Low-impact optical camera and satellite platform separation device

Abstract

The invention relates to the technical field of space optics, in particular to a low-impact separation device between an optical camera and a satellite platform, which comprises a controller and at least six separation supports, and the at least six separation supports are uniformly arranged at intervals in the direction of the outer envelope circumference of the satellite platform and the optical camera. The at least six separation supports are divided into a plurality of separation support sets, and the separation supports of each separation support set are adjacent to the separation supports of at least one other separation support set. The separation support comprises two supports which are connected and symmetrically arranged, one support is connected to the optical camera, and the other support is connected to the satellite. The support comprises a shell, a support butt joint end and an explosive bolt. The explosive bolt is connected to the support butt joint end and located in a containing space defined by the support butt joint end and the shell. And the controller is used for receiving a detonation signal to activate the explosive bolts, so that the explosive bolts of different separation support groups are detonated at different time, and the explosive bolts of the same separation support group are detonated simultaneously.

Description

Technical Field

[0001] The invention belongs to the field of space optics technology, and in particular relates to a low-impact separation device between an optical camera and a satellite platform. Background Art

[0002] Ultra-large aperture optical cameras require special devices when connected to satellite platforms due to their large size, heavy weight, and high stability to meet high resolution. This device must not only ensure a firm connection between the optical camera and the satellite platform, but also unlock and separate as required after the satellite enters orbit. In other words, the device needs to meet the requirements of stable connection and reliable unlocking.

[0003] Traditionally, optical cameras and satellite platforms are usually supported by three points. However, with the development of high-resolution optical remote sensing technology, the aperture of optical cameras is getting larger and larger, and the requirements for their stability are getting higher and higher. The traditional three-point support method is too large in the local force at a single point, resulting in insufficient stability of the optical camera. It can no longer meet the support requirements between optical cameras with an aperture of more than 2 meters and satellite platforms. Multiple supports must be used to complete the connection between the optical camera and the satellite platform. And as the size and weight of the optical camera increase, the load-bearing specifications of the pyrotechnics (i.e., explosive bolts) used for the rigid connection between the optical camera and the satellite platform become larger. Correspondingly, the impact force generated by the explosion of the pyrotechnics also becomes several times or even dozens of times the original, making the optical camera and the satellite platform easily affected by the impact force generated by the explosion of the pyrotechnics. The optical elements of the optical camera, the precision mechanism of the satellite platform, and the electric unit will all be destructively affected. Summary of the invention

[0004] In view of this, the present invention aims to provide a low-impact separation device between an optical camera and a satellite platform, which greatly reduces the impact of the explosion impact force of the explosive bolt on the optical camera and the satellite platform.

[0005] To achieve the above object, the technical solution created by the present invention is implemented as follows: A low-impact separation device between an optical camera and a satellite platform, comprising a controller and at least six separation supports, wherein the at least six separation supports are evenly spaced and arranged along the direction of the outer envelope circumference of the satellite platform and the optical camera, and the at least six separation supports are divided into a plurality of separation support groups, wherein the separation supports of each separation support group are adjacent to the separation supports of at least one other separation support group; The separation support includes two supports that are connected and symmetrically arranged, one of which is connected to the optical camera and the other is connected to the satellite platform; the support includes a shell, a support docking end and an explosive bolt; the explosive bolt is connected to the support docking end and is located in a receiving space formed by the support docking end and the shell; The controller is used to receive the detonation signal to activate the explosive bolts, so that the explosive bolts of different groups of separation support groups are detonated at different times, and the explosive bolts of the same group of separation support groups are detonated at the same time.

[0006] Furthermore, the support includes a buffer component, which is arranged in the accommodating space and between the connecting end of the shell and the explosive bolt; the connecting end of the shell is used to be connected to the optical camera or the satellite platform.

[0007] Furthermore, the buffer assembly includes an impact-reducing baffle, which includes a baffle plane portion and a plurality of buffer grooves arranged at intervals, wherein the side walls of the buffer grooves extend obliquely from the baffle plane portion, in a direction away from the explosive bolt, and in a direction close to the axis of the buffer groove; the buffer groove is provided with a first through hole for the bolt head of the explosive bolt to pass through.

[0008] Furthermore, the plane portion of the baffle is provided with a plurality of stress groove groups, which are arranged close to the buffer groove and are arranged at intervals along the radial direction of the buffer groove; one stress groove group includes two stress grooves, which are respectively arranged on the opposite side surfaces of the plane portion of the baffle, and the stress groove is recessed downward from one side surface of the plane portion of the baffle and extends along the circumference of the buffer groove.

[0009] Furthermore, the support also includes a combined trap, which is arranged in the accommodating space and between the connecting end of the shell and the impact-reducing baffle; the combined trap includes a planar portion and a plurality of tapered grooves, and the side walls of the tapered grooves extend obliquely from the planar portion, in a direction away from the explosive bolt, and in a direction away from the axis of the tapered groove; the tapered groove is provided with a second through hole for the bolt head of the explosive bolt to pass through.

[0010] Furthermore, in the axial direction of the tapered groove, the ratio of the diameter difference between the two opposite sides of the tapered groove to the height of the tapered groove is 1:15.

[0011] Furthermore, the upper surface of the impact-reducing baffle is in contact with the lower surface of the combined trap, and the second through hole is aligned with the first through hole.

[0012] Furthermore, the buffer assembly also includes an impact-reducing retaining ring, which includes a central portion and an edge portion connected to the shell, and the impact-reducing retaining ring extends in an arc shape from the edge portion to the central portion; the impact-reducing retaining ring is provided with a plurality of third through holes arranged at intervals.

[0013] Furthermore, the shell includes an impact-reducing cover and a mounting cover; the impact-reducing cover is connected to the mounting cover, and the impact-reducing cover is located at the connecting end of the shell.

[0014] Furthermore, the buffer component is made of metal material.

[0015] Compared with the prior art, the invention can achieve the following beneficial effects: The present invention creates a low-impact separation device between an optical camera and a satellite platform, wherein at least six separation supports are evenly spaced and arranged along the direction of the outer envelope circumference of the satellite platform and the optical camera. While realizing a high-load-bearing and high-reliability connection between the optical camera and the satellite platform, multiple separation supports are detonated in groups, that is, the explosive bolts of different groups of separation supports are detonated at different times, the explosive bolts of the same group of separation supports are detonated simultaneously, and the two explosive bolts in each separation support are combined in a symmetrical shock-reducing manner, so that the impact response can be reduced, the influence of the explosive impact force of the explosive bolts on the optical camera and the satellite platform is greatly reduced, and the impact response of the unlocking explosion of the separation support on the optical elements of the optical camera and each single machine of the satellite platform is reduced. The device can be widely used in the design of multi-point connection structures of various large-caliber optical payloads and satellite platforms. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The drawings constituting part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments and descriptions of the present invention are used to explain the present invention and do not constitute an improper limitation on the present invention. In the drawings: Figure 1 A schematic diagram of the structure of a low-impact separation device between an optical camera and a satellite platform in one direction according to an embodiment of the present invention; Figure 2 A schematic diagram of the structure of the low-impact separation device between the optical camera and the satellite platform in another direction according to an embodiment of the present invention; Figure 3 A schematic structural diagram of a separation support of a separation device between a low-impact optical camera and a satellite platform as described in an embodiment of the present invention.

[0017] Description of reference numerals: 10. Separation device; 11. Separation support; 12. Separation support group; 13. Support; 14. Shell; 15. Support docking end; 16. Explosive bolt; 17. Accommodation space; 18. Buffer assembly; 19. Connecting end; 20. Impact reduction baffle; 21. Baffle plane portion; 22. Buffer groove; 23. Stress groove group; 24. Stress groove; 25. Combined trap; 26. Plane portion; 27. Taper groove; 28. First through hole; 29. ​​Second through hole; 30. Impact reduction retaining ring; 31. Third through hole; 32. Impact reduction cover; 33. Mounting cover; 34. Detonating cord. DETAILED DESCRIPTION

[0018] In order to make the purpose, technical scheme and advantages of the invention clearer, the invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only used to explain the invention and do not constitute a limitation to the invention. Similar components in different embodiments use associated similar component numbers. In the following embodiments, many detailed descriptions are to enable the invention to be better understood. However, those skilled in the art can easily recognize that some of the features can be omitted in different situations, or can be replaced by other components, materials, and methods. In some cases, some operations related to the invention are not shown or described in the specification, in order to avoid the core part of the invention being overwhelmed by too much description, and for those skilled in the art, it is not necessary to describe these related operations in detail, and they can fully understand the related operations according to the description in the specification and the general technical knowledge in the art.

[0019] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other to form various implementation methods. At the same time, the steps or actions in the method description can also be interchanged or adjusted in a manner that is obvious to those skilled in the art. Therefore, the various sequences in the specification and the drawings are only for the purpose of clearly describing a certain embodiment and are not meant to be a necessary sequence, unless otherwise specified that a certain sequence must be followed.

[0020] In the description of the invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the drawings, and are only for the convenience of describing the invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the invention. In addition, the terms "first", "second", etc. are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first", "second", etc. may explicitly or implicitly include one or more of the features. In the description of the invention, unless otherwise specified, the meaning of "multiple" is two or more.

[0021] In the description of the invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the invention can be understood according to specific circumstances.

[0022] The present invention will be described in detail below with reference to the accompanying drawings and in combination with embodiments.

[0023] See also Figure 1 , Figure 2 and Figure 3 As shown, an embodiment of the invention provides a low-impact separation device 10 between an optical camera and a satellite platform, wherein the optical camera refers to an optical remote sensing camera. The separation device 10 includes a controller and at least six separation supports 11. The at least six separation supports 11 are evenly spaced along the direction of the outer envelope circumference of the satellite platform and the optical camera, and the at least six separation supports 11 are divided into multiple separation support groups 12, wherein the number of separation supports 11 in the multiple separation support groups 12 may be the same or different. The separation supports 11 of each separation support group 12 are adjacent to the separation supports 11 of at least one other separation support group 12. Figure 1 In the illustrated embodiment, the separation device 10 includes six separation supports 11. The six separation supports 11 are evenly spaced and arranged along the outer envelope circumference of the satellite platform and the optical camera. The six separation supports 11 are divided into two separation support groups 12, each of which has three separation supports 11. Separation supports 11 of another separation support group 12 are arranged on adjacent sides of one separation support 11 in one separation support group 12.

[0024] The separation support 11 includes two supports 13 connected and symmetrically arranged, wherein one support 13 is connected to the optical camera, and the other support 13 is connected to the satellite platform. The support 13 includes a shell 14, a support docking end 15, and an explosive bolt 16. The explosive bolt 16 is connected to the support docking end 15 and is located in a receiving space 17 enclosed by the support docking end 15 and the shell 14. The support 13 includes the explosive bolt 16, and the two supports 13 are symmetrically arranged, so that each separation support 11 is locked by two symmetrical explosive bolts 16. The two explosive bolts 16 are symmetrically connected in series. Only one explosive bolt 16 needs to be exploded, and the lock between the two supports 13 is released, so that the lock between the optical camera and the satellite platform is released. It is easy to unlock, and the unlocking reliability is improved compared with the reliability of locking with a single explosive bolt 16 or locking with a parallel explosive bolt 16. When the explosive bolt 16 explodes, the bolt head and the screw rod of the explosive bolt 16 will quickly separate at the separation pre-section A. When two symmetrically arranged explosive bolts 16 are used at the same time, the two bolt heads of the two explosive bolts 16 will fly away in opposite directions under the action of the explosive force, and the impulses of the two screw rods of the two explosive bolts 16 will cancel each other out.

[0025] The controller is used to receive the detonation signal to activate the explosive bolts 16, so that the explosive bolts 16 of different groups of separated support groups 12 are detonated at different times, and the explosive bolts 16 of the same group of separated support groups 12 are detonated at the same time. The controller is used to receive the detonation signal and send a trigger signal to the electric ignition device to activate the explosive bolts 16 through the detonating cord 34. Figure 1 In the embodiment shown, all the explosive bolts 16 of one separation support group 12 may be detonated first, and then all the explosive bolts 16 of another separation support group 12 may be detonated. This may reduce the impact energy by about 50%.

[0026] The present invention creates a low-impact separation device 10 between an optical camera and a satellite platform, wherein at least six separation supports 11 are evenly spaced and arranged along the outer envelope circumference of the satellite platform and the optical camera. While realizing a high-load-bearing, high-reliability connection between the optical camera and the satellite platform, multiple separation supports 11 are detonated in groups, that is, the explosive bolts 16 of different groups of separation support groups 12 are detonated at different times, the explosive bolts 16 of the same group of separation support groups 12 are detonated simultaneously, and the two explosive bolts 16 in each separation support 11 are combined in a symmetrical shock-reducing manner, so that the shock response can be reduced, and the impact of the explosive impact force of the explosive bolts 16 on the optical camera and the satellite platform is greatly reduced, and the impact response of the unlocking explosion of the separation support 11 on the optical elements of the optical camera and each single unit of the satellite platform is reduced. The device can be widely used in the design of multi-point connection structures of various large-caliber optical payloads and satellite platforms.

[0027] In one embodiment, the support 13 includes a buffer assembly 18, which is arranged in the accommodating space 17 and between the connecting end 19 of the shell 14 and the explosive bolt 16. The buffer assembly 18 can be fixedly connected to the inner wall of the shell 14 by bolts. When the explosive bolt 16 explodes, the buffer assembly 18 is located on the flight path of the bolt head, which can reduce the impact response transmitted to the satellite platform and the optical camera. The connecting end 19 of the shell 14 is used to connect to the optical camera or the satellite platform. The connecting end 19 of the shell 14 of one of the supports 13 of the separation support 11 is connected to the optical camera, and the connecting end 19 of the shell 14 of the other support 13 is connected to the satellite platform.

[0028] In one embodiment, the buffer assembly 18 includes an impact-reducing baffle 20, which includes a baffle plane portion 21 and a plurality of buffer grooves 22 arranged at intervals, and the side wall of the buffer groove 22 extends obliquely from the baffle plane portion 21, in a direction away from the explosive bolt 16, and in a direction close to the axis of the buffer groove 22. The buffer groove 22 is provided with a first through hole 28 for the bolt head of the explosive bolt 16 to pass through. After the explosive bolt 16 explodes and separates, the bolt head flying at high speed collides with the impact-reducing baffle 20, causing the impact-reducing baffle 20 to deform and absorb a portion of the energy, and the bolt head can pass through the first through hole 28 of the buffer groove 22 and fly in the direction of the connecting end 19 of the shell 14. The buffer groove 22 is provided so that it is difficult for the bolt head to return to the side of the support docking end 15 through the first through hole 28, thereby realizing the non-return function of the bolt head.

[0029] In one embodiment, the baffle plane portion 21 is provided with a plurality of stress groove groups 23, which are arranged close to the buffer groove 22 and arranged at intervals along the radial direction of the buffer groove 22. In this embodiment, the baffle plane portion 21 is provided with three stress groove groups 23. One group of stress groove groups 23 includes two stress grooves 24, which are respectively arranged on two opposite side surfaces of the baffle plane portion 21, and the stress grooves 24 are recessed downward from one side surface of the baffle plane portion 21 and extend along the circumference of the buffer groove 22. In this way, when the high-speed flying bolt head collides with the impact-reducing baffle 20, the impact-reducing baffle 20 can be deformed and absorb a portion of the energy.

[0030] In one embodiment, the support 13 further includes a combined trap 25, wherein the combined trap 25 can be made of a metal material, such as aluminum, steel, titanium alloy, etc. The combined trap 25 is arranged in the accommodating space 17 and between the connecting end 19 of the housing 14 and the impact reducing baffle 20. The combined trap 25 includes a plane portion 26 and a plurality of tapered grooves 27, and the side walls of the tapered grooves 27 extend obliquely from the plane portion 26, in a direction away from the explosive bolt 16, and in a direction away from the axis of the tapered grooves 27. The tapered grooves 27 are provided with a second through hole 29 for the bolt head of the explosive bolt 16 to pass through. The bolt head flying at high speed after the explosive bolt 16 explodes and separates can pass through the second through hole 29 of the tapered groove 27 and fly in the direction of the connecting end 19 of the housing 14. The provision of the tapered grooves 27 makes it difficult for the bolt head to return to the side of the support docking end 15 through the second through hole 29, thereby realizing the non-return function of the bolt head.

[0031] In one embodiment, the upper surface of the impact-reducing baffle 20 abuts against the lower surface of the combined trap 25 , and the second through hole 29 is aligned with the first through hole 28 .

[0032] In one embodiment, in the axial direction of the tapered groove 27, the ratio of the diameter difference between the two opposite sides of the tapered groove 27 and the height of the tapered groove 27 is 1:15. This can prevent the bolt head from returning to the side of the support butt end 15.

[0033] In one embodiment, the buffer assembly 18 further includes an impact reducing retaining ring 30, which includes a central portion and an edge portion connected to the housing 14, and the impact reducing retaining ring 30 extends in an arc shape from the edge portion to the central portion. The impact reducing retaining ring 30 extends in an arc shape from the edge portion to the central portion and in a direction close to the combined trap 25. The impact reducing retaining ring 30 is provided with a plurality of third through holes 31 arranged at intervals. The combined trap 25 is provided between the impact reducing retaining plate 20 and the impact reducing retaining ring 30. After the explosive bolt 16 explodes and separates, the bolt head flying at high speed collides with the impact reducing retaining ring 30, causing the impact reducing retaining ring 30 to deform and absorb a portion of the energy. The bolt head can pass through the third through hole 31 of the impact reducing retaining ring 30 and fly in the direction of the connecting end 19 of the housing 14, or can be restricted between the impact reducing retaining ring 30 and the combined trap 25.

[0034] In one embodiment, in the axial direction of the housing 14 , the impact-reducing baffle 20 , the combined trap 25 , and the impact-reducing baffle ring 30 are sequentially arranged.

[0035] In one embodiment, the housing 14 includes an impact-reducing cover 32 and a mounting cover 33. The impact-reducing cover 32 is made of metal material, such as aluminum, steel, titanium alloy, etc. The impact-reducing cover 32 is connected to the mounting cover 33, and the impact-reducing cover 32 is located at the connection end 19 of the housing 14. After the explosive bolt 16 is separated by explosion, the bolt head flying at high speed can collide with the impact-reducing cover 32, causing the impact-reducing cover 32 to deform and absorb part of the energy, thereby greatly reducing the impact transmitted to the optical camera and / or the satellite platform.

[0036] In one embodiment, the buffer assembly 18 is made of metal material, such as aluminum, steel, titanium alloy, etc. The materials of the impact-reducing baffle 20, the impact-reducing baffle ring 30 and the impact-reducing cover 32 may be the same or different.

[0037] exist Figure 3 In the embodiment shown, a triple impact reduction structure is designed according to the flight trajectory of the bolt head after the explosive bolt 16 is separated by explosion, and the bolt head flying at high speed can pass through the impact reduction baffle 20, the combined trap 25, the impact reduction retaining ring 30 and the impact reduction cover 32 in sequence. The bolt head flying at high speed can first pass through the impact reduction baffle 20, collide with the impact reduction baffle 20, so that the impact reduction baffle 20 is deformed and absorbs a part of the energy, and fly to the impact reduction retaining ring 30 through the first through hole 28 and the second through hole 29. The bolt head passes through the impact reduction retaining ring 30, collides with the impact reduction retaining ring 30, so that the impact reduction retaining ring 30 is deformed and absorbs a part of the energy, and finally flies to the impact reduction cover 32 through the third through hole 31. The deformation of the impact reduction cover 32 can absorb a part of the energy again, thereby greatly reducing the impact response transmitted to the optical camera and the satellite platform. After many tests, it can be obtained that the triple impact reduction structure can effectively reduce the impact energy by about 30%.

[0038] The embodiment of the present invention provides a low-impact separation device 10 between an optical camera and a satellite platform, which can effectively reduce the impact energy by about 80%, and effectively ensure the normal operation of the optical elements of the optical camera and each unit of the satellite.

[0039] It should be understood that the various forms of processes shown above can be used to reorder, add or delete steps. For example, the steps described in the disclosure of the present invention can be performed in parallel, sequentially or in different orders, as long as the desired results of the technical solution disclosed in the present invention can be achieved, and this document does not limit this.

[0040] The above specific implementations do not constitute a limitation on the protection scope of the present invention. It should be understood by those skilled in the art that various modifications, combinations, sub-combinations and substitutions can be made according to design requirements and other factors. Any modification, equivalent substitution and improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A low-impact separation device between an optical camera and a satellite platform, characterized in that: It comprises a controller and at least six separation supports, wherein the at least six separation supports are evenly spaced and arranged along the direction of the outer envelope circumference of the satellite platform and the optical camera, and the at least six separation supports are divided into a plurality of separation support groups, and the separation supports of each separation support group are adjacent to the separation supports of at least one other separation support group; The separation support comprises two supports which are connected and symmetrically arranged, wherein one of the supports is connected to the optical camera, and the other support is connected to the satellite platform; the support comprises a shell, a support docking end and an explosive bolt; the explosive bolt is connected to the support docking end and is located in a receiving space formed by the support docking end and the shell; The controller is used to receive a detonation signal to activate the explosive bolts, so that the explosive bolts of different groups of the separation support groups are detonated at different times, and the explosive bolts of the same group of the separation support groups are detonated simultaneously.

2. The low-impact separation device between an optical camera and a satellite platform according to claim 1, characterized in that: The support includes a buffer component, which is arranged in the accommodating space and located between the connecting end of the shell and the explosive bolt; the connecting end of the shell is used to be connected to the optical camera or the satellite platform.

3. The low-impact separation device between an optical camera and a satellite platform according to claim 2, characterized in that: The buffer assembly includes an impact-absorbing baffle, which includes a baffle plane portion and a plurality of buffer grooves arranged at intervals. The side walls of the buffer grooves extend obliquely from the baffle plane portion, in a direction away from the explosive bolt, and in a direction close to the axis of the buffer groove. The buffer groove is provided with a first through hole for the bolt head of the explosive bolt to pass through.

4. The low-impact separation device between an optical camera and a satellite platform according to claim 3, characterized in that: The baffle plate plane portion is provided with a plurality of stress groove groups, the plurality of stress groove groups are arranged close to the buffer groove and are arranged at intervals along the radial direction of the buffer groove; one stress groove group includes two stress grooves, the two stress grooves are respectively arranged on the two opposite side surfaces of the baffle plate plane portion, the stress grooves are recessed downward from one side surface of the baffle plate plane portion, and are extended along the circumference of the buffer groove.

5. The low-impact separation device between an optical camera and a satellite platform according to claim 3, characterized in that: The support also includes a combined trap, which is arranged in the accommodating space and between the connecting end of the shell and the impact-reducing baffle; the combined trap includes a planar portion and a plurality of tapered grooves, and the side walls of the tapered grooves extend obliquely from the planar portion in a direction away from the explosive bolt and in a direction away from the axis of the tapered groove; the tapered groove is provided with a second through hole for the bolt head of the explosive bolt to pass through.

6. The low-impact separation device between an optical camera and a satellite platform according to claim 5, characterized in that: In the axial direction of the tapered groove, the ratio of the diameter difference between the two opposite sides of the tapered groove to the height of the tapered groove is 1:

15.

7. The low-impact separation device between an optical camera and a satellite platform according to claim 5, characterized in that: The upper surface of the impact-reducing baffle is in contact with the lower surface of the combined trap, and the second through hole is aligned with the first through hole.

8. The low-impact separation device between an optical camera and a satellite platform according to claim 2, characterized in that: The buffer assembly also includes an impact-reducing retaining ring, which includes a central portion and an edge portion connected to the shell, and the impact-reducing retaining ring extends in an arc shape from the edge portion to the central portion; the impact-reducing retaining ring is provided with a plurality of third through holes arranged at intervals.

9. The low-impact separation device between an optical camera and a satellite platform according to claim 2, characterized in that: The shell comprises an impact-reducing cover and a mounting cover; the impact-reducing cover is connected to the mounting cover, and the impact-reducing cover is located at the connecting end of the shell.

10. The low-impact separation device between an optical camera and a satellite platform according to claim 2, characterized in that: The buffer component is made of metal material.

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