Spacecraft-rocket separation device

Abstract

The application provides a satellite-rocket separation device, which comprises a rocket end connecting structure, one end surface of which is used for connecting with a rocket; a satellite end connecting structure, one end surface of which is used for connecting with a satellite, and the other end surface is abutted with the other end surface of the rocket end connecting structure, and the satellite end connecting structure has a connecting part; a driving assembly arranged on the rocket end connecting structure; and a clamping assembly comprising a locking shaft and a plurality of clamping pieces, wherein the locking shaft is detachably connected with the driving assembly, the plurality of clamping pieces are swingably arranged on the locking shaft, the clamping pieces have relatively arranged clamping positions and avoiding positions, when the plurality of clamping pieces are located at the clamping positions, the plurality of clamping pieces cooperate with the clamping connecting part, when the clamping pieces are located at the avoiding positions, the clamping pieces are away from the connecting part, and the driving assembly can drive the clamping pieces to swing between the clamping positions and the avoiding positions. Through the technical scheme provided in the application, the problem of poor adaptability of the satellite-rocket separation device in the prior art can be solved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of satellite-rocket separation device, in particular to a satellite-rocket separation device. BACKGROUND

[0002] At present, the satellite-rocket separation device is a device for reliably connecting a satellite and a rocket and releasing the satellite after the satellite-rocket enters an orbit, and plays an important role in satellite launching.

[0003] The existing micro-satellite separation generally adopts a pyrotechnic separation device such as an explosive bolt or a separation nut or a memory alloy unlocking separation device. The pyrotechnic separation device has the problems of undetectable separation performance, high separation impact, pollution and safety, and the memory alloy unlocking separation device has the problems of high requirement for environmental temperature and increased unlocking time at low temperature. SUMMARY

[0004] The present application provides a satellite-rocket separation device to solve the problem of poor adaptability of the satellite-rocket separation device in the prior art.

[0005] The present application provides a satellite-rocket separation device, which comprises: a rocket end connecting structure, one end face of the rocket end connecting structure being used for connecting with a rocket; a satellite end connecting structure, one end face of the satellite end connecting structure being used for connecting with a satellite, the other end face of the satellite end connecting structure abutting against the other end face of the rocket end connecting structure, the satellite end connecting structure having a connecting part; a driving assembly, which is arranged on the rocket end connecting structure; and a clamping assembly, which comprises a locking shaft and a plurality of clamping pieces, the locking shaft being detachably connected with the driving assembly, the plurality of clamping pieces being swingably arranged on the locking shaft, the plurality of clamping pieces being distributed at intervals in the circumferential direction of the locking shaft, each clamping piece having oppositely arranged clamping and avoiding positions, the plurality of clamping pieces clamping the connecting part when the plurality of clamping pieces are located at the clamping positions, and each clamping piece being away from the connecting part when the clamping piece is located at the avoiding position, the driving assembly being capable of driving the clamping pieces to swing between the clamping and avoiding positions.

[0006] Further, the clamping piece and the locking shaft have a first reset piece therebetween, the first reset piece being capable of driving the clamping piece to swing from the clamping position to the avoiding position.

[0007] Further, the satellite-rocket separation device further comprises a separation assembly, which is arranged between the rocket end connecting structure and the satellite end connecting structure and is fixed on the rocket end connecting structure, the separation assembly driving the satellite end connecting structure to separate from the rocket end connecting structure when the plurality of clamping pieces are located at the avoiding positions.

[0008] Further, the driving assembly comprises a fixed shell fixed on the rocket end connecting structure, the fixed shell having a through hole and a receiving cavity in communication with each other, and the locking shaft being fixedly connected with the fixed shell; a driving structure fixed on the fixed shell; a connecting pipe slidably arranged in the receiving cavity and sleeved on the locking shaft, the driving structure being drivingly connected with the connecting pipe through the through hole, the connecting pipe being located on the side of the clamping pieces away from the connecting part, the connecting pipe having a driving end located between the clamping pieces and the locking shaft, and the driving structure driving the plurality of clamping pieces to swing synchronously between the clamping position and the avoiding position through the connecting pipe.

[0009] Further, the clamping pieces are hingedly connected with the locking shaft, the clamping pieces having oppositely arranged connecting ends and clamping ends, the connecting ends being arranged close to the connecting pipe relative to the clamping ends, the clamping ends being capable of clamping the connecting part, the connecting ends being gradually arranged away from the locking shaft in the direction close to the connecting pipe, and the cross-sectional area of the driving end being gradually reduced in the direction close to the clamping pieces.

[0010] Further, one end of the clamping piece close to the connecting part has a bending section, the connecting part comprising a first connecting section fixed on the satellite end connecting structure and a second connecting section located on one end of the first connecting section close to the rocket end connecting structure, the second connecting section having a diameter greater than that of the first connecting section, and the first connecting section and the second connecting section having a stepped surface therebetween, the bending section being in abutment with the stepped surface when the clamping pieces are located at the clamping position.

[0011] Further, the second connecting section is provided with a groove, the cross-sectional area of the groove being gradually increased in the direction close to the locking shaft, one end of the locking shaft close to the second connecting section has a fixing section, the fixing section being located in the groove, the cross-sectional area of the fixing section being gradually reduced in the direction close to the second connecting section, and the fixing section being structurally matched with the groove.

[0012] Further, the connecting pipe and the locking shaft have an elastic member therebetween to limit the displacement of the connecting pipe.

[0013] Further, the opening of the fixed shell is provided with a fixing structure, the side wall of the locking shaft is provided with a connecting lug, and the side wall of the connecting pipe is provided with a slot, the connecting lug being slidably arranged in the slot, and the connecting lug being detachably connected with the fixing structure through the slot.

[0014] Further, the separating assembly comprises a cover body detachably arranged on the rocket end connecting structure, and a second reset member, one end of the second reset member being connected with the cover body, the other end of the second reset member being in abutment with the satellite end connecting structure, and the second reset member being capable of driving the satellite end connecting structure away from the rocket end connecting structure.

[0015] Further, the satellite-rocket separation device further comprises a travel switch arranged on the rocket end connecting structure and used for detecting the relative position between the rocket end connecting structure and the satellite end connecting structure.

[0016] The rocket end connecting structure is connected with a rocket, the satellite end connecting structure is connected with a satellite, and the rocket end connecting structure and the satellite end connecting structure abut against each other, the clamping piece is fixed on the rocket end connecting structure through the locking shaft and the driving assembly, the clamping piece has the clamping position and the avoiding position arranged oppositely, that is, the clamping assembly can clamp the connecting part of the satellite end connecting structure, so that the rocket end connecting structure and the satellite end connecting structure are fixedly connected, when the clamping piece is in the avoiding position, the clamping piece is away from the connecting part, so that the rocket end connecting structure and the satellite end connecting structure are separated, and the driving assembly can drive the clamping piece to swing between the clamping position and the avoiding position. In this way, through cooperation of the driving assembly and the clamping assembly, accurate control of the rocket end connecting structure and the satellite end connecting structure can be realized, safe unlocking and separation within a predetermined time are ensured, the separation time of the rocket end connecting structure and the satellite end connecting structure is short, uncontrollability and risks possibly caused by the initiating explosive are avoided, meanwhile, pollution can be avoided, and meanwhile, the above structure is adopted, the satellite-rocket separation device is not limited by temperature, and is good in temperature adaptability. Due to the swing design of the clamping piece, a gentle separation process can be realized, high impact force caused by sudden release or explosive separation is avoided, and then the structural integrity and functions of the satellite can be ensured. Therefore, the satellite-rocket separation device has the performances of micro-impact, no pollution, low impact and high safety, and adaptability of the satellite-rocket separation device is improved. BRIEF DESCRIPTION OF DRAWINGS

[0017] The drawings constituting a part of the specification show the present application and are used to provide further understanding of the present application, and their explanation serves to explain the present application, and does not constitute an improper limitation on the present application. In the drawings:

[0018] Figure 1 A structure schematic view of a satellite-rocket separation device provided according to an embodiment of the present application is shown;

[0019] Figure 2 A structure schematic view of a satellite-rocket separation device when a clamping piece is in an avoiding position is shown according to an embodiment of the present application;

[0020] Figure 3 A structure schematic view of a satellite-rocket separation device when a clamping piece is in a clamping position is shown according to an embodiment of the present application;

[0021] Figure 4 A sectional view of a satellite-rocket separation device provided according to an embodiment of the present application is shown;

[0022] Figure 5 A structure schematic view of a rocket end connecting structure provided according to an embodiment of the present application is shown;

[0023] Figure 6A structural schematic diagram of the fixed shell provided by the embodiment of the present application is shown;

[0024] Figure 7 A structural schematic diagram of the locking shaft provided by the embodiment of the present application is shown;

[0025] Figure 8 A structural schematic diagram of the separation assembly provided by the embodiment of the present application is shown.

[0026] Among them, the above-mentioned drawings include the following reference signs:

[0027] 10, rocket end connecting structure;

[0028] 20, satellite end connecting structure;

[0029] 21, connecting part;

[0030] 211, first connecting section;

[0031] 212, second connecting section; 2121, groove;

[0032] 30, driving assembly;

[0033] 31, fixed shell; 311, through hole; 312, accommodating cavity; 313, fixed structure;

[0034] 32, driving structure;

[0035] 33, connecting pipe; 331, driving end;

[0036] 40, clamping assembly;

[0037] 41, locking shaft; 411, fixed section; 412, connecting lug; 413, fixed lug;

[0038] 42, clamping piece; 421, connecting end; 422, clamping end; 423, bending section;

[0039] 43, first reset piece;

[0040] 50, separation assembly;

[0041] 51, cover; 52, second reset piece; 53, guide shaft;

[0042] 60, elastic piece;

[0043] 70, travel switch. DETAILED DESCRIPTION

[0044] Clearly, the described embodiments are only a part of all the embodiments of the present application, rather than all the embodiments. The description of the at least one example embodiment is actually only illustrative, and is by no means any limitation on the present application and its application or use. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative labor fall within the scope of the present application.

[0045] As shown in Figures 1 to 5 The present application provides a satellite-rocket separation device, which comprises a rocket end connecting structure 10, a satellite end connecting structure 20, a driving assembly 30 and a clamping assembly 40. One end surface of the rocket end connecting structure 10 is used for connecting with a rocket. One end surface of the satellite end connecting structure 20 is used for connecting with a satellite, and the other end surface of the satellite end connecting structure 20 abuts against the other end surface of the rocket end connecting structure 10. The satellite end connecting structure 20 has a connecting part 21. The driving assembly 30 is arranged on the rocket end connecting structure 10. The clamping assembly 40 comprises a locking shaft 41 and a plurality of clamping pieces 42. The locking shaft 41 is detachably connected with the driving assembly 30. The plurality of clamping pieces 42 are swingably arranged on the locking shaft 41. The plurality of clamping pieces 42 are distributed at intervals along the circumference of the locking shaft 41. The clamping piece 42 has oppositely arranged clamping positions and avoiding positions. When the plurality of clamping pieces 42 are located at the clamping positions, the plurality of clamping pieces 42 clamp the connecting part 21. When the clamping piece 42 is located at the avoiding position, the clamping piece 42 is away from the connecting part 21. The driving assembly 30 can drive the clamping piece 42 to swing between the clamping position and the avoiding position.

[0046] The rocket end connecting structure 10 is connected with a rocket, the satellite end connecting structure 20 is connected with a satellite, the rocket end connecting structure 10 abuts against the satellite end connecting structure 20, the clamping piece 42 is fixed on the rocket end connecting structure 10 through the locking shaft 41 and the driving assembly 30, the clamping piece 42 has a clamping position and a avoiding position arranged oppositely, that is, the clamping assembly 40 can clamp the connecting part 21 of the satellite end connecting structure 20, so that the rocket end connecting structure 10 and the satellite end connecting structure 20 are fixedly connected, when the clamping piece 42 is in the avoiding position, the clamping piece 42 is away from the connecting part 21, so that the rocket end connecting structure 10 and the satellite end connecting structure 20 are separated, and the driving assembly 30 can drive the clamping piece 42 to swing between the clamping position and the avoiding position. In this way, through cooperation of the driving assembly 30 and the clamping assembly 40, accurate control of the rocket end connecting structure 10 and the satellite end connecting structure 20 can be realized, safe unlocking and separation within a predetermined time are ensured, the separation time of the rocket end connecting structure 10 and the satellite end connecting structure 20 is short, uncontrollability and risks possibly caused by a pyrotechnic device are avoided, pollution is also avoided, and meanwhile, the above structure is adopted, so that the satellite-rocket separation device is not limited by temperature and has good temperature adaptability. Due to the swing design of the clamping piece 42, a gentle separation process can be realized, high impact force caused by sudden release or explosive separation is avoided, and then the structural integrity and functions of the satellite can be ensured. Therefore, the satellite-rocket separation device has the performances of micro-impact, no pollution, low impact and high safety, and adaptability of the satellite-rocket separation device is improved.

[0047] In addition, in the application, through work of the driving assembly 30, repeated locking and unlocking separation tests can be realized, and reliability and effectiveness of separation of the rocket end connecting structure 10 and the satellite end connecting structure 20 are ensured.

[0048] Specifically, in the application, the rocket end connecting structure 10 and the satellite end connecting structure 20 are made of aluminum material and adopt a lightweight structure stiffness design, the rocket end connecting structure 10 and the satellite end connecting structure 20 are flange structures, and the outer edges of the flange structures adopt a lace structure form.

[0049] As shown in Figure 2 and Figure 3 , the clamping piece 42 and the locking shaft 41 have a first reset piece 43 therebetween, the first reset piece 43 can drive the clamping piece 42 to swing from the clamping position to the avoiding position. In the application, the driving assembly 30 can drive the clamping piece 42 to swing from the avoiding position to the clamping position, and the first reset piece 43 can drive the clamping piece 42 to swing from the clamping position to the avoiding position. In this way, the first reset piece 43 can automatically drive the clamping piece 42 to swing, without additional operation or power source, the swing process of the clamping piece 42 is simplified, and the response speed of the clamping piece 42 is improved.

[0050] The first reset member 43 is a spring.

[0051] As shown in Figure 1 , Figure 4 and Figure 8 , the satellite-rocket separation device further comprises a separation assembly 50, which is arranged between the rocket end connecting structure 10 and the satellite end connecting structure 20 and is fixed on the rocket end connecting structure 10. When the plurality of clamping members 42 are in the avoiding position, the separation assembly 50 drives the satellite end connecting structure 20 to separate from the rocket end connecting structure 10. In this way, the separation assembly 50 can improve the separation speed of the satellite end connecting structure 20 from the rocket end connecting structure 10, facilitate the separation of the satellite end connecting structure 20 from the rocket end connecting structure 10, and thus facilitate the subsequent work to proceed normally.

[0052] As shown in Figure 2 and Figure 3 , the driving assembly 30 comprises a fixed shell 31, a driving structure 32 and a connecting pipe 33.

[0053] The fixed shell 31 is fixed on the rocket end connecting structure 10. The fixed shell 31 has a through hole 311 and a receiving cavity 312 in communication with each other, and the locking shaft 41 is fixedly connected with the fixed shell 31. The driving structure 32 is fixed on the fixed shell 31. In this way, the locking shaft 41 and the driving structure 32 can be fixed, and the compactness of the cooperation between the driving assembly 30 and the clamping assembly 40 is improved, and the overall volume of the driving assembly 30 and the clamping assembly 40 is reduced.

[0054] The connecting pipe 33 is slidably arranged in the receiving cavity 312, and the connecting pipe 33 is sleeved on the locking shaft 41. The driving structure 32 is drivingly connected with the connecting pipe 33 through the through hole 311. The connecting pipe 33 is located on the side of the clamping member 42 away from the connecting part 21. The connecting pipe 33 has a driving end 331 located between the clamping member 42 and the locking shaft 41. The driving structure 32 drives the plurality of clamping members 42 to swing synchronously between the clamping position and the avoiding position through the connecting pipe 33. When the driving structure 32 drives the connecting pipe 33 to move towards the clamping member 42, the clamping member 42 swings from the avoiding position to the clamping position. When the driving structure 32 drives the connecting pipe 33 to move away from the clamping member 42, the first reset member 43 drives the clamping member 42 to swing from the clamping position to the avoiding position.

[0055] In this way, through the linkage mechanism of the connecting pipe 33 and the plurality of clamping members 42, the driving structure 32 can accurately and synchronously control all the clamping members 42 to swing between the clamping position and the avoiding position, ensuring the consistency and controllability of the unlocking and separation of the satellite end connecting structure 20, thereby improving the accuracy and reliability of the separation process.

[0056] And the design of the connecting pipe 33 and the fixed shell 31 simplifies the internal structure of the driving assembly 30, avoids the complex and failure-prone multi-point driving design, reduces the maintenance cost and potential failure rate, and reduces the overall weight and volume of the satellite-rocket separation device, while reducing the processing cost of the satellite-rocket separation device.

[0057] Specifically, in the present application, the driving structure 32 is an actuator, and different types of actuators can be used to adapt to different magnitudes of microsatellites.

[0058] And the actuator is electrically unlocked, which reduces the satellite-rocket separation impact and improves testability. At the same time, the motor of the actuator works for a short time, and the unlocking time is less than that of other existing separation products.

[0059] The clamping piece 42 is hingedly connected to the locking shaft 41. In this way, the clamping piece 42 is facilitated to swing relative to the locking shaft 41.

[0060] The clamping piece 42 has oppositely arranged connecting end 421 and clamping end 422, the connecting end 421 is arranged close to the connecting pipe 33 relative to the clamping end 422, the clamping end 422 can clamp the connecting part 21, the connecting end 421 is gradually arranged away from the locking shaft 41 along the direction close to the connecting pipe 33, and the cross-sectional area of the driving end 331 gradually decreases along the direction close to the clamping piece 42.

[0061] With the above structure, the driving end 331 is facilitated to be inserted between the connecting end 421 and the locking shaft 41, and the reliability of the connecting pipe 33 driving the clamping piece 42 to swing is ensured.

[0062] As shown in Figure 3 The end of the clamping piece 42 close to the connecting part 21 has a bending section 423. The connecting part 21 includes a first connecting section 211 and a second connecting section 212. The first connecting section 211 is fixed on the satellite end connecting structure 20. The second connecting section 212 is located at one end of the first connecting section 211 close to the rocket end connecting structure 10, the diameter of the second connecting section 212 is greater than that of the first connecting section 211, and there is a stepped surface between the first connecting section 211 and the second connecting section 212. When the clamping piece 42 is in the clamping position, the bending section 423 abuts against the stepped surface.

[0063] In this way, the abutment of the bending section 423 and the stepped surface forms a stable locking point, ensuring the firm connection between the satellite end connecting structure 20 and the rocket end connecting structure 10 during launch, and avoiding accidental unlocking due to vibration or external force. And the stepped surface serves as a reference point for unlocking of the clamping piece 42, ensuring the accuracy and consistency of the clamping piece 42 in the unlocking position, and avoiding separation impact or operation failure due to inaccurate unlocking position.

[0064] As shown in Figure 3 andFigure 7 As shown, the second connecting section 212 is provided with a groove 2121, the cross-sectional area of the groove 2121 gradually increases along the direction close to the locking shaft 41, the locking shaft 41 close to one end of the second connecting section 212 has a fixed section 411, the fixed section 411 is located in the groove 2121, the cross-sectional area of the fixed section 411 gradually decreases along the direction close to the second connecting section 212, and the fixed section 411 is matched with the structure of the groove 2121.

[0065] In this way, during the unlocking process, the locking shaft 41 can be smoothly moved along the guide of the groove 2121, the friction and resistance in the movement are reduced, the smoothness and accuracy of the unlocking action are ensured, and thus the impact force of the satellite-rocket separation device during unlocking is reduced. Moreover, the fixed section 411 is matched with the structure of the groove 2121, a self-locking mechanism is formed, the locking shaft 41 can remain stable even if severe vibration and impact are encountered during satellite launching, accidental unlocking is prevented, and the reliability and safety of the connection are improved.

[0066] Further, the elastic member 60 is arranged between the connecting pipe 33 and the locking shaft 41 to limit the displacement of the connecting pipe 33. In this way, the stability of the connecting pipe 33 during the up-and-down movement can be ensured, and the impact between the connecting pipe 33 and the locking shaft 41 can be avoided.

[0067] Specifically, the elastic member 60 is a spring.

[0068] As shown in Figure 6 and Figure 7 , the opening of the fixed shell 31 is provided with a fixed structure 313, the side wall of the locking shaft 41 is provided with a connecting lug 412, and the side wall of the connecting pipe 33 is provided with a slot, the connecting lug 412 is slidably arranged in the slot, and the connecting lug 412 is detachably connected with the fixed structure 313 through the slot.

[0069] In this way, the fixed structure 313 at the opening of the fixed shell 31 cooperates with the connecting lug 412 on the side wall of the locking shaft 41, and the connecting lug 412 is slidably arranged in the slot, which ensures the accurate alignment and stability of the connecting pipe 33 during the sliding process, avoids the shaking or deviation during the sliding process, and thus improves the reliability of the driving assembly 30 and the stability of the satellite-rocket separation. At the same time, by using the above structure, the locking shaft 41 can be easily fixed, and the difficulty of fixing the locking shaft 41 is reduced.

[0070] Specifically, in the present application, four fixed structures 313 are arranged at the opening of the fixed shell 31, and four connecting lugs 412 are arranged on the side wall of the locking shaft 41, and the four fixed structures 313 and the four connecting lugs 412 are arranged one by one.

[0071] In the present application, four groups of fixing ears 413 are arranged on the side wall of the locking shaft 41, and the four groups of fixing ears 413 are arranged at intervals along the circumference of the locking shaft 41, and each group of fixing ears 413 has two fixing ears 413, and each group of fixing ears 413 is detachably connected with a clamping piece 42.

[0072] Further, the separation assembly 50 comprises a cover 51 and a second reset member 52. The cover 51 is detachably arranged on the rocket end connecting structure 10. One end of the second reset member 52 is connected with the cover 51, and the other end of the second reset member 52 is in abutment with the satellite end connecting structure 20, and the second reset member 52 can drive the satellite end connecting structure 20 to move away from the rocket end connecting structure 10.

[0073] In this way, the arrangement of the second reset member 52 can ensure that after unlocking, the satellite end connecting structure 20 can smoothly move away from the rocket end connecting structure 10 according to a predetermined motion trajectory and speed, which helps to control the impact force during separation and protect the satellite from damage. Moreover, the second reset member 52 can quickly start and push the satellite end connecting structure 20, thereby significantly improving the efficiency of the satellite-rocket separation and ensuring that the satellite is accurately separated at a predetermined time and position.

[0074] Specifically, the second reset member 52 is a spring.

[0075] In this way, the second reset member 52 can be guided to avoid deviation of the second reset member 52 during operation, further improving the accuracy of the satellite-rocket separation.

[0076] As shown in Figure 1 The satellite-rocket separation device further comprises a travel switch 70 arranged on the rocket end connecting structure 10, which is used to detect the relative position between the rocket end connecting structure 10 and the satellite end connecting structure 20. In this way, the travel switch 70 can detect the relative position between the rocket end connecting structure 10 and the satellite end connecting structure 20 in real time, which is convenient for the staff to monitor in real time, thereby facilitating the staff to carry out subsequent work.

[0077] It should be noted that the terms used herein are only for the purpose of describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, the singular form is intended to include the plural form, unless the context clearly indicates otherwise, and it should be understood that when the terms "comprise" and / or "include" are used in the specification, there is a presence of the features, steps, operations, devices, components and / or combinations thereof.

[0078] The foregoing is considered as illustrative only of the principles of the application. Further, since numerous modifications and changes will readily occur to those skilled in the art, it is not desired to limit the application to the exact construction and practice described. Accordingly, all such variations are intended to be included within the scope of the present application as defined in the following claims, along with full equivalents thereof.

[0079] In the description of the present application, it is to be understood that the orientation or positional relationships indicated by terms such as "front", "back", "up", "down", "left", "right", "lateral", "vertical", "horizontal", "top", "bottom", and the like are generally based on the orientation or positional relationships shown in the drawings, and are merely intended to facilitate the description of the present application and simplify the description, and do not indicate or imply that the device or element must have a particular orientation or be constructed and operated in a particular orientation, and therefore should not be construed as limiting the scope of protection of the present application. The orientation terms "inner", "outer" refer to the inner and outer relative to the contour of the components themselves.

[0080] For the convenience of description, spatial relative terms such as "above", "upper", "top", "up", and the like can be used herein to describe the spatial relationship of one device or feature to another device or feature as shown in the drawings. It should be understood that the spatial relative terms are intended to include different orientations of the device in use or operation in addition to the orientation of the device described in the drawings. For example, if the device in the drawings is inverted, the device described as "above" or "on" the other device or structure will be positioned "below" or "under" the other device or structure. Thus, the exemplary term "above" can include both the "above" and "below" orientations. The device can also be positioned in other different ways (rotated 90 degrees or in other orientations) and the spatial relative descriptions used herein will be interpreted accordingly.

[0081] In addition, it should be noted that the use of the terms "first", "second", and the like do not have a special meaning, and are merely used to distinguish the corresponding components, and therefore should not be construed as limiting the scope of protection of the present application.

[0082] The above merely provides the preferred embodiments of the present application, and is not used to limit the present application. For those skilled in the art, the present application can have various modifications and changes. Any modifications, equivalent replacements, improvements, etc. made within the principles and technical scope of the present application shall fall into the scope of the present application.

Claims

1. A star-rocket separation device, characterized in that, The star-rocket separation device includes: A rocket end connection structure (10), one end face of which is used to connect to the rocket; A satellite-end connection structure (20) is provided, one end face of which is used to connect with a satellite, and the other end face of which abuts against the other end face of the rocket-end connection structure (10). The satellite-end connection structure (20) has a connecting part (21). A drive assembly (30) is disposed on the rocket end connection structure (10); A clamping assembly (40) includes a locking shaft (41) and a plurality of clamping members (42). The locking shaft (41) is detachably connected to the drive assembly (30). The plurality of clamping members (42) are oscillatingly disposed on the locking shaft (41). The plurality of clamping members (42) are circumferentially spaced along the locking shaft (41). The clamping members (42) have a clamping position and a clearance position that are relatively disposed. When the plurality of clamping members (42) are in the clamping position, the plurality of clamping members (42) cooperate to clamp the connecting part (21). When the clamping members (42) are in the clearance position, the clamping members (42) move away from the connecting part (21). The drive assembly (30) can drive the clamping members (42) to swing between the clamping position and the clearance position. The clamping member (42) and the locking shaft (41) have a first reset member (43), which can drive the clamping member (42) to swing from the clamping position to the avoidance position; The driving component (30) includes: A fixed shell (31) is fixed on the rocket end connection structure (10). The fixed shell (31) has a through hole (311) and a receiving cavity (312) that are in relative communication. The locking shaft (41) is fixedly connected to the fixed shell (31). The drive structure (32) is fixed to the fixed shell (31); A connecting tube (33) is slidably disposed in the receiving cavity (312) and the connecting tube (33) is sleeved on the locking shaft (41). The driving structure (32) is driven to connect with the connecting tube (33) through the through hole (311). The connecting tube (33) is located on the side of the clamping member (42) away from the connecting part (21). The connecting tube (33) has a driving end (331). The driving end (331) is located between the clamping member (42) and the locking shaft (41). The driving structure (32) drives multiple clamping members (42) to swing synchronously between the clamping position and the avoidance position through the connecting tube (33). The clamping member (42) is hinged to the locking shaft (41). The clamping member (42) has a connecting end (421) and a clamping end (422) arranged opposite to each other. The connecting end (421) is arranged close to the connecting tube (33) relative to the clamping end (422). The clamping end (422) can clamp the connecting part (21). The connecting end (421) is arranged gradually away from the locking shaft (41) in the direction close to the connecting tube (33). The cross-sectional area of ​​the driving end (331) gradually decreases in the direction close to the clamping member (42). When the driving structure (32) drives the connecting pipe (33) to move closer to the clamping member (42), the clamping member (42) swings from the avoidance position to the clamping position. When the driving structure (32) drives the connecting pipe (33) to move away from the clamping member (42), the first reset member (43) drives the clamping member (42) to swing from the clamping position to the avoidance position.

2. The star-rocket separation device according to claim 1, characterized in that, The satellite-rocket separation device further includes a separation component (50), which is disposed between the rocket end connection structure (10) and the satellite end connection structure (20), and the separation component (50) is fixed on the rocket end connection structure (10). When the plurality of clamping members (42) are in the avoidance position, the separation component (50) drives the satellite end connection structure (20) to separate from the rocket end connection structure (10).

3. The star-rocket separation device according to claim 1, characterized in that, The clamping member (42) has a bent section (423) at one end near the connecting portion (21), the connecting portion (21) comprising: The first connecting segment (211) is fixed on the satellite end connecting structure (20); The second connecting segment (212) is located at the end of the first connecting segment (211) near the rocket end connecting structure (10). The diameter of the second connecting segment (212) is larger than the diameter of the first connecting segment (211). There is a stepped surface between the first connecting segment (211) and the second connecting segment (212). When the clamping member (42) is in the clamping position, the bent segment (423) abuts against the stepped surface.

4. The star-rocket separation device according to claim 3, characterized in that, The second connecting segment (212) is provided with a groove (2121). The cross-sectional area of ​​the groove (2121) gradually increases along the direction close to the locking shaft (41). The locking shaft (41) has a fixing segment (411) at one end close to the second connecting segment (212). The fixing segment (411) is located in the groove (2121). The cross-sectional area of ​​the fixing segment (411) gradually decreases along the direction close to the second connecting segment (212). The structure of the fixing segment (411) is adapted to the groove (2121).

5. The star-rocket separation device according to claim 1, characterized in that, An elastic element (60) is provided between the connecting tube (33) and the locking shaft (41) to limit the displacement of the connecting tube (33).

6. The star-rocket separation device according to claim 1, characterized in that, The fixed shell (31) has a fixed structure (313) at its opening, the locking shaft (41) has a connecting ear (412) on its side wall, the connecting tube (33) has a slot on its side wall, the connecting ear (412) is slidably inserted into the slot, and the connecting ear (412) is detachably connected to the fixed structure (313) through the slot.

7. The star-rocket separation device according to claim 2, characterized in that, The separation component (50) includes: The cover (51) is detachably mounted on the rocket end connection structure (10); The second reset member (52) has one end connected to the cover (51) and the other end abutting against the satellite end connection structure (20). The second reset member (52) can drive the satellite end connection structure (20) away from the rocket end connection structure (10).

8. The star-rocket separation device according to claim 1, characterized in that, The star-rocket separation device also includes: A limit switch (70) is provided on the rocket end connection structure (10) to detect the relative position between the rocket end connection structure (10) and the satellite end connection structure (20).

Images