A separation device between a low-impact optical camera and a satellite platform

Abstract

The present invention relates to the field of space optical technology, and particularly to a separation device between an optical camera and a satellite platform with low impact, which includes a controller and at least six separation supports. The at least six separation supports are evenly spaced along the circumferential direction of the outer envelopes of the satellite platform and the optical camera. The at least six separation supports are divided into multiple groups of separation support groups, and the separation supports of each group of separation support groups are adjacent to the separation supports of at least one other group of separation support groups. Each 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. Each support includes a housing, a support docking end, and an explosive bolt. The explosive bolt is connected to the support docking end and is located in the accommodation space formed by the enclosure of the support docking end and the housing. The controller is used to receive a detonation signal to activate the explosive bolt, so that the explosive bolts of different groups of separation support groups detonate at different times, and the explosive bolts of the same group of separation support groups detonate simultaneously.

Description

Technical Field

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

[0002] Due to its large volume, heavy weight, and the need for high stability to meet the requirements of high resolution, a special device is required when a super-large-aperture optical camera is connected to a satellite platform. This device not only needs to ensure a firm connection between the optical camera and the satellite platform, but also needs to be unlocked and separated as required after the satellite enters the orbit. That is, this device needs to meet the requirements of stable connection and reliable unlocking.

[0003] Traditionally, the connection between an optical camera and a satellite platform is usually a three-point support. However, with the development of high-resolution optical remote sensing technology, the aperture of the optical camera is getting larger and larger, and the requirement for its stability is also getting higher and higher. Due to the excessive local force on a single point in the traditional three-point support method, the stability of the optical camera is insufficient, and it can no longer meet the support requirements between an optical camera with a diameter of more than 2 meters and a satellite platform. Multiple supports must be used to complete the connection between the optical camera and the satellite platform. Moreover, with the increase in the volume and weight of the optical camera, 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 mechanisms of the satellite platform, and the electrical units will all be damaged. Summary of the Invention

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

[0005] To achieve the above object, the technical solution of the present invention is realized as follows:

[0006] A separation device between an optical camera and a satellite platform with low impact includes a controller and at least six separation supports. The at least six separation supports are evenly spaced along the circumferential direction of the outer envelope of the satellite platform and the optical camera. The at least six separation supports are divided into multiple groups of separation support groups, and the separation supports of each group of separation support groups are adjacent to the separation supports of at least one other group of separation support groups;

[0007] The separation support includes two supports that are connected and symmetrically arranged. One support is connected to the optical camera, and the other support is connected to the satellite platform; the support includes a housing, a support docking end, and an explosive bolt; the explosive bolt is connected to the support docking end and is located in the accommodation space formed by the support docking end and the housing;

[0008] 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 detonate at different times, and the explosive bolts of the same group of separation support groups detonate simultaneously.

[0009] Furthermore, the support includes a buffer assembly which is arranged in the accommodation space and located between the connection end of the housing and the explosive bolt; the connection end of the housing is used to connect to an optical camera or a satellite platform.

[0010] Furthermore, the buffer assembly includes an impact-reducing shim. The impact-reducing shim includes a shim flat portion and a plurality of buffer grooves arranged at intervals. The side wall of the buffer groove extends obliquely from the shim flat portion in a direction away from the explosive bolt and towards 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.

[0011] Furthermore, the shim flat portion is provided with multiple groups of stress groove groups which are arranged close to the buffer groove and at intervals along the radial direction of the buffer groove; one group of stress groove groups includes two stress grooves which are respectively arranged on the opposite side surfaces of the shim flat portion, and the stress grooves are recessed downward from one side surface of the shim flat portion and extend along the circumferential direction of the buffer groove.

[0012] Furthermore, the support further includes a combination trap which is arranged in the accommodation space and located between the connection end of the housing and the impact-reducing shim; the combination trap includes a flat portion and a plurality of taper grooves. The side wall of the taper groove extends obliquely from the flat portion in a direction away from the explosive bolt and away from the axis of the taper groove; the taper groove is provided with a second through hole for the bolt head of the explosive bolt to pass through.

[0013] Furthermore, in the axial direction of the taper groove, the ratio of the diameter difference between the opposite sides of the taper groove to the height of the taper groove is 1:15.

[0014] Furthermore, the upper surface of the impact-reducing shim abuts against the lower surface of the combination trap, and the second through hole is aligned with the first through hole.

[0015] Furthermore, the buffer assembly further includes an impact-reducing retaining ring which includes a central portion and an edge portion connected to the housing, 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.

[0016] Furthermore, the housing 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 connection end of the housing.

[0017] Furthermore, the buffer assembly is made of a metal material.

[0018] Compared with the prior art, the present invention can achieve the following beneficial effects:

[0019] A separation device between a low-impact optical camera and a satellite platform of the present invention creates at least six separation supports evenly spaced along the circumferential direction of the outer envelopes of the satellite platform and the optical camera. While achieving high-load and high-reliability connection between the optical camera and the satellite platform, by means of grouped detonation of multiple separation supports, that is, explosive bolts of different groups of separation supports detonate at different times, and explosive bolts of the same group of separation supports detonate simultaneously, and the combination of symmetric impact reduction of two explosive bolts in each separation support, the impact response can be reduced, greatly reducing the impact force of the explosion of the explosive bolts on the optical camera and the satellite platform, and reducing the impact response of the unlocking explosion of the separation supports on the optical elements of the optical camera and each single machine of the satellite platform. It can be widely applied to the design of multi-point connection structures of various large-aperture optical payloads and satellite platforms. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The drawings forming a part of the present invention are used to provide a further understanding of the present invention. The schematic embodiments and descriptions of the present invention are used to explain the present invention and do not constitute an improper limitation to the present invention. In the drawings:

[0021] Figure 1 is a schematic structural diagram of the separation device between a low-impact optical camera and a satellite platform according to an embodiment of the present invention in one direction;

[0022] Figure 2 is a schematic structural diagram of the separation device between a low-impact optical camera and a satellite platform according to an embodiment of the present invention in another direction;

[0023] Figure 3 is a schematic structural diagram of the separation support of the separation device between a low-impact optical camera and a satellite platform according to an embodiment of the present invention.

[0024] Description of the reference numerals:

[0025] 10. Separation device; 11. Separation support; 12. Separation support group; 13. Support; 14. Housing; 15. Support docking end; 16. Explosive bolt; 17. Accommodation space; 18. Buffer assembly; 19. Connection end; 20. Impact reduction shim; 21. Shim flat part; 22. Buffer groove; 23. Stress groove group; 24. Stress groove; 25. Combination trap; 26. Flat part; 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. Installation cover; 34. Detonating cord. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0026] In order to make the objectives, technical solutions and advantages of the present invention clearer and more understandable, the present invention will be 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 present invention and do not constitute a limitation to the present invention. Similar elements in different embodiments are labeled with related similar element numbers. In the following embodiments, many details are described to enable a better understanding of the present invention. 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 elements, materials, and methods. In some cases, some operations related to the present invention are not shown or described in the specification, in order to avoid the core part of the present invention being overwhelmed by excessive description. 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 based on the description in the specification and the general technical knowledge in the art.

[0027] It should be noted that, without conflict, the embodiments and features in the embodiments of the present invention can be combined with each other to form various embodiments. At the same time, the steps or actions in the method description can also be adjusted in the order that is obvious to those skilled in the art. Therefore, the various sequences in the specification and drawings are only for clearly describing a certain embodiment and do not mean that they are the necessary sequences, unless it is stated that a certain sequence must be followed.

[0028] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc. is based on the orientation or positional relationship shown in the accompanying drawings. It is only for the convenience of describing the present 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 to the present 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 quantity of the indicated technical features. Thus, the features defined with "first", "second", etc. may explicitly or implicitly include one or more of such features. In the description of the present invention, unless otherwise stated, the meaning of "a plurality" is two or more.

[0029] In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, the terms "installation", "connection", and "coupling" 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 directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

[0030] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0031] See Figure 1 、 Figure 2 and Figure 3 As shown, an embodiment of the present invention provides a separation device 10 between an optical camera and a satellite platform with low impact, 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. At least six separation supports 11 are evenly spaced along the circumferential direction of the outer envelope of the satellite platform and the optical camera. At least six separation supports 11 are divided into multiple groups of separation support groups 12. Among them, the number of separation supports 11 in multiple groups of separation support groups 12 can be the same or different. The separation supports 11 of each group of separation support groups 12 are adjacent to the separation supports 11 of at least one other group of separation support groups 12. In Figure 1 In the shown embodiment, the separation device 10 includes six separation supports 11. Six separation supports 11 are evenly spaced along the circumferential direction of the outer envelope of the satellite platform and the optical camera. Six separation supports 11 are divided into two groups of separation support groups 12, and each group of separation support groups 12 has three separation supports 11. One separation support 11 in one group of separation support groups 12 has separation supports 11 of the other group of separation support groups 12 arranged on its adjacent sides.

[0032] The separating support 11 includes two supports 13 that are connected and symmetrically arranged. One of the supports 13 is connected to the optical camera, and the other support 13 is connected to the satellite platform. The support 13 includes a housing 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 within the accommodation space 17 formed by the enclosure of the support docking end 15 and the housing 14. The support 13 includes the explosive bolt 16, and the two supports 13 are symmetrically arranged such that each separating support 11 is locked by two symmetric explosive bolts 16. The two explosive bolts 16 are in a symmetric series connection. Only by detonating one explosive bolt 16 can the locking between the two supports 13 be released, and thus the locking between the optical camera and the satellite platform can be released. In this way, it is easy to unlock, and the unlocking reliability is improved compared with the locking reliability of a single-shot explosive bolt 16 or a parallel-connected explosive bolt 16. Moreover, when the explosive bolt 16 explodes, the bolt head and the screw of the explosive bolt 16 will quickly separate at the separation pre-section A. At the same time, two symmetrically arranged explosive bolts 16 are used, and the two bolt heads of the two explosive bolts 16 will fly away in opposite directions under the action of the explosion force, and the impulses of the two screws of the two explosive bolts 16 will cancel each other out.

[0033] The controller is used to receive the detonation signal to activate the explosive bolt 16, so that the explosive bolts 16 of different groups of separating support groups 12 detonate at different times, and the explosive bolts 16 of the same group of separating support groups 12 detonate simultaneously. The controller is used to receive the detonation signal and send a trigger signal to the electric ignition device to activate the explosive bolt 16 through the detonating cord 34. In Figure 1 the illustrated embodiment, all the explosive bolts 16 of one group of separating support groups 12 can be detonated first, and then all the explosive bolts 16 of the other group of separating support groups 12 can be detonated. In this way, about 50% of the impact energy can be reduced.

[0034] A separating device 10 between an optical camera and a satellite platform with low impact of the present invention includes at least six separating supports 11 that are evenly spaced along the circumferential direction of the outer envelope of the satellite platform and the optical camera. While achieving high-load and high-reliability connection between the optical camera and the satellite platform, through the grouped detonation of multiple separating supports 11, that is, the explosive bolts 16 of different groups of separating support groups 12 detonate at different times, and the explosive bolts 16 of the same group of separating support groups 12 detonate simultaneously, and the combined method of symmetric impact reduction of two explosive bolts 16 in each separating support 11, the impact response can be reduced, and the explosion impact force of the explosive bolts 16 on the optical camera and the satellite platform can be greatly reduced. The impact response of the unlocking explosion of the separating support 11 on the optical elements of the optical camera and each single machine of the satellite platform can be reduced, and it can be widely applied to the design of multi-point connection structures of various large-aperture optical payloads and satellite platforms.

[0035] In one embodiment, the support 13 includes a buffer assembly 18. The buffer assembly 18 is disposed within the accommodation space 17 and is located between the connection end 19 of the housing 14 and the explosive bolt 16. The buffer assembly 18 can be fixedly connected to the inner wall of the housing 14 by bolts. When the explosive bolt 16 explodes, the buffer assembly 18 is on the flight path of the bolt head, which can reduce the impact response transmitted to the satellite platform and the optical camera. The connection end 19 of the housing 14 is used to connect to the optical camera or the satellite platform. The connection end 19 of the housing 14 of one of the supports 13 of the separation support 11 is connected to the optical camera, and the connection end 19 of the housing 14 of the other support 13 is connected to the satellite platform.

[0036] In one embodiment, the buffer assembly 18 includes an impact reduction flap 20. The impact reduction flap 20 includes a flap flat portion 21 and a plurality of buffer grooves 22 arranged at intervals. The side walls of the buffer grooves 22 extend obliquely from the flap flat portion 21 in a direction away from the explosive bolt 16 and toward 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 reduction flap 20, causing the impact reduction flap 20 to deform and absorb a part of the energy. The bolt head can pass through the first through hole 28 of the buffer groove 22 and fly in the direction of the connection end 19 of the housing 14. And the buffer groove 22 is arranged such 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, thus realizing the check valve function of the bolt head.

[0037] In one embodiment, the flap flat portion 21 is provided with multiple groups of stress groove groups 23. The multiple groups of stress groove groups 23 are arranged close to the buffer groove 22 and are arranged at intervals along the radial direction of the buffer groove 22. In this embodiment, the flap flat portion 21 is provided with three groups of stress groove groups 23. One group of stress groove groups 23 includes two stress grooves 24. The two stress grooves 24 are respectively arranged on the opposite side surfaces of the flap flat portion 21. The stress groove 24 is recessed downward from one side surface of the flap flat portion 21 and extends along the circumferential direction of the buffer groove 22. Thus, when the bolt head flying at high speed collides with the impact reduction flap 20, the impact reduction flap 20 can deform and absorb a part of the energy.

[0038] In one embodiment, the support 13 further includes a combined trap 25, where the combined trap 25 can be made of a metallic material such as aluminum, steel, titanium alloy, etc. The combined trap 25 is disposed within the accommodation space 17 and is located between the connection end 19 of the housing 14 and the shock-absorbing flap 20. The combined trap 25 includes a planar portion 26 and a plurality of tapered grooves 27. The side walls of the tapered grooves 27 extend obliquely from the planar portion 26 in a direction away from the explosive bolt 16 and away from the axis of the tapered grooves 27. The tapered grooves 27 are provided with second through holes 29 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 can pass through the second through holes 29 of the tapered grooves 27 and fly towards the connection 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 holes 29, thereby realizing the check valve function of the bolt head.

[0039] In one embodiment, the upper surface of the shock-absorbing flap 20 abuts against the lower surface of the combined trap 25, and the second through holes 29 are aligned with the first through holes 28.

[0040] In one embodiment, in the axial direction of the tapered grooves 27, the ratio of the diameter difference between the opposite sides of the tapered grooves 27 to the height of the tapered grooves 27 is 1:15. This can prevent the bolt head from returning to the side of the support docking end 15.

[0041] In one embodiment, the buffer assembly 18 further includes a shock-absorbing retaining ring 30. The shock-absorbing retaining ring 30 includes a central portion and an edge portion connected to the housing 14. The shock-absorbing retaining ring 30 extends arcuately from the edge portion to the central portion. Among them, the shock-absorbing retaining ring 30 extends arcuately from the edge portion to the central portion in a direction close to the combined trap 25. The shock-absorbing retaining ring 30 is provided with a plurality of third through holes 31 arranged at intervals. The combined trap 25 is disposed between the shock-absorbing flap 20 and the shock-absorbing retaining ring 30. After the explosive bolt 16 explodes and separates, the bolt head flying at high speed collides with the shock-absorbing retaining ring 30, causing the shock-absorbing retaining ring 30 to deform and absorb a part of the energy. The bolt head can pass through the third through holes 31 of the shock-absorbing retaining ring 30 and fly towards the connection end 19 of the housing 14, or can be restricted between the shock-absorbing retaining ring 30 and the combined trap 25.

[0042] In one embodiment, in the axial direction of the housing 14, the shock-absorbing flap 20, the combined trap 25, and the shock-absorbing retaining ring 30 are arranged in sequence.

[0043] In one embodiment, the housing 14 includes a shock-absorbing cover 32 and a mounting cover 33. The shock-absorbing cover 32 is made of a metallic material such as aluminum, steel, titanium alloy, etc. The shock-absorbing cover 32 is connected to the mounting cover 33, and the shock-absorbing cover 32 is located at the connecting end 19 of the housing 14. The bolt head flying at high speed after the explosive bolt 16 explodes and separates can collide with the shock-absorbing cover 32, causing the shock-absorbing cover 32 to deform and absorb a part of the energy, thereby greatly reducing the shock transmitted to the optical camera and / or the satellite platform.

[0044] In one embodiment, the buffer assembly 18 is made of a metallic material such as aluminum, steel, titanium alloy, etc. Among them, the materials of the shock-absorbing washer 20, the shock-absorbing snap ring 30, and the shock-absorbing cover 32 may be the same or different.

[0045] In Figure 3 In the illustrated embodiment, according to the flight trajectory of the bolt head after the explosive bolt 16 explodes and separates, a triple shock-absorbing structure is designed. The bolt head flying at high speed can sequentially pass through the shock-absorbing washer 20, the combined trap 25, the shock-absorbing snap ring 30, and the shock-absorbing cover 32. The bolt head flying at high speed can first pass through the shock-absorbing washer 20 and collide with the shock-absorbing washer 20, causing the shock-absorbing washer 20 to deform and absorb a part of the energy, and pass through the first through hole 28 and the second through hole 29, and fly towards the shock-absorbing snap ring 30. The bolt head passes through the shock-absorbing snap ring 30 and collides with the shock-absorbing snap ring 30, causing the shock-absorbing snap ring 30 to deform and absorb a part of the energy, and pass through the third through hole 31, and finally fly towards the shock-absorbing cover 32. The deformation of the shock-absorbing cover 32 can absorb a part of the energy again, thereby greatly reducing the shock response transmitted to the optical camera and the satellite platform. Through multiple tests, it can be obtained that the triple shock-absorbing structure can effectively reduce about 30% of the shock energy.

[0046] An optical camera and satellite platform separation device 10 with low shock provided by an embodiment of the present invention can effectively reduce about 80% of the shock energy, effectively ensuring the normal operation of the optical elements of the optical camera and each single machine of the satellite.

[0047] It should be understood that various forms of the processes shown above can be used, steps can be reordered, added, or deleted. For example, the steps recorded in the present invention disclosure can be executed in parallel, sequentially, or in a different order, as long as the desired results of the technical solution disclosed in the present invention can be achieved. No limitations are imposed herein.

[0048] The above specific embodiments do not constitute a limitation to the protection scope of the present invention. Those skilled in the art should understand that various modifications, combinations, sub-combinations, and substitutions can be made according to design requirements and other factors. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention shall be included within 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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