the rocket separation device is fixed to the satellite, and the second connecting body is fixed to the rocket. The satellite is connected to the rocket through this satellite-rocket separation device. When the satellite and the rocket are separated, the driving motor of the driving mechanism works, and the driving cam assembly rotates to drive the locking mechanism to move from the locking position to the separation position. When the locking mechanism moves to the separation position, the first connecting body and the second connecting body can be separated. At this time, giving the satellite a thrust away from the rocket can separate the first connecting body and the second connecting body. The separation device of the present invention uses mechanical structure actions to complete the satellite-rocket separation, which is more environmentally friendly than the pyrotechnic separation device, safer and more reliable than the electromagnetic separation, and will not interfere with other devices. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The accompanying drawings forming a part of this application are used to provide a further understanding of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:

[0016] Figure 1 shows a schematic structural diagram of an embodiment of the satellite-rocket separation device according to the present invention;

[0017] Figure 2 shows a partial structural diagram of an embodiment of the satellite-rocket separation device of the present invention;

[0018] Figure 3 shows an exploded schematic diagram of an embodiment of the satellite-rocket separation device of the present invention;

[0019] Figure 4 shows a schematic diagram of an embodiment of the claw of the satellite-rocket separation device of the present invention;

[0020] Figure 5 shows a schematic diagram of an embodiment of the ejection mechanism of the satellite-rocket separation device of the present invention;

[0021] Figure 6 shows a schematic diagram of an embodiment of the snap ring assembly of the satellite-rocket separation device of the present invention;

[0022] Figure 7 shows a schematic diagram of an embodiment of the driving mechanism of the satellite-rocket separation device of the present invention.

[0023] Among them, the above-mentioned accompanying drawings include the following reference numerals:

[0024] 10. First connecting body; 11. Positioning hole; 20. Second connecting body; 30. Locking mechanism; 31. Claw; 311. Positioning projection; 40. Snap ring; 41. Driving motor; 42. Cam assembly; 43. First driving end; 44. Second driving end; 45. First lock block structure; 46. Second lock block structure; 51. Locking block; 52. Slide rail assembly; 60. Spring. Detailed implementation mode

[0025] It should be noted that, without conflict, the embodiments in this application and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the drawings and in combination with the embodiments.

[0026] In order to solve the problems of insecurity and non-environmental protection in the prior art star-rocket separation device, the present invention provides a star-rocket separation device.

[0027] Please refer to Figures 1 to 7 , a star-rocket separation device, comprising: a first connecting body 10 and a second connecting body 20, the first connecting body 10 is connected to the satellite, the second connecting body 20 is connected to the rocket, and the first connecting body 10 and the second connecting body 20 are detachably connected; a locking mechanism 30, the locking mechanism 30 is arranged on the second connecting body 20, wherein, the locking mechanism 30 has a locking position and a separation position, when the locking mechanism 30 is in the locking position, the first connecting body 10 is locked on the second connecting body 20, and when the locking mechanism 30 is in the separation position, the first connecting body 10 is separated from the second connecting body 20; a driving mechanism, the driving mechanism is connected to the locking mechanism 30 to drive the locking mechanism 30 to move between the locking position and the separation position, wherein, the driving mechanism includes a driving motor 41 and a cam assembly 42, the driving motor 41 is drivingly connected to the cam assembly 42 to control the movement of the locking mechanism 30 through the cam assembly 42.

[0028] The star-rocket separation device of the present invention is mainly applied when the satellite and the rocket are separated, to control the separation of the satellite and the rocket. Specifically, the first connecting body 10 of the rocket separation device is fixed together with the satellite, the second connecting body 20 is fixed on the rocket, the satellite is connected to the rocket through the star-rocket separation device. During star-rocket separation, the driving motor 41 of the driving mechanism works, drives the cam assembly 42 to rotate to drive the locking mechanism 30 to move from the locking position to the separation position. When the locking mechanism 30 moves to the separation position, the first connecting body 10 and the second connecting body 20 can be separated. At this time, giving the satellite a thrust away from the rocket can separate the first connecting body 10 and the second connecting body 20. The separation device of the present invention uses mechanical structure actions to complete star-rocket separation, which is more environmentally friendly than the pyrotechnic separation device, safer and more reliable than the electromagnetic separation, and will not cause interference to other devices.

[0029] The locking mechanism 30 includes: a claw assembly, which is arranged on the second connecting body 20 so that the second connecting body 20 is clamped and connected to the first connecting body 10 through the claw assembly.

[0030] The claw assembly includes: a plurality of claws 31, which are arranged on the second connecting body 20 at intervals to form an annular structure. Among them, each claw 31 is arranged to be contractible in the radial direction of the annular structure so as to move closer to each other to the separation position or move away from each other to the locking position simultaneously.

[0031] As Figure 3 and Figure 4 As shown, the locking mechanism 30 in this embodiment connects the first connecting body 10 and the second connecting body 20 in a clamping manner. Specifically, both the first connecting body 10 and the second connecting body 20 are annular structures. A plurality of claws 31 are evenly distributed on the second connecting body 20 and form an annular structure. The claw 31 can move and contract parallel to the radial direction of the annular structure, or one end of the claw 31 is rotatably connected to the second connecting body 20, and the other end of the claw 31 rotates inward or outward along the radial direction under the drive of the snap ring 40.

[0032] Preferably, the claw 31 is rotatably arranged on the second connecting body 20. Specifically, a rotating shaft and a torsion spring are arranged on the second connecting body 20. The claw 31 is rotatably arranged on the rotating shaft, and the torsion spring gives the claw 31 a thrust to expand outward so that the positioning protrusion 311 on the claw 31 is inserted into the positioning hole 11 to make the locking mechanism 30 in the locking position.

[0033] The claw 31 is provided with a positioning protrusion 311, and the first connecting body 10 is provided with a positioning hole 11. When the locking mechanism 30 moves to the locking position, the positioning protrusion 311 is inserted into the positioning hole 11 to fix the first connecting body 10 and the claw 31 together. When the locking mechanism 30 moves to the separation position, the positioning protrusion 311 disengages from the positioning hole 11 to separate the first connecting body 10 and the claw 31.

[0034] As Figure 4 As shown, two positioning protrusions 311 are arranged on the outer side of the claw 31 in this embodiment. Correspondingly, two positioning holes 11 are arranged on the first connecting body 10 to be respectively used for cooperating with the positioning protrusions 311. When the snap ring 40 contracts inward, it drives the upper part to rotate inward to the inner side of the annular structure, so that the positioning protrusion 311 disengages from the positioning hole 11. When the snap ring 40 expands and tightens outward, the claw 31 rotates outward under the drive of the torsion spring so that the positioning protrusion 311 is inserted into the positioning hole 11, thereby fixing the snap ring 40 and the claw 31 together.

[0035] The star-arrow separation device further includes: a snap ring assembly, the snap ring assembly is connected to each of the plurality of claws 31, wherein the driving mechanism drives the plurality of claws 31 to move simultaneously through the snap ring assembly.

[0036] The snap ring assembly includes a snap ring 40, the snap ring 40 is sleeved outside the claw assembly, wherein the snap ring 40 is an unclosed ring structure, the snap ring 40 has a first driving end 43 and a second driving end 44, and the driving mechanism drives the first driving end 43 and the second driving end 44 to move closer to or away from each other simultaneously, so as to drive the plurality of claws 31 to move closer to or away from each other simultaneously.

[0037] As Figure 6 shown, in this embodiment, a semi-closed annular snap ring 40 is sleeved outside the claw assembly. When the driving mechanism drives the snap ring 40 to contract, it will push each claw 31 inward to move. When the snap ring 40 expands outward, the claws 31 move outward under the action of an external force. Specifically, the locking block 51 is fixed to one end of the slider assembly by bolts or is blocked at one end of the slide rail assembly 52 by a stop block. At this time, the snap ring 40 is in a tensioned state, and the positioning protrusion 311 on the claw 31 is inserted into the positioning hole 11. When the star-arrow separates, the first driving end 43 and the second driving end 44 of the snap ring 40 contract inward under the action of their own elastic force, driving the locking block 51 to move along the slide rail assembly 52. At this time, each claw 31 rotates inward, so that the positioning protrusion 311 disengages from the positioning hole 11, and then the first connecting body 10 moves upward under the push of the spring 60 to separate from the second connecting body 20.

[0038] The star-arrow separation device further includes a slider mechanism, the slider mechanism is arranged on the second connecting body 20, wherein the slider mechanism includes:

[0039] A slide rail assembly 52, the slide rail assembly 52 is arranged on the second connecting body 20; a locking block 51, the locking block 51 is movably arranged on the slide rail assembly 52 and is simultaneously drivingly connected to the first driving end 43 and the second driving end 44; wherein, the driving mechanism is drivingly connected to the locking block 51, and the locking block 51 has a first position and a second position, so as to drive the first driving end 43 and the second driving end 44 to move closer to each other when the locking block 51 moves to the first position, and drive the first driving end 43 and the second driving end 44 to move away from each other when the locking block 51 moves to the second position.

[0040] As Figure 3As shown, in this embodiment, the slide rail assembly 52 includes a linear slide rail. The linear slide rail extends along the radial direction of the annular structure and is installed on the second connecting body 20 by bolts. A locking block 51 is provided on the linear slide rail to move the plug cover along the linear slide rail. An elastic pin is installed on the plug cover, and a stop block is installed on the linear guide rail. The locking block 51 is a wedge-shaped block and is installed on the stop block. The locking block 51 is respectively connected to the first driving end 43 and the second driving end 44. When the locking block 51 moves inward along the linear slide rail, the first driving end 43 and the second driving end 44 approach each other, so that the snap ring 40 contracts; when the locking block 51 moves outward along the linear slide rail, the first driving end 43 and the second driving end 44 move away from each other, so that the snap ring 40 expands and tightens.

[0041] The satellite-rocket separation device further includes an ejection mechanism. The ejection mechanism is arranged on the second connecting body 20 and is drivingly connected to the first connecting body 10 to drive the separation of the first connecting body 10 and the second connecting body 20 when the locking mechanism 30 moves to the separation position.

[0042] The ejection mechanism includes a plurality of springs 60. The plurality of springs 60 are evenly distributed on the second connecting body 20 to be respectively connected to different positions of the first connecting body 10. Among them, each spring 60 is in a compressed state to push the first connecting body 10 to move when the locking mechanism 30 moves to the separation position.

[0043] When the locking mechanism 30 moves to the separation position, an external force is required to push the first connecting body 10 away from the second connecting body 20 at this time. In this embodiment, a week of guide posts are arranged on the second connecting body 20, and the spring 60 is sleeved on the guide posts to ensure that the spring 60 always moves along the vertical direction. When the locking mechanism 30 is in the locking position, the first connecting body 10 and the second connecting body 20 are locked together, and the spring 60 is in a compressed state. When the locking mechanism 30 is in the separation position, the spring 60 pushes the first connecting body 10 to separate from the second connecting body 20 upward. In order to ensure the stable attitude of the satellite after separation, the springs 60 should be evenly distributed when arranged.

[0044] In addition, as Figure 7 shown, the cam mechanism includes a first lock block structure 45, a cam, and a second lock block structure 46. The drive motor 41 pushes the stop block to move through the cam mechanism to lock the locking block 51 or move the locking block 51 along the linear slide rail.

[0045] The satellite-rocket separation device of the present invention also reserves the installation positions for the separation switches of the satellite and the rocket. The separation switch for the satellite and the satellite sensor plug are installed on the first connecting body. The separation switch for the rocket and the satellite sensor socket are installed on the second connecting body. The satellite sensor socket and the plug can customize the communication interface according to needs.

[0046] From the above description, it can be seen that the above embodiments of the present invention achieve the following technical effects:

[0047] The satellite-rocket separation device of the present invention is mainly applied when the satellite and the rocket are separated to control the separation of the satellite and the rocket. Specifically, the first connecting body 10 of the rocket separation device is fixed to the satellite, and the second connecting body 20 is fixed to the rocket. The satellite is connected to the rocket through this satellite-rocket separation device. During satellite-rocket separation, the driving motor 41 of the driving mechanism operates, and the driving cam assembly 42 rotates to drive the locking mechanism 30 to move from the locking position to the separation position. When the locking mechanism 30 moves to the separation position, the first connecting body 10 and the second connecting body 20 can be separated. At this time, giving the satellite a thrust away from the rocket can separate the first connecting body 10 and the second connecting body 20. The separation device of the present invention uses mechanical structure actions to complete satellite-rocket separation, which is more environmentally friendly than the pyrotechnic separation device, safer and more reliable than the electromagnetic separation, and will not cause interference to other devices.

[0048] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or their combinations.

[0049] Unless otherwise specifically stated, the relative arrangements, numerical expressions, and numerical values of the components and steps described in these embodiments do not limit the scope of the present invention. At the same time, it should be understood that for the convenience of description, the dimensions of the various parts shown in the drawings are not drawn according to the actual proportional relationship. Technologies, methods, and devices known to those of ordinary skill in the relevant art may not be discussed in detail, but in appropriate cases, the technologies, methods, and devices should be regarded as part of the authorization specification. In all the examples shown and discussed here, any specific value should be interpreted as merely exemplary and not as a limitation. Therefore, other examples of the exemplary embodiments may have different values. It should be noted that like reference numerals and letters denote like items in the following drawings. Therefore, once an item is defined in one drawing, it does not need to be further discussed in subsequent drawings.

[0050] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by orientation words such as "front, back, up, down, left, right", "lateral, vertical, perpendicular, horizontal" and "top, bottom", etc. is usually based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description. Without contrary explanation, these orientation words do not indicate and imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation on the protection scope of the present invention; the orientation words "inside, outside" refer to the inside and outside relative to the contour of each component itself.

[0051] For the convenience of description, spatial relative terms such as "above...", "over...", "on the upper surface of...", "upper" etc. can be used here to describe the spatial positional relationship between a device or feature shown in the drawings and other devices or features. It should be understood that the spatial relative terms are intended to include different orientations in use or operation other than the orientation described in the drawings for the device. For example, if the device in the drawing is inverted, the device described as "above other devices or structures" or "over other devices or structures" will then be positioned as "below other devices or structures" or "under other devices or structures". Thus, the exemplary term "above..." can include both the orientations of "above..." and "below...". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the corresponding explanations for the spatial relative descriptions used here are made accordingly.

[0052] In addition, it should be noted that using words such as "first", "second" etc. to limit components is only for the convenience of distinguishing the corresponding components. Without otherwise stated, the above words have no special meaning. Therefore, it should not be construed as a limitation on the protection scope of the present invention.

[0053] The above are only the preferred embodiments of the present invention and are not used to limit the present invention. For those skilled in the art, the present invention can have various changes and modifications. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A satellite-rocket separation device, characterized in that, it includes: a first connector (10) and a second connector (20), the first connector (10) is connected to the satellite, the second connector (20) is connected to the rocket, and the first connector (10) and the second connector (20) are detachably connected; a locking mechanism (30), the locking mechanism (30) is arranged on the second connector (20), wherein the locking mechanism (30) has a locking position and a separation position, when the locking mechanism (30) is in the locking position, the first connector (10) is locked on the second connector (20), and when the locking mechanism (30) is in the separation position, the first connector (10) is separated from the second connector (20); a driving mechanism, the driving mechanism is connected to the locking mechanism (30) to drive the locking mechanism (30) to move between the locking position and the separation position, wherein the driving mechanism includes a driving motor (41) and a cam assembly (42), the driving motor (41) is drivingly connected to the cam assembly (42) to control the movement of the locking mechanism (30) through the cam assembly (42); the locking mechanism (30) includes a claw assembly, the claw assembly is arranged on the second connector (20) so that the second connector (20) is clamped and connected to the first connector (10) through the claw assembly, the claw assembly includes a plurality of claws (31), the plurality of claws (31) are arranged at intervals on the second connector (20) to form an annular structure, and each claw (31) is arranged to be contractible in the radial direction of the annular structure so as to move towards each other simultaneously to the separation position or move away from each other simultaneously to the locking position; the satellite-rocket separation device further includes a snap ring assembly, the snap ring assembly is connected to the plurality of claws (31), wherein the driving mechanism drives the plurality of claws (31) to move simultaneously through the snap ring assembly; the satellite-rocket separation device further includes an ejection mechanism, the ejection mechanism is arranged on the second connector (20), and the ejection mechanism is drivingly connected to the first connector (10) to drive the first connector (10) to separate from the second connector (20) when the locking mechanism (30) moves to the separation position.

2. The satellite-rocket separation device according to claim 1, characterized in that, the claw (31) is provided with a positioning protrusion (311), the first connector (10) is provided with a positioning hole (11), when the locking mechanism (30) moves to the locking position, the positioning protrusion (311) is inserted into the positioning hole (11) to fix the first connector (10) and the claw (31) together, and when the locking mechanism (30) moves to the separation position, the positioning protrusion (311) disengages from the positioning hole (11) to separate the first connector (10) from the claw (31).

3. The star-arrow separation device according to claim 1, characterized in that the snap ring assembly includes a snap ring (40), the snap ring (40) is sleeved outside the claw assembly, wherein the snap ring (40) is an unclosed ring structure, the snap ring (40) has a first driving end (43) and a second driving end (44), and the driving mechanism simultaneously drives the first driving end (43) and the second driving end (44) to move closer to or away from each other, so as to drive a plurality of the claws (31) to move closer to or away from each other simultaneously.

4. The star-arrow separation device according to claim 3, characterized in that the star-arrow separation device further includes a slider mechanism, the slider mechanism is arranged on the second connecting body (20), wherein the slider mechanism includes: a slide rail assembly (52), the slide rail assembly (52) is arranged on the second connecting body (20); a locking block (51), the locking block (51) is movably arranged on the slide rail assembly (52) and is simultaneously drivingly connected to the first driving end (43) and the second driving end (44); wherein, the driving mechanism is drivingly connected to the locking block (51), the locking block (51) has a first position and a second position, so as to drive the first driving end (43) and the second driving end (44) to move closer to each other when the locking block (51) moves to the first position, and drive the first driving end (43) and the second driving end (44) to move away from each other when the locking block (51) moves to the second position.

5. The star-arrow separation device according to claim 1, characterized in that the ejection mechanism includes: a plurality of springs (60), the plurality of springs (60) are evenly distributed on the second connecting body (20) to be respectively connected to different positions of the first connecting body (10), wherein each of the springs (60) is in a compressed state to push the first connecting body (10) to move when the locking mechanism (30) moves to the separation position.

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