Satellite-rocket separation device

Abstract

The invention provides a satellite-rocket separation device, which comprises a rocket end connecting structure, a satellite-rocket separation structure and a satellite-rocket separation structure, wherein one end surface of the rocket end connecting structure is connected with a rocket; one end face of the satellite end connecting structure is used for being connected with a satellite, the other end face of the satellite end connecting structure abuts against the other end face of the rocket end connecting structure, and the satellite end connecting structure is provided with a connecting part; the driving assembly is arranged on the rocket end connecting structure; the clamping assembly comprises a locking shaft and a plurality of clamping pieces, the locking shaft is detachably connected with the driving assembly, the multiple clamping pieces are arranged on the locking shaft in a swinging mode, each clamping piece is provided with a clamping position and an avoiding position which are oppositely arranged, when the multiple clamping pieces are located at the clamping positions, the multiple clamping pieces are matched to clamp the connecting part, and when the multiple clamping pieces are located at the avoiding positions, the multiple clamping pieces are matched to clamp the connecting part; when the clamping piece is located at the avoiding position, the clamping piece is far away from the connecting part, and the driving assembly can drive the clamping piece to swing between the clamping position and the avoiding position. According to the technical scheme, the problem that in the prior art, a satellite-rocket separation device is poor in adaptability can be solved.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite-rocket separation devices, and in particular to a satellite-rocket separation device. Background Art

[0002] At present, the satellite-rocket separation device is a device that reliably connects the satellite and the rocket, and releases and separates the satellite after the satellite and rocket enter orbit. The satellite-rocket separation device plays an important role in satellite launches.

[0003] Existing micro-satellite separation generally uses explosive bolts, separation nuts and other pyrotechnic separation devices or memory alloy unlocking separation devices. Pyrotechnic separation devices have the disadvantages of undetectable separation performance, high separation impact, pollution and safety issues, while memory alloy unlocking separation devices have the disadvantages of relatively high ambient temperature requirements and increased unlocking time at low temperatures. Summary of the invention

[0004] The present invention 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 invention provides a satellite-rocket separation device, which includes: a rocket-end connection structure, one end face of the rocket-end connection structure is used to connect to the rocket; a satellite-end connection structure, one end face of the satellite-end connection structure is used to connect to the satellite, the other end face of the satellite-end connection structure abuts against the other end face of the rocket-end connection structure, and the satellite-end connection structure has a connecting portion; a driving assembly, which is arranged on the rocket-end connection structure; a clamping assembly, which includes a locking shaft and a plurality of clamping members, the locking shaft is detachably connected to the driving assembly, and the plurality of clamping members are all swingably arranged on the locking shaft, the plurality of clamping members are spaced apart along the circumference of the locking shaft, the clamping members have relatively arranged clamping positions and avoidance positions, when the plurality of clamping members are located at the clamping positions, the plurality of clamping members cooperate with the clamping connection portion, when the clamping members are located at the avoidance position, the clamping members are away from the connection portion, and the driving assembly can drive the clamping members to swing between the clamping position and the avoidance position.

[0006] Furthermore, a first reset member is provided between the clamping member and the locking shaft, and the first reset member can drive the clamping member to swing from the clamping position to the avoidance position.

[0007] Furthermore, the satellite-rocket separation device also includes a separation component, which is arranged between the rocket end connection structure and the satellite end connection structure, and the separation component is fixed on the rocket end connection structure. When the multiple clamps are in the avoidance position, the separation component drives the satellite end connection structure to separate from the rocket end connection structure.

[0008] Furthermore, the driving assembly includes: a fixed shell, fixed on the rocket end connecting structure, the fixed shell having a relatively connected through hole and a accommodating cavity, and the locking shaft is fixedly connected to the fixed shell; a driving structure, fixed on the fixed shell; a connecting tube, slidably arranged in the accommodating cavity, and the connecting tube is sleeved on the locking shaft, the driving structure is driven and connected to the connecting tube through the through hole, the connecting tube is located on the side of the clamping member away from the connecting part, the connecting tube has a driving end, the driving end is located between the clamping member and the locking shaft, and the driving structure drives multiple clamping members to swing synchronously between the clamping position and the avoidance position through the connecting tube.

[0009] Furthermore, the clamping member is hingedly connected to the locking shaft, and the clamping member has a connecting end and a clamping end that are relatively arranged, the connecting end is arranged close to the connecting tube relative to the clamping end, the clamping end can clamp the connecting part, the connecting end is gradually away from the locking shaft in the direction approaching the connecting tube, and the cross-sectional area of ​​the driving end gradually decreases in the direction approaching the clamping member.

[0010] Furthermore, the clamping member has a bent section at one end close to the connecting portion, and the connecting portion includes: a first connecting section, fixed on the satellite end connecting structure; a second connecting section, located at one end of the first connecting section close to the rocket end connecting structure, the diameter of the second connecting section is larger than the diameter of the first connecting section, and a step surface is provided between the first connecting section and the second connecting section, and when the clamping member is in the clamping position, the bent section abuts against the step surface.

[0011] Furthermore, a groove is provided on the second connecting section, and the cross-sectional area of ​​the groove gradually increases in the direction approaching the locking shaft. The locking shaft has a fixed section at one end close to the second connecting section, and the fixed section is located in the groove. The cross-sectional area of ​​the fixed section gradually decreases in the direction approaching the second connecting section, and the structure of the fixed section is adapted to that of the groove.

[0012] Furthermore, an elastic member is provided between the connecting pipe and the locking shaft to limit the displacement of the connecting pipe.

[0013] Furthermore, a fixing structure is provided at the opening of the fixing shell, a connecting ear is provided on the side wall of the locking shaft, a slot is provided on the side wall of the connecting tube, the connecting ear can be slidably inserted into the slot, and the connecting ear is detachably connected to the fixing structure through the slot.

[0014] Furthermore, the separation assembly includes: a cover body, which is detachably arranged on the rocket end connection structure; a second reset member, one end of which is connected to the cover body, and the other end of the second reset member abuts against the satellite end connection structure, and the second reset member can drive the satellite end connection structure away from the rocket end connection structure.

[0015] Furthermore, the satellite-rocket separation device also includes: a travel switch, which is arranged on the rocket end connecting structure and is used to detect the relative position between the rocket end connecting structure and the satellite end connecting structure.

[0016] By applying the technical solution of the present invention, the rocket end connection structure is connected to the rocket, the satellite end connection structure is connected to the satellite, and the rocket end connection structure and the satellite end connection structure are in contact with each other. The clamping member is fixed on the rocket end connection structure through a locking shaft and a driving assembly. The clamping member has a clamping position and an avoidance position that are relatively set, that is, the clamping member can clamp the connection part of the satellite end connection structure so that the rocket end connection structure and the satellite end connection structure are fixedly connected. When the clamping member is in the avoidance position, the clamping member is away from the connection part so that the rocket end connection structure and the satellite end connection structure are separated. The driving assembly can drive the clamping member to swing between the clamping position and the avoidance position. In this way, through the cooperation of the driving assembly and the clamping assembly, it is possible to achieve precise control of the rocket end connection structure and the satellite end connection structure, ensure safe unlocking and separation within a predetermined time, the separation time of the rocket end connection structure and the satellite end connection structure is short, avoid the uncontrollability and risks that may be caused by pyrotechnics, and avoid pollution. At the same time, by adopting the above structure, the rocket-satellite separation device is not limited by temperature and has good temperature adaptability. Due to the swinging design of the clamping piece, a gentle separation process can be achieved, avoiding the high impact force caused by sudden release or explosive separation, thereby ensuring the structural integrity and function of the satellite. Therefore, with the above structure, the satellite-rocket separation device has the performance of micro-impact, no pollution, low impact and high safety, thereby improving the adaptability of the satellite-rocket separation device. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The drawings constituting a part of the present application are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:

[0018] Figure 1 It shows a schematic structural diagram of a satellite-rocket separation device provided in an embodiment of the present invention;

[0019] Figure 2 It shows a schematic structural diagram of the satellite-rocket separation device when the clamping member provided in an embodiment of the present invention is located in the avoidance position;

[0020] Figure 3 It shows a structural schematic diagram of the satellite-rocket separation device when the clamping member provided in an embodiment of the present invention is in the clamping position;

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

[0022] Figure 5 A schematic structural diagram of a rocket end connection structure provided according to an embodiment of the present invention is shown;

[0023] Figure 6A schematic structural diagram of a fixed housing provided according to an embodiment of the present invention is shown;

[0024] Figure 7 It shows a schematic structural diagram of a locking shaft provided according to an embodiment of the present invention;

[0025] Figure 8 A schematic structural diagram of a separation component provided according to an embodiment of the present invention is shown.

[0026] The above drawings include the following reference numerals:

[0027] 10. Rocket end connection structure;

[0028] 20. Satellite terminal connection structure;

[0029] 21. Connecting part;

[0030] 211, first connecting section;

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

[0032] 30. Drive components;

[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. Fixing section; 412. Connecting ear; 413. Fixing ear;

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

[0039] 43. A first restoring member;

[0040] 50. Separate components;

[0041] 51. cover body; 52. second reset member; 53. guide shaft;

[0042] 60. Elastic parts;

[0043] 70. Limit switch. DETAILED DESCRIPTION

[0044] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments. The following description of at least one exemplary embodiment is actually only illustrative and is by no means intended to limit the present invention and its application or use. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0045] like Figures 1 to 5 As shown, the present application provides a satellite-rocket separation device, which includes a rocket-end connection structure 10, a satellite-end connection structure 20, a drive assembly 30 and a clamping assembly 40. One end surface of the rocket-end connection structure 10 is used to connect with the rocket. One end surface of the satellite-end connection structure 20 is used to connect with the satellite, and the other end surface of the satellite-end connection structure 20 abuts against the other end surface of the rocket-end connection structure 10, and the satellite-end connection structure 20 has a connection portion 21. The drive assembly 30 is arranged on the rocket-end connection structure 10. The clamping assembly 40 includes a locking shaft 41 and a plurality of clamping members 42. The locking shaft 41 is detachably connected to the driving assembly 30. The plurality of clamping members 42 are all swingably arranged on the locking shaft 41. The plurality of clamping members 42 are distributed at intervals along the circumference of the locking shaft 41. The clamping members 42 have relatively arranged clamping positions and avoidance positions. When the plurality of clamping members 42 are located at the clamping positions, the plurality of clamping members 42 cooperate with the clamping connection portion 21. When the clamping members 42 are located at the avoidance position, the clamping members 42 are away from the connection portion 21. The driving assembly 30 can drive the clamping members 42 to swing between the clamping position and the avoidance position.

[0046] By applying the technical solution of the present application, the rocket end connection structure 10 is connected to the rocket, the satellite end connection structure 20 is connected to the satellite, and the rocket end connection structure 10 is abutted against the satellite end connection structure 20. The clamping member 42 is fixed to the rocket end connection structure 10 through the locking shaft 41 and the driving assembly 30. The clamping member 42 has a relatively set clamping position and an avoidance position, that is, the clamping assembly 40 can clamp the connecting portion 21 of the satellite end connection structure 20 so that the rocket end connection structure 10 is fixedly connected to the satellite end connection structure 20. When the clamping member 42 is in the avoidance position, the clamping member 42 is away from the connecting portion 21 so that the rocket end connection structure 10 is separated from the satellite end connection structure 20. The driving assembly 30 can drive the clamping member 42 to swing between the clamping position and the avoidance position. With such arrangement, through the cooperation of the driving assembly 30 and the clamping assembly 40, it is possible to achieve precise control of the rocket end connection structure 10 and the satellite end connection structure 20, ensuring safe unlocking and separation within a predetermined time. The separation time of the rocket end connection structure 10 and the satellite end connection structure 20 is relatively short, avoiding the uncontrollability and risks that may be caused by pyrotechnics, and at the same time avoiding pollution. At the same time, by adopting the above structure, the satellite-rocket separation device is not limited by temperature and has good temperature adaptability. Due to the swinging design of the clamping member 42, a gentle separation process can be achieved, avoiding the high impact force caused by sudden release or explosive separation, thereby ensuring the structural integrity and function of the satellite. Therefore, by adopting the above structure, the satellite-rocket separation device has the performance of micro-impact, no pollution, low impact and high safety, thereby improving the adaptability of the satellite-rocket separation device.

[0047] Furthermore, in the present application, repeated locking and unlocking separation tests can be performed by operating the driving assembly 30 to ensure the reliability and effectiveness of the separation of the rocket-end connection structure 10 and the satellite-end connection structure 20.

[0048] Specifically, in the present application, the rocket end connection structure 10 and the satellite end connection structure 20 are made of aluminum and adopt a lightweight structural stiffness design. The rocket end connection structure 10 and the satellite end connection structure 20 are flange structures, and the outer edge of the flange structure adopts a lace structure.

[0049] like Figure 2 and Figure 3 As shown, there is a first reset member 43 between the clamping member 42 and the locking shaft 41, and the first reset member 43 can drive the clamping member 42 to swing from the clamping position to the avoidance position. In the present application, the driving assembly 30 can drive the clamping member 42 to swing from the avoidance position to the clamping position, and the first reset member 43 can drive the clamping member 42 to swing from the clamping position to the avoidance position. In this way, the first reset member 43 can automatically drive the clamping member 42 to swing without the need for additional operation or power source, which simplifies the swinging process of the clamping member 42 and improves the response speed of the clamping member 42.

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

[0051] like Figure 1 , Figure 4 and Figure 8 As shown, the satellite-rocket separation device further includes a separation assembly 50, which is disposed between the rocket-end connection structure 10 and the satellite-end connection structure 20, and is fixed to the rocket-end connection structure 10. When the plurality of clamping members 42 are located at the avoidance position, the separation assembly 50 drives the satellite-end connection structure 20 to separate from the rocket-end connection structure 10. With such a configuration, the separation assembly 50 can increase the separation speed of the satellite-end connection structure 20 and the rocket-end connection structure 10, facilitate the separation of the satellite-end connection structure 20 and the rocket-end connection structure 10, and thus facilitate the normal performance of subsequent work.

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

[0053] The fixed shell 31 is fixed on the rocket end connection structure 10, and the fixed shell 31 has a relatively connected through hole 311 and a receiving cavity 312, and the locking shaft 41 is fixedly connected to the fixed shell 31. The driving structure 32 is fixed on the fixed shell 31. Such a configuration facilitates the fixing of the locking shaft 41 and the driving structure 32, while improving the compactness of the driving assembly 30 and the clamping assembly 40, and reducing the total volume of the driving assembly 30 and the clamping assembly 40.

[0054] The connecting tube 33 is slidably disposed in the accommodating cavity 312, and the connecting tube 33 is sleeved on the locking shaft 41. The driving structure 32 is connected to 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 portion 21. The connecting tube 33 has a driving end 331, and the driving end 331 is located between the clamping member 42 and the locking shaft 41. The driving structure 32 drives the multiple clamping members 42 to swing synchronously between the clamping position and the avoidance position through the connecting tube 33. When the driving structure 32 drives the connecting tube 33 to move in a direction close 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 tube 33 to move in a direction 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.

[0055] In this way, through the linkage mechanism between the connecting tube 33 and the multiple 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 avoidance position, ensuring the consistency and controllability of the unlocking and separation of the satellite end connection structure 20, thereby improving the accuracy and reliability of the separation process.

[0056] In addition, the design of the connecting tube 33 and the fixed shell 31 simplifies the internal structure of the drive assembly 30, avoids the complex and fault-prone multi-point drive design, reduces maintenance costs and potential failure rates, and also reduces the overall weight and volume of the satellite-rocket separation device, while also being able to reduce 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 micro-satellites of different magnitudes.

[0058] The use of actuator electric drive unlocking reduces the impact of satellite-rocket separation and improves testability. At the same time, the actuator's motor has a short working time and the unlocking time is shorter than other existing separation products.

[0059] The clamping member 42 is hingedly connected to the locking shaft 41. This arrangement facilitates the clamping member 42 to swing relative to the locking shaft 41.

[0060] The clamping member 42 has a connecting end 421 and a clamping end 422 that are relatively arranged. 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 portion 21. The connecting end 421 is gradually arranged away from the locking shaft 41 along the direction approaching the connecting tube 33, and the cross-sectional area of ​​the driving end 331 gradually decreases along the direction approaching the clamping member 42.

[0061] The above structure facilitates the insertion of the driving end 331 between the connecting end 421 and the locking shaft 41 , thereby ensuring the reliability of the connecting tube 33 driving the clamping member 42 to swing.

[0062] like Figure 3 As shown, the end of the clamping member 42 close to the connecting portion 21 has a bent section 423. The connecting portion 21 includes a first connecting section 211 and a second connecting section 212. The first connecting section 211 is fixed to the satellite end connecting structure 20. The second connecting section 212 is located at an 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 the diameter of the first connecting section 211. There is a step surface between the first connecting section 211 and the second connecting section 212. When the clamping member 42 is in the clamping position, the bent section 423 abuts against the step surface.

[0063] In this way, the contact between the bent section 423 and the step surface forms a stable locking point, ensuring a firm connection between the satellite end connection structure 20 and the rocket end connection structure 10 during the launch process, and avoiding accidental unlocking due to vibration or external force. In addition, the step surface serves as a reference point when the clamp 42 is unlocked, ensuring the accuracy and consistency of the clamp 42 in the unlocking position, and avoiding separation shock or operation failure due to inaccurate unlocking position.

[0064] like Figure 3 and Figure 7 As shown, a groove 2121 is provided on the second connecting section 212, and the cross-sectional area of ​​the groove 2121 gradually increases in the direction approaching the locking shaft 41. The locking shaft 41 has a fixed section 411 at one end close to the second connecting section 212. The fixed section 411 is located in the groove 2121, and the cross-sectional area of ​​the fixed section 411 gradually decreases in the direction approaching the second connecting section 212. The structure of the fixed section 411 is adapted to that of the groove 2121.

[0065] With such a configuration, during the unlocking process, the locking shaft 41 can move smoothly along the guide of the groove 2121, reducing friction and resistance during movement, ensuring smooth and accurate unlocking, and thus reducing the impact force when the satellite-rocket separation device is unlocked. In addition, the fixed section 411 is compatible with the structure of the groove 2121, forming a self-locking mechanism. Even if there is severe vibration and impact during the satellite launch process, the locking shaft 41 can remain stable, preventing accidental unlocking, and improving the reliability and safety of the connection.

[0066] Furthermore, an elastic member 60 is provided between the connecting tube 33 and the locking shaft 41 to limit the displacement of the connecting tube 33. This arrangement can ensure the stability of the connecting tube 33 during the up and down movement, and can avoid collision between the connecting tube 33 and the locking shaft 41.

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

[0068] like Figure 6 and Figure 7 As shown, a fixing structure 313 is provided at the opening of the fixing shell 31, a connecting ear 412 is provided on the side wall of the locking shaft 41, and a groove is provided on the side wall of the connecting tube 33. The connecting ear 412 can be slidably inserted into the groove, and the connecting ear 412 is detachably connected to the fixing structure 313 through the groove.

[0069] In this way, the fixing structure 313 at the opening of the fixing shell 31 cooperates with the connecting ear 412 on the side wall of the locking shaft 41, and the connecting ear 412 can be slidably inserted into the slot, ensuring the precise alignment and stability of the connecting tube 33 during the sliding process, avoiding shaking or deviation during the sliding process, thereby improving the reliability of the driving assembly 30 and the stability of the satellite-rocket separation. At the same time, the above structure is adopted to facilitate the fixing of the locking shaft 41, reducing the difficulty of fixing the locking shaft 41.

[0070] Specifically, in the present application, four fixing structures 313 are provided at the opening of the fixing shell 31 , and four connecting ears 412 are provided on the side wall of the locking shaft 41 . The four fixing structures 313 are provided in a one-to-one correspondence with the four connecting ears 412 .

[0071] Among them, 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. Each group of fixing ears 413 has two fixing ears 413, and each group of fixing ears 413 is detachably connected to a clamping member 42.

[0072] Further, the separation assembly 50 includes a cover 51 and a second reset member 52. The cover 51 is detachably arranged on the rocket end connection structure 10. One end of the second reset member 52 is connected to the cover 51, and the other end of the second reset member 52 abuts against the satellite end connection structure 20, and the second reset member 52 can drive the satellite end connection structure 20 away from the rocket end connection structure 10.

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

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

[0075] Among them, the separation component 50 also includes a guide shaft 53, and the guide shaft 53 is inserted into the second reset member 52. Such a configuration can guide the second reset member 52 to avoid the second reset member 52 from being offset during operation, thereby further improving the accuracy of satellite-rocket separation.

[0076] like Figure 1 As shown, the satellite-rocket separation device also includes a travel switch 70, which is arranged on the rocket end connection structure 10 and is used to detect the relative position between the rocket end connection structure 10 and the satellite end connection structure 20. In this way, the travel switch 70 can detect the relative position between the rocket end connection structure 10 and the satellite end connection 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 describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0078] Unless otherwise specifically stated, the relative arrangement, numerical expressions and numerical values ​​of the parts and steps set forth in these embodiments do not limit the scope of the present invention. Meanwhile, it should be understood that, for ease of description, the sizes of the various parts shown in the accompanying drawings are not drawn according to the actual proportional relationship. The technology, method and equipment known to those of ordinary skill in the relevant art may not be discussed in detail, but in appropriate cases, the technology, method and equipment should be considered as a part of the specification. In all examples shown and discussed here, any specific value should be interpreted as being merely exemplary, rather than as a limitation. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters represent similar items in the following drawings, and therefore, once a certain item is defined in an accompanying drawing, it does not need to be further discussed in subsequent drawings.

[0079] In the description of the present invention, it is necessary to understand that the directions or positional relationships indicated by directional words such as "front, back, up, down, left, right", "lateral, vertical, perpendicular, horizontal" and "top, bottom" are usually based on the directions or positional relationships shown in the drawings. They are only for the convenience of describing the present invention and simplifying the description. Unless otherwise specified, these directional words do not indicate or imply that the devices or elements referred to must have a specific direction or be constructed and operated in a specific direction. Therefore, they cannot be understood as limiting the scope of protection of the present invention. The directional words "inside and outside" refer to the inside and outside relative to the contours of each component itself.

[0080] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0081] In addition, it should be noted that the use of terms such as "first" and "second" to limit components is only for the convenience of distinguishing the corresponding components. If not otherwise stated, the above terms have no special meaning and therefore cannot be understood as limiting the scope of protection of the present invention.

[0082] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A satellite-rocket separation device, characterized in that: The satellite-rocket separation device comprises: A rocket end connection structure (10), wherein one end surface of the rocket end connection structure (10) is used to be connected to the rocket; A satellite end connection structure (20), wherein one end surface of the satellite end connection structure (20) is used for connection with a satellite, the other end surface of the satellite end connection structure (20) is in contact with the other end surface of the rocket end connection structure (10), and the satellite end connection structure (20) has a connection portion (21); A driving assembly (30) disposed on the rocket end connection structure (10); A clamping assembly (40), wherein the clamping assembly (40) comprises a locking shaft (41) and a plurality of clamping members (42), wherein the locking shaft (41) is detachably connected to the driving assembly (30), wherein the plurality of clamping members (42) are all swingably arranged on the locking shaft (41), wherein the plurality of clamping members (42) are spaced apart along the circumference of the locking shaft (41), wherein the clamping members (42) have relatively arranged clamping positions and avoidance positions, wherein when the plurality of clamping members (42) are located at the clamping positions, the plurality of clamping members (42) cooperate to clamp the connecting portion (21), and when the clamping members (42) are located at the avoidance positions, the clamping members (42) are away from the connecting portion (21), and the driving assembly (30) is capable of driving the clamping members (42) to swing between the clamping positions and the avoidance positions.

2. The satellite-rocket separation device according to claim 1, characterized in that: A first reset member (43) is provided between the clamping member (42) and the locking shaft (41), and the first reset member (43) can drive the clamping member (42) to swing from the clamping position to the avoidance position.

3. The satellite-rocket separation device according to claim 1, characterized in that: The satellite-rocket separation device also includes a separation component (50), which is arranged 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 located at the avoidance position, the separation component (50) drives the satellite end connection structure (20) to separate from the rocket end connection structure (10).

4. The satellite-rocket separation device according to claim 1, characterized in that: The driving assembly (30) comprises: A fixed shell (31) is fixed on the rocket end connection structure (10), the fixed shell (31) has a relatively connected through hole (311) and a receiving cavity (312), and the locking shaft (41) is fixedly connected to the fixed shell (31); A driving structure (32) fixed on the fixed shell (31); A connecting tube (33) is slidably arranged in the accommodating cavity (312), and the connecting tube (33) is sleeved on the locking shaft (41). The driving structure (32) is drivingly connected to the connecting tube (33) through the through hole (311). The connecting tube (33) is located on a side of the clamping member (42) away from the connecting portion (21). The connecting tube (33) has a driving end (331), and the driving end (331) is 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 avoidance position through the connecting tube (33).

5. The satellite-rocket separation device according to claim 4, characterized in that: The clamping member (42) is hingedly connected to the locking shaft (41), and the clamping member (42) comprises a connecting end (421) and a clamping end (422) which are 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 portion (21), the connecting end (421) is arranged gradually away from the locking shaft (41) along the direction approaching the connecting tube (33), and the cross-sectional area of ​​the driving end (331) gradually decreases along the direction approaching the clamping member (42).

6. The satellite-rocket separation device according to claim 1, characterized in that: The clamping member (42) has a bent section (423) at one end close to the connecting portion (21), and the connecting portion (21) comprises: A first connecting section (211) 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 larger than the diameter of the first connecting section (211), and a step surface is provided between the first connecting section (211) and the second connecting section (212), and when the clamping member (42) is located at the clamping position, the bending section (423) abuts against the step surface.

7. The satellite-rocket separation device according to claim 6, characterized in that: The second connecting section (212) is provided with a groove (2121), and the cross-sectional area of ​​the groove (2121) gradually increases in a direction approaching the locking shaft (41). The locking shaft (41) has a fixed section (411) at one end close to the second connecting section (212), and the fixed section (411) is located in the groove (2121). The cross-sectional area of ​​the fixed section (411) gradually decreases in a direction approaching the second connecting section (212), and the structure of the fixed section (411) is adapted to that of the groove (2121).

8. The satellite-rocket separation device according to claim 4, characterized in that: An elastic member (60) is provided between the connecting tube (33) and the locking shaft (41) to limit the displacement of the connecting tube (33).

9. The satellite-rocket separation device according to claim 4, characterized in that: A fixing structure (313) is provided at the opening of the fixing shell (31), a connecting ear (412) is provided on the side wall of the locking shaft (41), and a slot is provided on the side wall of the connecting tube (33), the connecting ear (412) is slidably inserted into the slot, and the connecting ear (412) is detachably connected to the fixing structure (313) via the slot.

10. The satellite-rocket separation device according to claim 3, characterized in that: The separation assembly (50) comprises: A cover body (51) is detachably arranged on the rocket end connection structure (10); A second restoring member (52), one end of the second restoring member (52) is connected to the cover body (51), and the other end of the second restoring member (52) is abutted against the satellite end connection structure (20), and the second restoring member (52) can drive the satellite end connection structure (20) away from the rocket end connection structure (10).

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

Images