Satellite launch box ejection device

Abstract

Disclosed is a satellite launch box ejection device (100), comprising: a lower fixing plate (101); an upper fixing plate (102); a central axis (201); a first shaft sleeve (202); a second shaft sleeve (203); a first connecting rod group and a second connecting rod group, wherein the first end of each first connecting rod (106) and the second connecting rod (107) are pivotally connected to the first shaft sleeve (202) and the second shaft sleeve (203), respectively, and the second end of each first connecting rod (106) and the second connecting rod (107) are pivotally connected to the first shaft sleeve (202) and the second shaft sleeve (203), respectively. a pull ring (103); a tension spring group, wherein the first end of each tension spring (108) is connected to the pull ring (103), and the second end is connected to the second end of the first connecting rod (106) and the second connecting rod (107); and a locking release mechanism, which is used to switch the device (100) from a locked state to a released state, so that under the restoring action of the tension spring group in a stretched state, the first and second connecting rod groups are opened to each other, and the upper fixing plate (102) is driven to be ejected through the second shaft sleeve (203), thereby ejecting and releasing the satellite.

Description

Technical Field

[0001] The invention relates to the field of aerospace technology, and in particular to an ejection device for a satellite launch box. Background Art

[0002] With the rapid development of aerospace technology, the frequency of satellite launches in my country is getting higher and higher, and the number of satellite launches is increasing. The ejection device of the satellite launch box is an indispensable device for satellite launch. After the satellite is launched into space by a rocket, it is necessary to complete the separation of the satellite and the rocket. The ejection device is the driving device that completes the separation of the satellite and the rocket and ejects the satellite from the launch box into space. Therefore, the design of the ejection device must strictly control the weight of the mechanism and ensure that the system has the characteristics of high reliability, high performance, and high operability.

[0003] At present, most of the mechanisms used to realize the satellite ejection function rely on the recovery of the compression spring after compression to realize the ejection of the satellite from the launch box. Although this device has a simple structure and light weight, it is limited by the characteristics of the spring itself, and the ejection stroke, elastic force and elastic force uniformity are limited, especially for large-sized satellites. Summary of the invention

[0004] To this end, according to an embodiment of the present invention, a satellite launch box ejection device 100 is proposed, which includes:

[0005] Lower fixing plate 101;

[0006] An upper fixing plate 102, on which the satellite is placed;

[0007] A central axis 201 passing through or located at the center of the lower fixing plate 101 and the upper fixing plate 102;

[0008] A first sleeve 202, which is mounted on the central shaft 201;

[0009] A second sleeve 203 is mounted on the central shaft 201, wherein the first sleeve 202 and the second sleeve 203 are located between the lower fixing plate 101 and the upper fixing plate 102, and the first sleeve 202 and the second sleeve 203 can slide relative to each other along the central shaft 201;

[0010] A first link assembly, comprising a first number of first links 106 arranged circumferentially along the central axis 201, wherein a first end of each first link 106 is pivotally connected to the first sleeve 202;

[0011] A second link assembly, comprising a first number of second links 107 arranged circumferentially along the central axis 201, wherein a first end of each second link 107 is pivotally connected to the second sleeve 203, wherein a second end of each first link 106 is pivotally connected to a second end of a corresponding second link 107;

[0012] The pull ring 103 is directly or indirectly mounted on the central shaft 201 and is located between the first sleeve 202 and the second sleeve 203;

[0013] a tension spring assembly, comprising a second number of tension springs 108 arranged circumferentially along the central axis 201, wherein the second number is equal to the first number or equal to twice the first number, and a first end of each tension spring 108 is connected to the pull ring 103, and a second end is connected to the second end of the corresponding first connecting rod 106 and second connecting rod 107; and

[0014] The locking release mechanism is used to switch the satellite launch box ejection device 100 from a locked state to a released state, wherein in the locked state, the first shaft sleeve 202 and the second shaft sleeve 203 are close to each other, the first connecting rod group and the second connecting rod group are folded with each other, and the tension spring group is in a stretched state. Therefore, under the restoring action of the tension spring group, the first connecting rod group and the second connecting rod group are opened to each other, and the first shaft sleeve 202 and the second shaft sleeve 203 are moved away from each other, driving the upper fixed plate 102 to eject relative to the lower fixed plate 101, thereby ejecting and releasing the satellite.

[0015] The satellite launch box ejection device 100 according to the embodiment of the present invention realizes the ejection function through the combination of the connecting rod mechanism and the tension spring. The ejection mechanism can be freely opened and folded, and can realize smooth ejection without impact. It has a simple structure, high reliability, small size, light weight and low cost. Compared with the technical solution in the prior art that relies on the recovery effect of the compression spring after compression to realize the ejection of the satellite from the launch box, the ejection stroke and ejection force have been greatly improved, and the ejection stroke and ejection force can be adjusted as needed, and in some embodiments, the ejection with a larger stroke can be realized by superposition of multi-stage connecting rod mechanisms. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 A schematic perspective view of a satellite launch box ejection device according to an embodiment of the present invention is shown.

[0017] Figure 2 Another schematic perspective view of a satellite launch box ejection device according to an embodiment of the present invention is shown.

[0018] Figure 3 Another schematic perspective view of a satellite launch box ejection device according to an embodiment of the present invention is shown.

[0019] Figure 4 A partially exploded perspective view of a satellite launch box ejection device according to an embodiment of the present invention is shown.

[0020] Figure 5Another partially exploded perspective view of a satellite launch box ejection device according to an embodiment of the present invention is shown.

[0021] Figure 6 A view facing the lower base plate and several cross-sectional views of a satellite launch box ejection device according to an embodiment of the present invention are shown. DETAILED DESCRIPTION

[0022] Embodiments of the present invention are described in detail below with reference to the accompanying drawings. In the following description, many specific details are set forth so that those skilled in the art can more fully understand the present invention. However, it is obvious to those skilled in the art that the implementation of the present invention may not have some of these specific details. In addition, it should be understood that the present invention is not limited to the specific embodiments introduced. On the contrary, any combination of the following features and elements may be considered to implement the present invention, regardless of whether they relate to different embodiments. Therefore, the following aspects, features, embodiments and advantages are only for illustrative purposes and should not be regarded as elements or limitations of the claims, unless clearly stated in the claims.

[0023] The meanings of the terms involved in this specification are generally the usual meanings in the art, or the meanings normally understood by those skilled in the art after reading this specification. The terms "including" and "comprising" in this specification are open-ended, that is, in addition to the elements mentioned, other elements not mentioned may also be included. The terms "connected", "connected" and other similar terms in this specification generally include mechanical connections, electrical connections, communication connections or combinations thereof, and generally include both direct connections and indirect connections or connections via other components. The terms "first", "second", etc. in this specification are only used to distinguish different components of the same type, and do not indicate any order in terms of importance, structure, function, etc.

[0024] Now refer to Figure 1-6 ,in, Figure 1 A schematic perspective view of a satellite launch box ejection device 100 according to an embodiment of the present invention is shown; Figure 2 Another schematic perspective view of a satellite launch box ejection device 100 according to an embodiment of the present invention is shown, wherein components such as the electromagnet and the central axis housing on the lower bottom plate are removed; Figure 3 Another schematic perspective view of a satellite launch box ejection device 100 according to an embodiment of the present invention is shown, which more clearly shows the upper base plate; Figure 4 A partial exploded perspective view of a satellite launch box ejection device 100 according to an embodiment of the present invention is shown, which shows the internal structure and upper base plate of the satellite launch box ejection device; Figure 5Another partially exploded perspective view of a satellite launch box ejection device 100 according to an embodiment of the present invention is shown, which shows the internal structure and the lower base plate of the satellite launch box ejection device 100; Figure 6 A view facing the lower bottom plate of a satellite launch box ejection device 100 according to an embodiment of the present invention and several cross-sectional views are shown.

[0025] like Figure 1-6 As shown in FIG. 1 , a satellite launch box ejection device 100 according to an embodiment of the present invention includes:

[0026] Lower fixing plate 101;

[0027] An upper fixing plate 102, on which the satellite is placed;

[0028] A central axis 201 passing through or located at the center of the lower fixing plate 101 and the upper fixing plate 102;

[0029] A first sleeve 202, which is mounted on the central shaft 201;

[0030] A second sleeve 203 is mounted on the central shaft 201, wherein the first sleeve 202 and the second sleeve 203 are located between the lower fixing plate 101 and the upper fixing plate 102, and the first sleeve 202 and the second sleeve 203 can slide relative to each other along the central shaft 201;

[0031] A first link assembly, comprising a first number of first links 106 arranged circumferentially along the central axis 201, wherein a first end of each first link 106 is pivotally connected to the first sleeve 202;

[0032] A second link assembly, comprising a first number of second links 107 arranged circumferentially along the central axis 201, wherein a first end of each second link 107 is pivotally connected to the second sleeve 203, wherein a second end of each first link 106 is pivotally connected to a second end of a corresponding second link 107;

[0033] The pull ring 103 is directly or indirectly mounted on the central shaft 201 and is located between the first sleeve 202 and the second sleeve 203;

[0034] a tension spring assembly, comprising a second number of tension springs (i.e., extension springs) 108 arranged circumferentially along the central axis 201, wherein the second number is equal to the first number or twice the first number, and a first end of each tension spring 108 is connected to the pull ring 103, and a second end is connected to the second end of the corresponding first connecting rod 106 and second connecting rod 107; and

[0035] The locking release mechanism is used to switch the satellite launch box ejection device 100 from a locked state to a released state, wherein in the locked state, the first shaft sleeve 202 and the second shaft sleeve 203 are close to each other, the first connecting rod group and the second connecting rod group are folded with each other, and the tension spring group is in a stretched state. Therefore, under the restoring action of the tension spring group, the first connecting rod group and the second connecting rod group are opened to each other, and the first shaft sleeve 202 and the second shaft sleeve 203 are moved away from each other, driving the upper fixed plate 101 to eject relative to the lower fixed plate 102, thereby ejecting and releasing the satellite.

[0036] In some embodiments, Figure 4-6 As shown in , the first sleeve 202 is fixedly connected to the lower fixing plate 101, the second sleeve 203 is fixedly connected to the upper fixing plate 102 and the central shaft 201, and the central shaft 201 can slide in the first sleeve 202. For example, the first sleeve 202 can be fixedly connected to the lower fixing plate 101 by bolt connection or the like; the second sleeve 203 can be fixedly connected to the upper fixing plate 102 by bolt connection or the like, and can be fixedly connected to the central shaft 201 by interference fit, pin connection, key connection or the like.

[0037] In other embodiments, the first sleeve 202 is fixedly connected to the lower fixing plate 101 and the central shaft 201, the second sleeve 203 is fixedly connected to the upper fixing plate 102, and the central shaft 201 can slide in the second sleeve 203. For example, the first sleeve 202 can be fixedly connected to the lower fixing plate 101 by bolt connection or the like, and can be fixedly connected to the central shaft 201 by interference fit, pin connection, key connection or the like; the second sleeve 203 can be fixedly connected to the upper fixing plate 102 by bolt connection or the like.

[0038] In some embodiments, Figure 4-6 As shown in the figure, the first end of each first connecting rod 106 is pivotally connected to the first sleeve 202 via a first pin 104 arranged on the first sleeve 202; the second end of each first connecting rod 106 is pivotally connected to the second end of the corresponding second connecting rod 107 via a second pin 105; the first end of each second connecting rod 107 is pivotally connected to the second sleeve 203 via a third pin 109 arranged on the second sleeve 203.

[0039] In some embodiments, Figure 4-6 As shown in the figure, a pair of tension springs 108 are provided on both sides of each pair of first connecting rods 106 and corresponding second connecting rods 107 pivotally connected by the second pin shaft 105 at the second end, and the second ends of the pair of tension springs 108 are respectively connected to the two ends of the second pin shaft 105, and the first ends of the pair of tension springs 108 are respectively connected to the pull rings 103.

[0040] In some embodiments, Figure 6As shown in , the pull ring 103 is sleeved on a portion of the second sleeve 203. In other embodiments, the pull ring 103 can also be sleeved on a portion of the first sleeve 202, or directly sleeved on the central shaft 201.

[0041] In some embodiments, Figure 4-6 As shown in , a first number of multiple first links 106 of the first link group and a first number of multiple second links 107 of the second link group are evenly arranged along the circumferential direction of the central axis 201 .

[0042] In some embodiments, Figure 4-6 As shown in , the first number is 4. That is, the first connecting rod group includes 4 first connecting rods 106 arranged along the circumference of the central axis 201, and the second connecting rod group includes 4 second connecting rods 107 arranged along the circumference of the central axis 201. Correspondingly, the tension spring group includes 8 tension springs 108 arranged along the circumference of the central axis 201. In other embodiments, the first number may also be 3, 5, etc.

[0043] In some embodiments, the cross-sectional shape of the central axis 201 is circular. In other embodiments, the cross-sectional shape of the central axis 201 may also be other shapes, such as elliptical, square, hexagonal, etc.

[0044] In some embodiments, the satellite launch box ejection device 100 can be switched between a locked state and a released state. In the locked state, the first sleeve 202 and the second sleeve 203 are close to each other, the first connecting rod group and the second connecting rod group are folded with each other, and the multiple tension springs 108 in the tension spring group are in a stretched state; in the released state, the multiple tension springs 108 in the tension spring group are in a natural state, the first connecting rod group and the second connecting rod group are opened to each other, and the first sleeve 202 and the second sleeve 203 are away from each other.

[0045] In some embodiments, the locking release mechanism is used to lock the satellite launch box ejection device 100 in a locked state, and to release the satellite launch box ejection device 100 from a locked state, so that under the natural recovery action of the multiple tension springs 108 in a stretched state, the satellite launch box ejection device 100 is switched to a released state, that is, the first connecting rod group and the second connecting rod group are opened to each other, and the first shaft sleeve 202 and the second shaft sleeve 203 are moved away from each other, so that the upper fixed plate 101 is ejected relative to the lower fixed plate 102, and the satellite located on the upper fixed plate 102 is ejected and released.

[0046] In some embodiments, the lock release mechanism comprises:

[0047] The electromagnet 301 is fixed on the surface of the lower fixing plate 101 and includes a pull rod 302. The pull rod 302 extends when the electromagnet 301 is powered off and retracts when the electromagnet 301 is powered on.

[0048] A locking pin 303 connected to the pull rod 302;

[0049] In which, an annular groove 204 is provided on the lower outer surface of the central shaft 201, and the locking pin 303 is pushed by the pull rod 302 to clamp the annular groove 204 when the electromagnet 301 is powered off, thereby locking the satellite launch box ejection device 100 in a locked state; and the locking pin 303 is pulled out of the annular groove 204 by the pull rod 302 when the electromagnet 301 is powered on, thereby switching the satellite launch box ejection device 100 to a released state.

[0050] In some embodiments, the electromagnet 301 may be electrically connected to a satellite launch system on a rocket, and may be energized according to a launch command or electrical signal issued by the satellite launch system.

[0051] In some embodiments, the pull rod 302 of the electromagnet 301 is surrounded by a spring, which is pressed between the end faces of the electromagnet 301 and the locking pin 303. In this way, when the electromagnet 301 is powered off, the locking pin 303 is pressed against the annular groove 204 of the central axis 201, thereby locking the satellite launch box ejection device 100 in a locked state; when the electromagnet 301 is powered on, the pull rod 302 overcomes the resistance of the spring and drives the locking pin 303 to withdraw from the annular groove 204 of the central axis 201, so that the central axis 201, together with the second shaft sleeve 203 and the upper fixed plate 102, moves upward relative to the first shaft sleeve 202 and the lower fixed plate 101 under the restoring action of the tension spring group as the first connecting rod group and the second connecting rod group open to each other, thereby ejecting the satellite on the upper fixed plate 102.

[0052] In some embodiments, the locking pin 303 and the pull rod 302 may be connected together via a pin shaft 304 , and the pin shaft 304 may pass through pin holes provided on the locking pin 303 and the pull rod 302 to connect the two together.

[0053] As described above, in other embodiments, the first sleeve 202 is fixedly connected to the lower fixing plate 101 and the central shaft 201 , the second sleeve 203 is fixedly connected to the upper fixing plate 102 , and the central shaft 201 can slide in the second sleeve 203 . In such an embodiment, the locking release mechanism and its electromagnet 301 can be fixed on the surface of the upper fixed plate 101, and an annular groove 204 is provided on the upper outer surface of the central axis 201. When the electromagnet 301 is powered off, the locking pin 303 is pushed by the pull rod 302 to clamp the annular groove 204, thereby locking the satellite launch box ejection device 100 in a locked state; and when the electromagnet 301 is powered on, the pull rod 302 drives the locking pin 303 to withdraw from the annular groove 204 of the central axis 201, so that the second sleeve 203 and the upper fixed plate 102, under the recovery action of the tension spring group, move upward relative to the central axis 201, the first sleeve 202 and the lower fixed plate 101 as the first connecting rod group and the second connecting rod group open to each other, thereby ejecting the satellite on the upper fixed plate 102.

[0054] In some embodiments, the stretched length of the tension spring group in the locked state of the satellite launch box ejection device 101 depends on the ejection stroke required by the satellite launch box ejection device 100, and / or the elastic modulus of the tension spring group depends on the ejection force required by the satellite launch box ejection device. That is, the stretched length and elastic modulus of the tension spring group can be determined or adjusted according to the required ejection stroke and ejection force. If the ejection stroke required by the satellite launch box ejection device 100 is larger, the stretched length of each tension spring 108 in the tension spring group in the locked state of the satellite launch box ejection device 101 is made larger; if the ejection force required by the satellite launch box ejection device 100 is larger, the elastic modulus of each tension spring 108 in the tension spring group is made larger. As known to those skilled in the art, the elastic modulus of the tension spring is related to the material, shape and thickness of the tension spring, so the appropriate elastic modulus can be selected by selecting a tension spring of appropriate material (such as spring steel, etc.), shape and thickness.

[0055] In some embodiments, there are multiple first sleeves 202, second sleeves 203, first connecting rod group, second connecting rod group, pull ring 103 and tension spring group, and they are repeatedly arranged along the central axis 201 between the upper fixing plate 102 and the lower fixing plate 101, and among the multiple first sleeves 202, only the first sleeve 202 close to the lower fixing plate 101 is fixedly connected to the lower fixing plate 101, and among the multiple second sleeves 203, only the second sleeve 203 close to the upper fixing plate 102 is fixedly connected to the upper fixing plate 102, and the remaining adjacent first sleeves 202 and second sleeves 203 are integrated or fixedly connected to each other. That is to say, the paired first connecting rod group and second connecting rod group and the corresponding tension spring group can be arranged in multiple stages in a superimposed manner along the central axis 201, so that the ejection stroke of the satellite launch box ejection device 100 can be further significantly increased.

[0056] In some embodiments, the relevant structural parts (except the tension spring) of the satellite launch box ejection device 101 can be made of lighter materials such as magnesium-aluminum alloy to further reduce the weight.

[0057] The satellite launch box ejection device 100 according to an embodiment of the present invention is described above with reference to the accompanying drawings. It should be noted that the above description and illustration are only examples and are not limitations of the present invention. In other embodiments of the present invention, the device may have more, fewer or different components, and the connection, inclusion and function relationships between the components may be different from those described and illustrated. For example, in addition to the illustrated and described subcomponents, a component may also include other subcomponents; multiple components may be combined into a larger component, and so on. All of these changes are within the spirit and scope of the present invention.

[0058] The satellite launch box ejection device 100 according to the embodiment of the present invention realizes the ejection function through the combination of the connecting rod mechanism and the tension spring. The ejection mechanism can be freely opened and folded, and can realize smooth ejection without impact. It has a simple structure, high reliability, small size, light weight and low cost. Compared with the technical solution in the prior art that relies on the recovery effect of the compression spring after compression to realize the ejection of the satellite from the launch box, the ejection stroke and ejection force have been greatly improved, and the ejection stroke and ejection force can be adjusted as needed, and in some embodiments, the ejection with a larger stroke can be realized by superposition of multi-stage connecting rod mechanisms.

[0059] Although the present invention has been disclosed as above through the embodiments, the present invention is not limited thereto. Various changes and modifications made by those skilled in the art without departing from the spirit and scope of the present invention should be included in the protection scope of the present invention, and the protection scope of the present invention shall only be subject to the scope defined by the language of the claims and their equivalents.

Claims

1. A satellite launch box ejection device (100), include: Lower fixing plate (101); An upper fixing plate (102) on which a satellite is placed; A central axis (201) passing through or located at the center of the lower fixing plate (101) and the upper fixing plate (102); A first sleeve (202) mounted on the central shaft (201); A second shaft sleeve (203) mounted on the central shaft (201), wherein the first shaft sleeve (202) and the second shaft sleeve (203) are located between the lower fixing plate (101) and the upper fixing plate (102), and the first shaft sleeve (202) and the second shaft sleeve (203) are capable of relative sliding along the central shaft (201); A first connecting rod assembly, comprising a first number of first connecting rods (106) arranged circumferentially along a central axis (201), wherein a first end of each first connecting rod (106) is pivotally connected to a first shaft sleeve (202); A second link assembly, comprising a first number of second links (107) arranged circumferentially along the central axis (201), wherein a first end of each second link (107) is pivotally connected to a second sleeve (203), wherein a second end of each first link (106) is pivotally connected to a second end of a corresponding second link (107); A pull ring (103) which is directly or indirectly mounted on the central shaft (201) and is located between the first shaft sleeve (202) and the second shaft sleeve (203); A tension spring assembly, comprising a second number of tension springs (108) arranged circumferentially along a central axis (201), wherein the second number is equal to the first number or equal to twice the first number, and a first end of each tension spring (108) is connected to a pull ring (103), and a second end is connected to the second end of a corresponding first connecting rod (106) and a second connecting rod (107); and A locking release mechanism is used to switch the satellite launch box ejection device (100) from a locked state to a released state, wherein in the locked state, the first shaft sleeve (202) and the second shaft sleeve (203) are close to each other, the first connecting rod group and the second connecting rod group are folded together, and the tension spring group is in a stretched state, so that under the restoring action of the tension spring group, the first connecting rod group and the second connecting rod group are opened to each other, the first shaft sleeve (202) and the second shaft sleeve (203) are moved away from each other, and the upper fixing plate (102) is driven to be ejected relative to the lower fixing plate (101), thereby ejecting and releasing the satellite.

2. The satellite launch box ejection device according to claim 1, in, The first shaft sleeve (202) is fixedly connected to the lower fixing plate (101), the second shaft sleeve (203) is fixedly connected to the upper fixing plate (102) and the central shaft (201), and the central shaft (201) is capable of sliding in the first shaft sleeve (202).

3. The satellite launch box ejection device according to claim 2, in, The locking release mechanism comprises: An electromagnet (301) is fixed on the surface of the lower fixed plate (101) and comprises a pull rod (302), wherein the pull rod (302) extends when the electromagnet (301) is powered off and retracts when the electromagnet (301) is powered on; A locking pin (303) connected to the pull rod (302); A ring groove (204) is provided on the lower outer surface of the central shaft (201); when the electromagnet (301) is powered off, the locking pin (303) is pushed by the pull rod (302) to engage the ring groove (204), thereby locking the satellite launch box ejection device (100) in a locked state; and when the electromagnet (301) is powered on, the locking pin (303) is pulled out of the ring groove (204) by the pull rod (302), thereby switching the satellite launch box ejection device (100) to a released state.

4. The satellite launch box ejection device according to claim 1, in, The first shaft sleeve (202) is fixedly connected to the lower fixing plate (101) and the central shaft (201), the second shaft sleeve (203) is fixedly connected to the upper fixing plate (102), and the central shaft (201) is capable of sliding in the second shaft sleeve (203).

5. The satellite launch box ejection device according to claim 4, in, The locking release mechanism comprises: An electromagnet (301) is fixed on the surface of the upper fixed plate (102) and comprises a pull rod (302), wherein the pull rod (302) extends when the electromagnet (301) is powered off and retracts when the electromagnet (301) is powered on; A locking pin (303) connected to the pull rod (302); A ring groove (204) is provided on the upper outer surface of the central shaft (201); when the electromagnet (301) is powered off, the locking pin (303) is pushed by the pull rod (302) to engage the ring groove (204), thereby locking the satellite launch box ejection device (100) in a locked state; and when the electromagnet (301) is powered on, the locking pin (303) is pulled out of the ring groove (204) by the pull rod (302), thereby switching the satellite launch box ejection device (100) to a released state.

6. The satellite launch box ejection device according to claim 1, in, The first number is four.

7. The satellite launch box ejection device according to claim 1, in, The stretched length of the tension spring group in the locked state of the satellite launch box ejection device depends on the ejection stroke required by the satellite launch box ejection device, and / or the elastic modulus of the tension spring group depends on the ejection force required by the satellite launch box ejection device.

8. The satellite launch box ejection device according to any one of claims 1 to 7, in, There are a plurality of the first shaft sleeves (202), the second shaft sleeves (203), the first connecting rod group, the second connecting rod group, the pull ring (103) and the tension spring group, and they are repeatedly arranged along the central axis (201) between the upper fixed plate (102) and the lower fixed plate (101), and among the plurality of first shaft sleeves (202), only the first shaft sleeve (202) close to the lower fixed plate (101) is fixedly connected to the lower fixed plate (101), and among the plurality of second shaft sleeves (203), only the second shaft sleeve (203) close to the upper fixed plate (102) is fixedly connected to the upper fixed plate (102), and the remaining adjacent first shaft sleeves (202) and second shaft sleeves (203) are integrated or fixedly connected to each other.

Images