Belt-type satellite-rocket separation unlocking device

Abstract

The present application relates to a strap-type satellite-rocket separation unlocking device, comprising a satellite adapter, a carrier adapter and a plurality of straps, the carrier adapter is a truncated cone cylindrical structure, the satellite adapter is an annular structure and is assembled at the end of the carrier adapter with a smaller diameter, the outer peripheral wall of the satellite adapter is provided with a first fixing structure, a plurality of straps form a circular ring structure and are arranged around the circumference of the satellite adapter, a connecting portion is provided between adjacent straps, an unlocking assembly is provided on the connecting portion, a plurality of groups of elastic tensioning assemblies are arranged at intervals between the outer peripheral wall of the carrier adapter and the outer side of the strap, and a second fixing structure for pressing the first fixing structure onto the carrier adapter is provided on the inner side of the strap. The present application has the following expected technical effects: the coordination requirements of each component are reduced, the strap can still be smoothly unfolded under various failure modes, which is sufficient to meet the requirements of low impact, and it is not easy to get stuck, and it is not easy to cause satellite-rocket separation failure.

Description

Technical Field

[0001] The present application relates to the field of aerospace technology, and in particular to a belt-wrapped satellite-rocket separation and unlocking device. Background Art

[0002] The separation of satellite and rocket is the last step in the process of launching a satellite by a carrier rocket. Whether the separation is completed normally is directly related to the success or failure of the spacecraft launch. The satellite-rocket separation device is mainly used to connect the satellite and the rocket body structure, provide support for the satellite, bear the load transmitted by the satellite during the flight, and can achieve the separation of satellite and rocket, provide a separation speed that meets the requirements, and try not to affect the satellite attitude. Moreover, at present, the belt connection and separation mechanism has become the main satellite-rocket connection and separation mechanism for the world's carrier rockets.

[0003] A Chinese patent with application number CN201510143772.5 discloses a belt-type unlocking and separation device driven by an explosive bolt, including an explosive bolt, an upper support, a lower support, a left belt, a right belt, a belt connecting spring and an explosive bolt separation body collecting device; the left belt is in contact with and cooperates with the upper support and the lower support respectively, and the right belt is in contact with and cooperates with the upper support and the lower support respectively, and the contact points on both sides of the left belt and the right belt are fastened together by two parallel explosive bolts, the belt connecting spring is threadedly connected to the left belt and the right belt respectively, and a bolt separation body collecting device is fixedly connected to each end of the right belt.

[0004] With respect to the above-mentioned related technologies, the inventor believes that there are the following defects:

[0005] The coordination of various components is very demanding. It is difficult to smoothly unfold the straps under various failure modes. The low-impact requirements cannot be met and jamming is likely to occur, leading to failure of satellite-rocket separation. Therefore, there is room for improvement. Summary of the invention

[0006] The present application provides a strap-type satellite-rocket separation and unlocking device to improve the following technical problems: the conventional strap-type unlocking and separation device has very high requirements for the coordination of the various components, it is difficult to smoothly unfold the strap under various failure modes, it cannot meet the low-impact requirements, and it is easy to get stuck, which leads to the failure of satellite-rocket separation.

[0007] The present application provides a belt-wrapped satellite-rocket separation and unlocking device, which adopts the following technical solution:

[0008] A strap-type satellite-rocket separation and unlocking device comprises a satellite adapter, a carrier adapter and a plurality of straps, wherein the carrier adapter is a truncated cone cylindrical structure, the satellite adapter is an annular structure and is assembled on the end of the carrier adapter with a smaller diameter, the outer peripheral wall of the satellite adapter is provided with a first fixing structure, a plurality of straps form a circular ring structure and are arranged around the circumference of the satellite adapter, a connecting portion for tightening the two is provided between adjacent straps, an unlocking component for unlocking the tightened state of the connecting portion is provided on the connecting portion, a plurality of groups of elastic tensioning components are arranged at intervals between the outer peripheral wall of the carrier adapter and the outer side of the strap, and a second fixing structure for pressing the first fixing structure onto the carrier adapter is provided on the inner side of the strap.

[0009] By adopting the above technical solution, after the unlocking component starts the unlocking action, the tensioned state of the connecting part can be unlocked, thereby releasing the pre-tightening force between adjacent straps, that is, the circular ring structure formed by multiple straps no longer tightens the satellite adapter. At the same time, under the action of the elastic tensioning component, the strap expands outward to complete the unlocking process of the device, and the carrier adapter and the satellite adapter are separated under the action of other driving forces; the strap-type satellite-rocket separation unlocking device designed above has reduced coordination requirements for each component, and the strap can still be smoothly unfolded under various fault modes, which is sufficient to meet the low impact requirements, is not prone to jamming, and is not prone to satellite-rocket separation failure.

[0010] Optionally, the elastic tensioning assembly includes a bracket, a spring and a connecting piece, the bracket is detachably mounted on the outer peripheral wall of the carrying adapter, the connecting piece is fixed to the outer side of the strap, and both ends of the spring are respectively connected to the bracket and the connecting piece.

[0011] By adopting the above technical solution, the bracket and the connecting plate provide a firm installation position for the two ends of the spring, and the elastic restoring force of the spring can drive the strap to drive the first fixed structure to move toward the second fixed structure, and then press the second fixed structure to facilitate the firm connection between the satellite adapter and the carrier adapter. The entire elastic tensioning assembly has a simple structure and is easy to assemble and maintain.

[0012] Optionally, a mounting groove is provided on the outer peripheral wall of the transport adapter, and the bracket is fixed in the mounting groove by a plurality of screws.

[0013] By adopting the above technical solution, the mounting groove has the effect of properly hiding the bracket and the screws, and the above mounting method can realize the detachable assembly of the bracket.

[0014] Optionally, the connecting portion includes a housing, a first rotating shaft, a second rotating shaft, a third rotating shaft, a fourth rotating shaft, a first connecting rod and a second connecting rod, the housing is provided with a cavity, the housing is provided with a first arc-shaped slide groove for the second rotating shaft to rotate, the center of the first arc-shaped slide groove is on the rotation axis of the first rotating shaft, the housing is provided with a second arc-shaped slide groove for the fourth rotating shaft to rotate, the center of the second arc-shaped slide groove is on the rotation axis of the third rotating shaft;

[0015] The first rotating shaft and the second rotating shaft form a group and are both rotatably mounted on one end of the housing, the first rotating shaft and the second rotating shaft are arranged in parallel, and the second rotating shaft is connected to an end of the bag belt, and the first rotating shaft and the second rotating shaft are connected as a whole through the first connecting rod;

[0016] The third rotating shaft and the fourth rotating shaft form a group and are both rotatably mounted on the other end of the housing, the third rotating shaft and the fourth rotating shaft are arranged in parallel, and the fourth rotating shaft is connected to the end of another adjacent bag belt, and the third rotating shaft and the fourth rotating shaft are connected as a whole through the second connecting rod;

[0017] The unlocking assembly is mounted on the housing, a portion of the unlocking assembly is connected to the end of the strap (3) connected to the second rotating shaft, and a portion of the unlocking assembly is not connected to the end of the strap connected to the fourth rotating shaft.

[0018] By adopting the above technical solution, one end of the strap is movably connected to the shell through the first connecting rod, the first rotating shaft, and the second rotating shaft, and the other end of the strap is movably connected to the shell through the second connecting rod, the third rotating shaft, and the fourth rotating shaft, so that the strap and the shell can both rotate around the first rotating shaft or the third rotating shaft. At the same time, the design of the first arc-shaped slide groove and the second arc-shaped slide groove can be used to limit the rotation range of the second rotating shaft and the fourth rotating shaft, respectively, thereby effectively preventing the strap from moving without restriction after being unlocked.

[0019] Optionally, a first hole is provided at one end of the strap, and the second rotating shaft passes through the first hole; a second hole is provided at the other end of the strap, and the fourth rotating shaft passes through the second hole.

[0020] By adopting the above technical solution and in the above manner, one end of the strap can be rotatably and firmly connected to the second rotating shaft, and the other end of the strap can be rotatably and firmly connected to the fourth rotating shaft.

[0021] Optionally, the cross-section of the shell is U-shaped, and outlets for connecting the strap are provided at both ends of the shell, and the opening of the shell is arranged toward the inside.

[0022] By adopting the above technical solution, the shell of the above design is simple to manufacture, convenient for installing various components in the shell, and conducive to connecting with the end of the bag belt.

[0023] Optionally, two straps are provided, and each strap is connected to at least three groups of the elastic tensioning components.

[0024] By adopting the above technical solution, the number of wrapping straps can be minimized to control the production cost of the entire device. At the same time, at least six groups of elastic tensioning components are used in combination to provide a larger and more uniform and comprehensive tensioning force to ensure a firm connection between the satellite adapter and the carrier adapter.

[0025] Optionally, the unlocking assembly includes a bolt box and an explosive bolt, the bolt box is fixedly mounted on the connecting portion, and the explosive bolt is installed in the bolt box.

[0026] By adopting the above technical solution, the unlocking component designed above is a common accessory with mature technology on the market, with a simple structure, and is relatively simple to manufacture, purchase, install and replace.

[0027] Optionally, the first fixing structure is a circular ring.

[0028] By adopting the above technical solution, the first fixed structure designed above has a simple structure and low manufacturing cost.

[0029] Optionally, the second fixing structure is a plurality of spaced apart card blocks, and a card slot for the ring to be embedded is provided on a side of the card block away from the wrapping belt.

[0030] By adopting the above technical solution, the second fixing structure of the above design has a simple structure, low manufacturing cost, and good pressing effect on the ring.

[0031] In summary, the present application includes at least one of the following beneficial technical effects:

[0032] After the unlocking component starts the unlocking action, the tensioned state of the connection part can be unlocked, thereby releasing the pre-tightening force between adjacent straps, that is, the circular ring structure formed by multiple straps no longer tightens the satellite adapter. At the same time, under the action of the elastic tensioning component, the strap expands outward to complete the unlocking process of the device, and the carrier adapter and the satellite adapter are separated under the action of other driving forces; the strap-type satellite-rocket separation unlocking device designed above has reduced requirements for the coordination of various components, and the strap can still be smoothly unfolded under various fault modes, which is sufficient to meet the low-impact requirements, is not prone to jamming, and is not prone to satellite-rocket separation failure. It has the advantages of good stability and full use of space, which effectively guarantees the applicability and economy of the device. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0034] Figure 1 It is a structural schematic diagram of a belt-wrapped satellite-rocket separation and unlocking device according to an embodiment of the present application.

[0035] Figure 2 It is a schematic diagram of the connection relationship between the satellite adapter and the bag belt in the embodiment of the present application.

[0036] Figure 3 It is a schematic diagram of the connection relationship between the connecting portion and the end of the strap in the embodiment of the present application.

[0037] Description of reference numerals:

[0038] 1. Satellite adapter; 11. First fixed structure; 2. Carrier adapter; 21. Mounting slot; 3. Wrapping belt; 31. Block; 4. Connecting part; 41. Housing; 411. First arc-shaped slide groove; 412. Second arc-shaped slide groove; 42. First rotating shaft; 43. Second rotating shaft; 44. Third rotating shaft; 45. Fourth rotating shaft; 46. First connecting rod; 47. Second connecting rod; 5. Unlocking assembly; 51. Bolt box; 52. Explosive bolt; 6. Elastic tensioning assembly; 61. Bracket; 62. Spring; 63. Connecting piece. DETAILED DESCRIPTION

[0039] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present application more clearly understood, the present application is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application.

[0040] It should be noted that when an element is referred to as being "fixed to" or "disposed on" another element, it can be directly on the other element or indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or indirectly connected to the other element.

[0041] It should be understood that the terms "length", "width", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", 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 present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0042] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, the meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.

[0043] The following is combined with Figure 1-3 This application is described in further detail.

[0044] The present application embodiment discloses a belt-wrapped satellite-rocket separation and unlocking device. Figure 1 and Figure 2 The wrapping-belt type satellite-rocket separation and unlocking device comprises a satellite adapter 1, a carrier adapter 2 and a plurality of wrapping straps 3. The carrier adapter 2 is a truncated cone cylindrical structure. The satellite adapter 1 is an annular structure and is assembled at the end of the carrier adapter 2 with a smaller diameter. The outer peripheral wall of the satellite adapter 1 is provided with a first fixing structure 11. The plurality of wrapping straps 3 form a circular ring structure and are arranged around the circumference of the satellite adapter 1. A connecting portion 4 for tightening the two is provided between adjacent wrapping straps 3. An unlocking component 5 for unlocking the tightened state of the connecting portion 4 is provided on the connecting portion 4. A plurality of groups of elastic tensioning components 6 are arranged at intervals between the outer peripheral wall of the carrier adapter 2 and the outer side of the wrapping strap 3. A second fixing structure for pressing the first fixing structure 11 onto the carrier adapter 2 is provided on the inner side of the wrapping strap 3.

[0045] The elastic tensioning assembly 6 includes a bracket 61, a spring 62 and a connecting piece 63. The bracket 61 can be detachably assembled on the outer wall of the carrier adapter 2, the connecting piece 63 is fixed to the outer side of the strap 3, and the two ends of the spring 62 are respectively connected to the bracket 61 and the connecting piece 63.

[0046] By adopting the above technical solution, the bracket 61 and the connecting piece 63 provide a firm installation position for the two ends of the spring 62, and the elastic restoring force of the spring 62 can drive the strap 3 to drive the first fixed structure 11 to move toward the second fixed structure, and then press the second fixed structure to facilitate the firm connection between the satellite adapter 1 and the carrier adapter 2. The entire elastic tensioning assembly 6 has a simple structure and is easy to assemble and maintain.

[0047] The outer wall of the carrier adapter 2 is provided with a mounting groove 21, and the bracket 61 is fixed in the mounting groove 21 by a plurality of screws. The mounting groove 21 has the effect of appropriately hiding the bracket 61 and the screws. At the same time, the above-mentioned mounting method can realize the detachable assembly of the bracket 61.

[0048] Two wrapping straps 3 are provided, and each wrapping strap 3 is connected to at least three groups of elastic tensioning components 6 . In this embodiment, each wrapping strap 3 corresponds to five groups of elastic tensioning components 6 .

[0049] By adopting the above technical solution, the number of straps 3 can be reduced as much as possible to control the manufacturing cost of the entire device. At the same time, at least six groups of elastic tensioning components 6 are used in combination to provide a larger and more uniform and comprehensive tensioning force to ensure a firm connection between the satellite adapter 1 and the carrier adapter 2.

[0050] The first fixing structure 11 is a circular ring and is integrally formed on the outer peripheral wall of the satellite adapter 1 . The first fixing structure 11 designed as above has a simple structure and low manufacturing cost.

[0051] The second fixing structure is a plurality of spaced apart blocks 31, and a slot for the ring to be inserted is provided on the side of the block 31 away from the strap 3. The second fixing structure designed above is simple in structure, low in manufacturing cost, and has a good pressing effect on the ring.

[0052] Reference Figure 1 and Figure 3 The connecting part 4 includes a shell 41, a first rotating shaft 42, a second rotating shaft 43, a third rotating shaft 44, a fourth rotating shaft 45, a first connecting rod 46 and a second connecting rod 47. The shell 41 is arranged in a cavity. The shell 41 is provided with a first arc-shaped slide groove 411 for the second rotating shaft 43 to rotate. The center of the first arc-shaped slide groove 411 is on the rotation axis of the first rotating shaft 42. The shell 41 is provided with a second arc-shaped slide groove 412 for the fourth rotating shaft 45 to rotate. The center of the second arc-shaped slide groove 412 is on the rotation axis of the third rotating shaft 44.

[0053] The first rotating shaft 42 and the second rotating shaft 43 are a group and are both rotatably mounted on one end of the housing 41. The first rotating shaft 42 and the second rotating shaft 43 are arranged in parallel, and the second rotating shaft 43 is connected to the end of a packing belt 3. The first rotating shaft 42 and the second rotating shaft 43 are connected as a whole through a first connecting rod 46.

[0054] The third rotating shaft 44 and the fourth rotating shaft 45 are a group and are both rotatably mounted on the other end of the housing 41. The third rotating shaft 44 and the fourth rotating shaft 45 are arranged in parallel, and the fourth rotating shaft 45 is connected to the end of another adjacent wrapping belt 3. The third rotating shaft 44 and the fourth rotating shaft 45 are connected as a whole through a second connecting rod 47.

[0055] The unlocking assembly 5 is installed on the housing 41 , and a part of the unlocking assembly 5 is connected to the end of the strap 3 connected to the second shaft 43 , and a part of the unlocking assembly 5 is not connected to the end of the strap 3 connected to the fourth shaft 45 .

[0056] By adopting the above technical solution, one end of the strap 3 is movably connected to the shell 41 through the first connecting rod 46, the first rotating shaft 42, and the second rotating shaft 43, and the other end of the strap 3 is movably connected to the shell 41 through the second connecting rod 47, the third rotating shaft 44, and the fourth rotating shaft 45, so that the strap 3 and the shell 41 can both rotate around the first rotating shaft 42 or the third rotating shaft 44. At the same time, the design of the first arc-shaped slide groove 411 and the second arc-shaped slide groove 412 can be used to limit the rotation range of the second rotating shaft 43 and the fourth rotating shaft 45, respectively, thereby effectively preventing the strap 3 from moving without restriction after being unlocked.

[0057] One end of the wrapping belt 3 is provided with a first hole, and the second rotating shaft 43 passes through the first hole; the other end of the wrapping belt 3 is provided with a second hole, and the fourth rotating shaft 45 passes through the second hole.

[0058] By adopting the above technical solution and in the above manner, one end of the strap 3 can be rotatably and firmly connected to the second rotating shaft 43 , and the other end of the strap 3 can be rotatably and firmly connected to the fourth rotating shaft 45 .

[0059] The cross-section of the shell 41 is U-shaped, and outlets for connecting the strap 3 are provided at both ends of the shell 41. The opening of the shell 41 is arranged toward the inside. The shell 41 designed as above is simple to manufacture, convenient for installation of various components in the shell 41, and conducive to connection with the end of the strap 3.

[0060] The unlocking assembly 5 includes a bolt box 51 and an explosive bolt 52. The bolt box 51 is fixedly mounted on the connecting part 4, and the explosive bolt 52 is installed in the bolt box 51. One end of the wrapping tape 3 is provided with a socket for inserting the explosive bolt 52. The unlocking assembly 5 designed above is a common accessory with mature technology on the market, with a simple structure, and is relatively simple to manufacture, purchase, install and replace.

[0061] The working principle of a belt-wrapped satellite-rocket separation and unlocking device in the embodiment of the present application is as follows:

[0062] After the unlocking component 5 starts the unlocking action, the tensioned state of the connecting part 4 can be unlocked, thereby releasing the pre-tightening force between adjacent straps 3, that is, the circular ring structure formed by multiple straps 3 no longer tightens the satellite adapter 1. At the same time, under the action of the elastic tensioning component 6, the strap 3 expands outward to complete the unlocking process of the device. The carrier adapter 2 and the satellite adapter 1 are separated under the action of other driving forces.

[0063] The beneficial technical effects of the belt-wrapped satellite-rocket separation and unlocking device according to the embodiment of the present application are as follows:

[0064] The strap-type satellite-rocket separation and unlocking device designed above has lower requirements for the coordination of various components. The strap 3 can still be smoothly unfolded under various fault modes, which is sufficient to meet the low-impact requirements, is not prone to jamming, and is not prone to satellite-rocket separation failure. It has the advantages of good stability and full use of space, which effectively guarantees the applicability and economy of the device.

[0065] The above description is only a preferred embodiment of the present application and is not intended to limit the present application. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the application should be included in the protection scope of the present application.

Claims

1. A belt-wrapped satellite-rocket separation and unlocking device, characterized in that: The invention comprises a satellite adapter (1), a carrier adapter (2) and a plurality of straps (3), wherein the carrier adapter (2) is a truncated cone cylindrical structure, the satellite adapter (1) is an annular structure and is mounted on the end of the carrier adapter (2) with a smaller diameter, the outer peripheral wall of the satellite adapter (1) is provided with a first fixing structure (11), the plurality of straps (3) form a circular ring structure and are arranged around the circumference of the satellite adapter (1), a connecting portion (4) for tightening the two is provided between adjacent straps (3), an unlocking component (5) for unlocking the tightened state of the connecting portion (4) is provided on the connecting portion (4), a plurality of groups of elastic tensioning components (6) are arranged at intervals between the outer peripheral wall of the carrier adapter (2) and the outer side of the strap (3), and a second fixing structure for pressing the first fixing structure (11) onto the carrier adapter (2) is provided on the inner side of the strap (3); The connecting portion (4) comprises a housing (41), a first rotating shaft (42), a second rotating shaft (43), a third rotating shaft (44), a fourth rotating shaft (45), a first connecting rod (46) and a second connecting rod (47); a cavity is arranged in the housing (41); a first arc-shaped sliding groove (411) for the second rotating shaft (43) to rotate is arranged on the housing (41); the center of the first arc-shaped sliding groove (411) is on the rotating axis of the first rotating shaft (42); a second arc-shaped sliding groove (412) for the fourth rotating shaft (45) to rotate is arranged on the housing (41); the center of the second arc-shaped sliding groove (412) is on the rotating axis of the third rotating shaft (44); The first rotating shaft (42) and the second rotating shaft (43) form a group and are both rotatably mounted on one end of the housing (41); the first rotating shaft (42) and the second rotating shaft (43) are arranged in parallel, and the second rotating shaft (43) is connected to an end of the strap (3); the first rotating shaft (42) and the second rotating shaft (43) are connected as a whole via the first connecting rod (46); The third rotating shaft (44) and the fourth rotating shaft (45) form a group and are both rotatably mounted on the other end of the housing (41). The third rotating shaft (44) and the fourth rotating shaft (45) are arranged in parallel, and the fourth rotating shaft (45) is connected to the end of another adjacent wrapping belt (3). The third rotating shaft (44) and the fourth rotating shaft (45) are connected as a whole via the second connecting rod (47). The unlocking component (5) is mounted on the housing (41), a portion of the unlocking component (5) is connected to the end of the strap (3) connected to the second rotating shaft (43), and a portion of the unlocking component (5) is not connected to the end of the strap (3) connected to the fourth rotating shaft (45).

2. The belt-wrapped satellite-rocket separation and unlocking device according to claim 1, characterized in that: The elastic tensioning assembly (6) includes a bracket (61), a spring (62) and a connecting piece (63); the bracket (61) can be detachably assembled on the outer peripheral wall of the carrying adapter (2); the connecting piece (63) is fixed to the outer side of the strap (3); and the two ends of the spring (62) are respectively connected to the bracket (61) and the connecting piece (63).

3. The belt-wrapped satellite-rocket separation and unlocking device according to claim 2, characterized in that: The outer peripheral wall of the transport adapter (2) is provided with a mounting groove (21), and the bracket (61) is fixed in the mounting groove (21) by means of a plurality of screws.

4. The belt-wrapped satellite-rocket separation and unlocking device according to claim 1, characterized in that: One end of the wrapping belt (3) is provided with a first hole, and the second rotating shaft (43) passes through the first hole; the other end of the wrapping belt (3) is provided with a second hole, and the fourth rotating shaft (45) passes through the second hole.

5. The belt-wrapped satellite-rocket separation and unlocking device according to claim 1, characterized in that: The cross section of the shell (41) is U-shaped, and outlets for connecting the wrapping belt (3) are arranged at both ends of the shell (41), and the opening of the shell (41) is arranged toward the inside.

6. The belt-wrapped satellite-rocket separation and unlocking device according to claim 1, characterized in that: Two of the wrapping belts (3) are provided, and each of the wrapping belts (3) is connected to at least three groups of the elastic tensioning components (6).

7. The belt-wrapped satellite-rocket separation and unlocking device according to claim 1, characterized in that: The unlocking assembly (5) comprises a bolt box (51) and an explosive bolt (52); the bolt box (51) is fixedly mounted on the connecting portion (4); and the explosive bolt (52) is mounted in the bolt box (51).

8. The belt-wrapped satellite-rocket separation and unlocking device according to claim 1, characterized in that: The first fixing structure (11) is a circular ring.

9. The belt-wrapped satellite-rocket separation and unlocking device according to claim 8, characterized in that: The second fixing structure is a plurality of spaced apart clamping blocks (31), and a clamping groove for the ring to be embedded is provided on a side of the clamping block (31) away from the wrapping belt (3).

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