Multi-satellite chain launch lockup, unlock and ejection mechanism

Abstract

The application relates to a multi-satellite chain type launching locking and unlocking and ejecting mechanism and belongs to the technical field of spacecrafts. The mechanism comprises a guide rail support, a plurality of satellite assemblies are longitudinally arranged in the guide rail support, a plurality of auxiliary rods are slidably connected in the guide rail support, the plurality of auxiliary rods are respectively fixed to the side surfaces of the plurality of satellite assemblies, a plurality of supporting rods are arranged in the guide rail support, satellite ejecting devices for ejecting the auxiliary rods are arranged on the supporting rods, a plurality of satellite unlocking devices for locking and unlocking the supporting rods are arranged on the guide rail support, a sliding groove is horizontally arranged on the guide rail support, sliding blocks are fixedly connected to the two ends of the supporting rods, and a plurality of auxiliary devices for pushing the sliding blocks to move so that the auxiliary rods and the supporting rods are dislocated in the horizontal direction of the guide rail support are arranged in the guide rail support. The satellite ejecting devices can be left on the guide rail support, so that the safety of satellite flight is effectively improved.

Description

Technical Field

[0001] This application relates to the field of spacecraft technology, and in particular to a multi-satellite chain launch locking, unlocking, and ejection mechanism. Background Technology

[0002] With the rapid development of aerospace technology, my country is launching satellites at an increasingly higher frequency and in greater numbers. Satellite launches require locking, unlocking, and ejection mechanisms. Traditional locking, unlocking, and ejection mechanisms are typically only suitable for launching single satellites, not for chain ejection of multiple satellites.

[0003] In existing chain-launch systems for multiple satellites, a corresponding satellite launch mechanism is typically installed based on the number of satellites, and this mechanism needs to be mounted on the side of the satellite. However, mounting the satellite launch mechanism on both sides of the satellite results in poor stability and can easily affect the safety of the satellite's flight. Summary of the Invention

[0004] To effectively improve the safety of satellite flight, this application provides a multi-satellite chain launch locking, unlocking, and ejection mechanism.

[0005] The purpose of this application is to provide a multi-satellite chain launch locking, unlocking, and ejection mechanism, which adopts the following technical solution:

[0006] A multi-satellite chain launch locking, unlocking, and ejection mechanism includes a guide rail bracket for longitudinally arranging multiple satellite components. Multiple auxiliary rods are slidably connected within the guide rail bracket, each auxiliary rod being fixed to the side of one of the satellite components. Multiple support rods are provided within the guide rail bracket, each support rod equipped with a satellite ejection device for ejecting the auxiliary rods. Multiple satellite unlocking devices for locking and unlocking the auxiliary rods are provided on the guide rail bracket. A sliding groove is laterally formed on the guide rail bracket, and sliding blocks are fixedly connected to both ends of each support rod. Multiple auxiliary devices are provided within the guide rail bracket to push the sliding blocks, causing the auxiliary rods and support rods to be misaligned laterally within the guide rail bracket.

[0007] By adopting the above technical solution, when a satellite component needs to be launched, the auxiliary rod is unlocked using the satellite unlocking device. Under the action of the satellite ejection device, the support rod moves longitudinally along the guide rail support, thereby ejecting the satellite component and the support rod from the guide rail support. Then, the auxiliary device is used to move the used support rod and the satellite ejection device on the support rod laterally, so that the support rod and the satellite ejection device are misaligned with the auxiliary rod on the unlaunched satellite component, thereby avoiding the presence of the support rod and the satellite ejection device affecting the launch of other satellite components. This allows the satellite ejection device to remain on the guide rail support, effectively improving the safety of satellite flight.

[0008] Optionally, the satellite ejection device includes a first support rod, a second support rod, a third support rod, a fourth support rod, and a positioning rod. One end of the first and second support rods is hinged to a support rod, and one end of the third and fourth support rods is hinged to the positioning rod. The auxiliary rod has a positioning hole for insertion and engagement with the positioning rod. The other ends of the first and third support rods are hinged to each other, and the other ends of the second and fourth support rods are hinged to each other. A tension spring is provided between the hinge axis of the first and third support rods and the hinge axis of the second and fourth support rods.

[0009] By adopting the above technical solution, after the satellite unlocking device unlocks the support rod, the tension of the spring is used to push the auxiliary rod away from the support rod, thereby ejecting the corresponding satellite component; at the same time, the movement of the auxiliary rod will cause the positioning rod to separate from the positioning hole, thus facilitating the separation of the satellite component from the satellite ejection device.

[0010] Optionally, the support rod is provided with a telescopic rod, one end of which is fixedly connected to the support rod, and the other end of which is fixedly connected to the positioning rod.

[0011] By adopting the above technical solution, the telescopic rod can guide the movement of the positioning rod, thereby making the satellite ejection device more effective at ejecting satellite components.

[0012] Optionally, the satellite unlocking device includes a locking rod and a locking groove. A sliding hole is provided on the side of the guide rail bracket, and the locking rod is slidably connected in the sliding hole. The locking groove is provided on the side of the auxiliary rod, and the locking rod and the locking groove are inserted into each other.

[0013] By adopting the above technical solution, the sliding hole and locking rod work together to guide the movement of the locking rod; when the end of the locking rod is inserted into the locking groove, it is easy to lock the support rod on the guide rail bracket; when the end of the locking rod is separated from the locking groove, it is easy to unlock the support rod on the guide rail bracket, thus making the locking and unlocking effect of the support rod better.

[0014] Optionally, a cover plate is hinged to one end of the guide rail bracket, and a locking and unlocking device for locking and unlocking the cover plate is provided on the guide rail bracket. A linkage component is provided inside the guide rail bracket, and the linkage component is used to cause the corresponding locking rod to retract into the sliding hole when the cover plate is opened or the sliding block is misaligned.

[0015] By adopting the above technical solution, when the cover is opened under the action of the locking and unlocking device, the locking rod near the cover will retract into the sliding hole under the action of the linkage component, which facilitates the ejection of the first satellite component from the guide rail bracket; by using the movement of the sliding block, other locking rods will retract into the sliding hole under the action of the linkage component, which facilitates the ejection of other satellite components from the guide rail bracket.

[0016] Optionally, the linkage assembly includes a linkage hole and multiple linkage rods. The linkage hole is opened inside the guide rail bracket and communicates with the sliding groove. The linkage hole is set along the longitudinal direction of the guide rail bracket. The linkage rods are slidably connected inside the linkage hole. A linkage spring is sleeved on the linkage rod, and a locking spring is sleeved on the locking rod. The end face of the linkage rod is an inclined surface. The other end of the locking rod abuts against the inclined surface of the linkage rod. The other end of one linkage rod abuts against the cover plate, and the other ends of the remaining linkage rods abut against the sliding block.

[0017] By adopting the above technical solution, when the cover is opened, the linkage rod will move towards the cover under the action of the linkage spring. At the same time, the other end of the locking rod will slide along the inclined surface of the linkage rod under the action of the locking spring, so that the end of the locking rod can be retracted into the sliding hole, thereby unlocking the first satellite component. When the sliding block is misaligned with the connecting hole, the corresponding linkage rod will move towards the cover under the action of the linkage spring. At the same time, the other end of the locking rod will slide along the inclined surface of the linkage rod under the action of the locking spring, so that the end of the locking rod can be retracted into the sliding hole, thereby unlocking the other satellite components.

[0018] Optionally, the other end of the linkage is rotatably connected to a ball bearing.

[0019] By adopting the above technical solution, during the process of the sliding block moving along the sliding groove, the other end of the linkage rod will press against the surface of the sliding block to move. The rolling of the ball will reduce the resistance encountered by the sliding block when it moves, thereby making the unlocking effect of other satellite components better.

[0020] Optionally, the locking and unlocking device includes a power component, a plug-in post, and a plug-in hole. A locking seat is fixedly connected to the free end of the cover plate, and the plug-in hole is opened on the locking seat. The power component is fixed on the guide rail bracket to drive the plug-in post to move laterally, and the plug-in post is plugged into the plug-in hole. An unlocking torsion spring is sleeved on the hinge shaft of the cover plate. One end of the unlocking torsion spring is fixed to the cover plate, and the other end of the unlocking torsion spring is fixed to the guide rail bracket.

[0021] By adopting the above technical solution, the insertion post is moved by a power component, which facilitates the separation of the insertion post from the insertion hole. This allows the cover plate to open automatically under the action of the unlocking torsion spring, thereby allowing the satellite component to be ejected from the guide rail bracket.

[0022] Optionally, the auxiliary device includes an auxiliary groove and a push block. The auxiliary groove is formed on the side of the satellite component, and the push block is slidably connected in the auxiliary groove. The push block abuts against the side of the support rod. An auxiliary spring is provided in the auxiliary groove. One end of the auxiliary spring is fixedly connected to the bottom of the auxiliary groove, and the other end of the auxiliary spring is fixedly connected to the push block.

[0023] By adopting the above technical solution, when the positioning rod separates from the positioning hole, the auxiliary rod unlocks and restricts the support rod in the lateral direction of the guide rail bracket. The support rod and the satellite ejection device will move laterally under the action of the auxiliary spring, which has a simple structure.

[0024] In summary, this application includes at least the following beneficial technical effects:

[0025] 1. When a satellite component needs to be launched, the support rod is unlocked using the satellite unlocking device. Under the action of the satellite ejection device, the support rod moves longitudinally along the guide rail support, thereby ejecting the satellite component and the support rod from the guide rail support. Then, an auxiliary device is used to move the used support rod and the satellite ejection device on the support rod laterally, so that the support rod and the satellite ejection device are misaligned with the auxiliary rod on the unlaunched satellite component, thereby avoiding the presence of the support rod and the satellite ejection device affecting the launch of other satellite components. This allows the satellite ejection device to remain on the guide rail support, effectively improving the safety of satellite flight.

[0026] 2. The sliding hole and locking rod work together to guide the movement of the locking rod; when the end of the locking rod is inserted into the locking groove, it is easy to lock the support rod on the guide rail bracket; when the end of the locking rod is separated from the locking groove, it is easy to unlock the support rod on the guide rail bracket, thus making the locking and unlocking effect of the support rod better. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the structure of a multi-satellite chain launch locking, unlocking, and ejection mechanism in an embodiment of this application;

[0028] Figure 2 This is a partial structural cross-sectional view of an embodiment of this application, mainly used to show the connection diagram of the guide rail bracket, satellite unlocking device and linkage components;

[0029] Figure 3 yes Figure 2 Enlarged view of section A;

[0030] Figure 4 This is a partial connection diagram of an embodiment of this application, mainly used to illustrate the connection diagram between the support rod and the satellite ejection device;

[0031] Figure 5 This is a partial structural cross-sectional view of an embodiment of this application, mainly used to illustrate the connection between the support rod and the auxiliary device.

[0032] Explanation of reference numerals in the attached drawings: 1. Guide rail bracket; 2. Auxiliary rod; 3. Support rod; 4. Satellite ejection device; 41. First support rod; 42. Second support rod; 43. Third support rod; 44. Fourth support rod; 45. Positioning rod; 46. Tension spring; 5. Satellite unlocking device; 51. Locking rod; 52. Locking groove; 53. Sliding hole; 6. Sliding groove; 7. Sliding block; 8. Auxiliary device; 81. Auxiliary groove; 82. Push block; 83. Auxiliary spring; 9. Positioning hole; 10. Telescopic rod; 11. Cover plate; 12. Locking and unlocking device; 121. Power component; 122. Insertion post; 123. Insertion hole; 124. Unlocking torsion spring; 13. Linkage assembly; 131. Linkage hole; 132. Linkage rod; 133. Linkage spring; 134. Locking spring; 14. Ball bearing; 15. Locking seat. Detailed Implementation

[0033] To make the purpose, technical solution, and advantages of this application clearer, the following description is provided in conjunction with the appendix. Figure 1-5 The present application will be further described in detail below with reference to embodiments. It should be understood that the specific embodiments described herein are for illustrative purposes only and are not intended to limit the scope of the application.

[0034] This application discloses a multi-satellite chain launch locking, unlocking, and ejection mechanism. (Refer to...) Figure 1 and Figure 2 The mechanism includes a guide rail bracket 1, which houses multiple satellite components arranged longitudinally, with four satellite components in total; a cover plate 11 is hinged to the top of the guide rail bracket 1, and a locking and unlocking device 12 is installed on the guide rail bracket 1 for locking and unlocking the cover plate 11.

[0035] Reference Figure 1 and Figure 2The locking and unlocking device 12 includes a power component 121, a plug-in post 122, and a plug-in hole 123. A locking seat 15 is fixedly connected to the free end of the cover plate 11, and the plug-in hole 123 is formed on the locking seat 15. The power component 121 is fixed to the guide rail bracket 1 to drive the plug-in post 122 to move laterally, and the plug-in post 122 engages with the plug-in hole 123. An unlocking torsion spring 124 is sleeved on the hinge shaft of the cover plate 11, with one end fixed to the cover plate 11 and the other end fixed to the guide rail bracket 1. The power component 121 is a power cylinder, the outer shell of which is fixed to the side of the guide rail bracket 1, and the piston rod of the power cylinder is connected to the plug-in post 122 by a key. The insertion post 122 is moved by a power cylinder, which facilitates the separation of the insertion post 122 from the insertion hole 123. This allows the cover plate 11 to open automatically under the action of the unlocking torsion spring 124, which helps the satellite component to be ejected from the guide rail bracket 1.

[0036] Reference Figure 2 and Figure 3 Multiple auxiliary rods 2 are slidably connected inside the guide rail bracket 1, and the multiple auxiliary rods 2 are respectively fixed to the sides of multiple satellite components. Multiple support rods 3 are installed inside the guide rail bracket 1. Multiple satellite unlocking devices 5 for locking and unlocking the auxiliary rods 2 are provided on the guide rail bracket 1. The satellite unlocking device 5 includes a locking rod 51 and a locking groove 52. A sliding hole 53 is opened on the side of the guide rail bracket 1, and the locking rod 51 is slidably connected in the sliding hole 53. The locking groove 52 is opened on the side of the auxiliary rod 2, and the locking rod 51 and the locking groove 52 are inserted and engaged.

[0037] In this embodiment, the sliding hole 53 and the locking rod 51 cooperate to guide the movement of the locking rod 51; when the end of the locking rod 51 is inserted into the locking groove 52, it is easy to lock the support rod 3 on the guide rail bracket 1; when the end of the locking rod 51 is separated from the locking groove 52, it is easy to unlock the support rod 3 on the guide rail bracket 1, thereby making the locking and unlocking effect of the support rod 3 better.

[0038] Reference Figure 2 and Figure 3A linkage component 13 is provided inside the guide rail bracket 1. The linkage component 13 is used to retract the corresponding locking rod 51 into the sliding hole 53 when the cover plate 11 is opened or the sliding block 7 is misaligned. The linkage component 13 includes a linkage hole 131 and multiple linkage rods 132. The linkage hole 131 is opened inside the guide rail bracket 1 and is connected to the sliding groove 6. The linkage hole 131 is set along the longitudinal direction of the guide rail bracket 1. The linkage rods 132 are slidably connected to the linkage hole 131. A linkage spring 133 is sleeved on the linkage rod 132 and a locking spring 134 is sleeved on the locking rod 51. The end face of the linkage rod 132 is an inclined surface. The other end of the locking rod 51 abuts against the inclined surface of the linkage rod 132. The other end of one linkage rod 132 abuts against the cover plate 11, and the other ends of the remaining linkage rods 132 abut against the sliding block 7.

[0039] In this embodiment, when the cover plate 11 is opened, the linkage rod 132 will move toward the cover plate 11 under the action of the linkage spring 133. At the same time, the other end of the locking rod 51 will slide along the inclined surface of the linkage rod 132 under the action of the locking spring 134, so that the end of the locking rod 51 can be retracted into the sliding hole 53, thereby unlocking the first satellite component. When the sliding block 7 is misaligned with the connecting hole, the corresponding linkage rod 132 will move toward the cover plate 11 under the action of the linkage spring 133. At the same time, the other end of the locking rod 51 will slide along the inclined surface of the linkage rod 132 under the action of the locking spring 134, so that the end of the locking rod 51 can be retracted into the sliding hole 53, thereby unlocking the other satellite components.

[0040] Reference Figure 2 and Figure 3 The other end of the linkage rod 132 is connected to a ball bearing 14. As the sliding block 7 moves along the sliding groove 6, the other end of the linkage rod 132 will press against the surface of the sliding block 7 to move. The rolling of the ball bearing 14 will reduce the resistance encountered by the sliding block 7 when it moves, thereby making the unlocking effect of other satellite components better.

[0041] Reference Figure 2 and Figure 4A satellite ejection device 4 for ejecting the auxiliary rod 2 is installed on the support rod 3. The satellite ejection device 4 includes a first support rod 41, a second support rod 42, a third support rod 43, a fourth support rod 44, and a positioning rod 45. One end of the first support rod 41 and the second support rod 42 is hinged to the support rod 3, and one end of the third support rod 43 and the fourth support rod 44 is hinged to the positioning rod 45. The auxiliary rod 2 is provided with a positioning hole 9 that is inserted into the positioning rod 45. The other end of the first support rod 41 and the other end of the third support rod 43 are hinged to each other, and the other end of the second support rod 42 and the other end of the fourth support rod 44 are hinged to each other. A tension spring 46 is installed between the hinge axis of the first support rod 41 and the third support rod 43 and the hinge axis of the second support rod 42 and the fourth support rod 44.

[0042] In this embodiment, after the satellite unlocking device 5 unlocks the support rod 3, the tension of the tension spring 46 pushes the auxiliary rod 2 away from the support rod 3, thereby ejecting the corresponding satellite component. At the same time, the movement of the auxiliary rod 2 will cause the positioning rod 45 to separate from the positioning hole 9, thereby facilitating the separation of the satellite component from the satellite ejection device 4.

[0043] Reference Figure 2 and Figure 4 A telescopic rod 10 is installed on the support rod 3. One end of the telescopic rod 10 is fixedly connected to the support rod 3, and the other end is fixedly connected to the positioning rod 45. The telescopic rod 10 guides the movement of the positioning rod 45, thereby improving the ejection effect of the satellite ejection device 4 on the satellite components.

[0044] Reference Figure 2 and Figure 5 A sliding groove 6 is laterally provided on the guide rail bracket 1. Sliding blocks 7 are fixedly connected to both ends of the support rod 3. Multiple auxiliary devices 8 are installed inside the guide rail bracket 1 to move the sliding blocks 7 so that the auxiliary rod 2 and the support rod 3 are misaligned laterally in the guide rail bracket 1. The auxiliary device 8 includes an auxiliary groove 81 and a pushing block 82. The auxiliary groove 81 is opened on the side of the satellite component. The pushing block 82 is slidably connected in the auxiliary groove 81 and abuts against the side of the support block. An auxiliary spring 83 is installed in the auxiliary groove 81. One end of the auxiliary spring 83 is fixedly connected to the bottom of the auxiliary groove 81, and the other end of the auxiliary spring 83 is fixedly connected to the pushing block 82.

[0045] In this embodiment, when the positioning rod 45 separates from the positioning hole 9, the auxiliary rod 2 unlocks and restricts the support rod 3 in the lateral direction of the guide rail bracket 1. The support rod 3 and the satellite ejection device 4 will move laterally under the action of the auxiliary spring 83, which has a simple structure.

[0046] The implementation principle of a multi-satellite chain launch locking, unlocking, and ejection mechanism in this application embodiment is as follows: When a satellite component needs to be launched, the support rod 3 is unlocked using the satellite unlocking device 5. Under the action of the satellite ejection device 4, the support rod 3 moves longitudinally along the guide rail bracket 1, thereby ejecting the satellite component and the support rod 3 from the guide rail bracket 1. Then, the auxiliary device 8 is used to make the used support rod 3 and the satellite ejection device 4 on the support rod 3 move laterally, so that the support rod 3 and the satellite ejection device 4 are misaligned with the auxiliary rod 2 on the unlaunched satellite component, thereby avoiding the presence of the support rod 3 and the satellite ejection device 4 from affecting the launch of other satellite components. In this way, the satellite ejection device 4 can remain on the guide rail bracket 1, thereby effectively improving the safety of satellite flight.

[0047] The above are all preferred embodiments of this application and are not intended to limit the scope of protection of this application. Any feature disclosed in this specification (including the abstract and drawings) may be replaced by other equivalent or similar features unless specifically stated otherwise. Therefore, all equivalent changes made to the structure, shape, and principle of this application should be covered within the scope of protection of this application.

Claims

1. A multi-satellite chain launch locking, unlocking, and ejection mechanism, characterized in that, The system includes a guide rail bracket (1) for longitudinally arranging multiple satellite components; multiple auxiliary rods (2) are slidably connected inside the guide rail bracket (1), and the multiple auxiliary rods (2) are respectively fixed to the sides of the multiple satellite components; multiple support rods (3) are provided inside the guide rail bracket (1), and satellite ejection devices (4) for ejecting the auxiliary rods (2) are provided on the support rods (3); multiple satellite unlocking devices (5) for locking and unlocking the auxiliary rods (2) are provided on the guide rail bracket (1); a sliding groove (6) is opened laterally on the guide rail bracket (1); sliding blocks (7) are fixedly connected to both ends of the support rods (3); and multiple auxiliary devices (8) are provided inside the guide rail bracket (1) to push the sliding blocks (7) to move so that the auxiliary rods (2) and support rods (3) are misaligned laterally in the guide rail bracket (1). The satellite unlocking device (5) includes a locking rod (51) and a locking groove (52). A sliding hole (53) is provided on the side of the guide rail bracket (1), and the locking rod (51) is slidably connected in the sliding hole (53). The locking groove (52) is provided on the side of the auxiliary rod (2), and the locking rod (51) and the locking groove (52) are inserted into each other. One end of the guide rail bracket (1) is hinged to a cover plate (11). The guide rail bracket (1) is provided with a locking and unlocking device (12) for locking and unlocking the cover plate (11). The guide rail bracket (1) is provided with a linkage component (13). The linkage component (13) is used to make the corresponding locking rod (51) retract into the sliding hole (53) when the cover plate (11) is opened or the sliding block (7) is misaligned.

2. The multi-satellite chain launch locking, unlocking, and ejection mechanism according to claim 1, characterized in that, The satellite ejection device (4) includes a first support rod (41), a second support rod (42), a third support rod (43), a fourth support rod (44), and a positioning rod (45). One end of the first support rod (41) and the second support rod (42) is hinged to the support rod (3), and one end of the third support rod (43) and the fourth support rod (44) is hinged to the positioning rod (45). The auxiliary rod (2) has a positioning hole (9) that is inserted into the positioning rod (45). The other end of the first support rod (41) and the other end of the third support rod (43) are hinged to each other, and the other end of the second support rod (42) and the other end of the fourth support rod (44) are hinged to each other. A tension spring (46) is provided between the hinge axis of the first support rod (41) and the third support rod (43) and the hinge axis of the second support rod (42) and the fourth support rod (44).

3. The multi-satellite chain launch locking, unlocking, and ejection mechanism according to claim 2, characterized in that, A telescopic rod (10) is provided on the support rod (3). One end of the telescopic rod (10) is fixedly connected to the support rod (3), and the other end of the telescopic rod (10) is fixedly connected to the positioning rod (45).

4. The multi-satellite chain launch locking, unlocking, and ejection mechanism according to claim 1, characterized in that, The linkage assembly (13) includes a linkage hole (131) and multiple linkage rods (132). The linkage hole (131) is opened in the guide rail bracket (1) and is connected to the sliding groove (6). The linkage hole (131) is set along the longitudinal direction of the guide rail bracket (1). The linkage rods (132) are slidably connected in the linkage hole (131). A linkage spring (133) is sleeved on the linkage rod (132), and a locking spring (134) is sleeved on the locking rod (51). The end face of the linkage rod (132) is an inclined surface. The other end of the locking rod (51) abuts against the inclined surface of the linkage rod (132). The other end of one linkage rod (132) abuts against the cover plate (11), and the other ends of the remaining linkage rods (132) abut against the sliding block (7).

5. A multi-satellite chain launch locking, unlocking, and ejection mechanism according to claim 4, characterized in that, The other end of the linkage rod (132) is rotatably connected to a ball bearing (14).

6. The multi-satellite chain launch locking, unlocking, and ejection mechanism according to claim 1, characterized in that, The locking and unlocking device (12) includes a power component (121), a plug-in post (122), and a plug-in hole (123). The free end of the cover plate (11) is fixedly connected to a locking seat (15), and the plug-in hole (123) is opened on the locking seat (15). The power component (121) is fixed on the guide rail bracket (1) to drive the plug-in post (122) to move laterally. The plug-in post (122) is plugged into the plug-in hole (123). An unlocking torsion spring (124) is sleeved on the hinge shaft of the cover plate (11). One end of the unlocking torsion spring (124) is fixed on the cover plate (11), and the other end of the unlocking torsion spring (124) is fixed on the guide rail bracket (1).

7. The multi-satellite chain launch locking, unlocking, and ejection mechanism according to claim 1, characterized in that, The auxiliary device (8) includes an auxiliary groove (81) and a push block (82). The auxiliary groove (81) is opened on the side of the satellite component. The push block (82) is slidably connected in the auxiliary groove (81). The push block (82) abuts against the side of the support rod (3). An auxiliary spring (83) is provided in the auxiliary groove (81). One end of the auxiliary spring (83) is fixedly connected to the bottom of the auxiliary groove (81), and the other end of the auxiliary spring (83) is fixedly connected to the push block (82).

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