Spherical column type non-pyrotechnic pneumatic separating and unlocking device of carrier rocket

Abstract

The invention provides a sphere-column-type non-firework pneumatic separation unlocking device of a carrier rocket, which comprises a gas path piece of an annular structure, and a plurality of limiting holes are formed in the inner wall of the gas path piece; the inflation end cover is detachably connected with the upper portion of the air path piece, and an inflation inlet is formed in the center of the inflation end cover. The first ends of the plurality of thrust rods are connected with the separation body, and the second ends of the plurality of thrust rods are connected with the gas path piece in a sliding manner; the first end of the locking stud penetrates through the through hole of the separation body and the through hole of the body, a sliding cavity is formed in the locking stud, and a plurality of limiting cavities are formed in the outer side of the first end of the locking stud in a penetrating mode; the multiple ball columns are arranged in the multiple limiting cavities in a sliding mode, and the outer ends of the multiple ball columns are matched with the multiple limiting holes. The check block is arranged in the sliding cavity in a sliding mode, and a reset spring is arranged between the check block and the inner bottom face of the sliding cavity. According to the scheme, separation and unlocking of the separation body and the cup body can be achieved in a pneumatic driving mode, damage to the separation and unlocking device and the separation body cannot be caused, and reutilization is facilitated.

Description

Technical Field

[0001] This invention relates to the field of launch vehicle technology, and in particular to a spherical-type non-pyrotechnic aerodynamic separation and unlocking device for launch vehicles. Background Technology

[0002] Separation and unlocking devices are key mechanisms in rockets, missiles, and spacecraft, responsible for connecting, unlocking, and separating components. They are an essential part of the spacecraft structure. Through programmed control, they jettison discarded components (such as boosters and fairings) to achieve safe separation, ensuring the separated parts reach a predetermined velocity without the risk of collision.

[0003] However, current pyrotechnic separation and unlocking devices generate a large impact force during separation, which can easily damage the separating components and the main body. Furthermore, the separation and unlocking device is damaged during separation and cannot be reused. Summary of the Invention

[0004] This invention provides a spherical non-pyrotechnic pneumatic separation and unlocking device for launch vehicles, which can achieve separation and unlocking of the separation body and the cup body through pneumatic drive, without causing damage to the separation and unlocking device or the separation body, and is conducive to reuse.

[0005] To solve the above-mentioned technical problems, the technical solution of the present invention is as follows: A spherical-type non-pyrotechnic aerodynamic separation and unlocking device for a launch vehicle includes: The gas passage component has an annular structure, and the inner wall of the gas passage component is formed with multiple limiting holes. The multiple limiting holes have a hemispherical structure and are evenly distributed around the axis of the gas passage component. An inflatable end cap is detachably connected to the upper part of the air circuit component. An inflation port is provided in the center of the inflatable end cap. The inflation port is connected to the inner cavity of the air circuit component. The inflation port is connected to the air supply device through an air pipe. Multiple thrust rods, with the first end of each thrust rod connected to the separator and the second end of each thrust rod slidably connected to the pneumatic component; A locking stud has a first end that penetrates the through hole of the separator and the main body, and the first end of the locking stud slides in fit with the inner cavity of the air passage component. The locking stud has a sliding cavity inside, which penetrates the end face of the first end of the locking stud. Multiple limiting cavities are provided on the outer side of the first end of the locking stud. The multiple limiting cavities are radially distributed along the locking stud and communicate with the sliding cavity. The second end of the locking stud is threaded with a locking nut, which abuts against the main body. Multiple ball columns are slidably arranged in multiple limiting cavities. The outer ends of the ball columns are hemispherical and are adapted to multiple limiting holes. A stop block is slidably disposed within the sliding cavity, and a return spring is provided between the stop block and the inner bottom surface of the sliding cavity.

[0006] Optionally, the spherical-type non-pyrotechnic aerodynamic separation and unlocking device of the launch vehicle further includes: Connecting ring, the connecting ring being formed on the bottom surface of the inflatable end cap; A connecting boss is formed on the upper surface of the gas passage component, and the connecting ring is threadedly connected to the connecting boss. The first sealing ring is embedded in the first annular groove on the surface of the connecting boss, and the first sealing ring is in close contact with the bottom surface of the inflatable end cap.

[0007] Optional, multiple thrust rods include: A limiting ring is disposed at the bottom end of the guide cavity on the bottom surface of the air passage component; A sliding block, which is slidably disposed within the guide cavity; The rod body is integrally formed with the sliding block, the end of the rod body passes through the limiting ring, and the end of the rod body is connected to the separating body.

[0008] Optionally, the spherical-type non-pyrotechnic aerodynamic separation and unlocking device of the launch vehicle further includes: Multiple air passages, the first end of each of the multiple air passages is connected to the inner cavity of the air passage component, and the second end of each of the multiple air passages is connected to the inner cavity of each of the multiple guide cavities away from the limiting ring. The fourth sealing ring is embedded in the fourth annular groove on the outside of the sliding block, and the fourth sealing ring is in close contact with the inner wall of the guide cavity.

[0009] Optionally, the spherical-type non-pyrotechnic aerodynamic separation and unlocking device of the launch vehicle further includes: Multiple second sealing rings are respectively embedded in multiple second annular grooves on the inner wall of the gas passage component, and the multiple second sealing rings are distributed on both sides of multiple limiting holes.

[0010] Optionally, the spherical-type non-pyrotechnic aerodynamic separation and unlocking device of the launch vehicle further includes: Multiple third sealing rings are embedded in multiple third annular grooves on the outer side of the stop block. The multiple third sealing rings are in close contact with the inner wall of the sliding cavity and are located near both ends of the stop block.

[0011] Optionally, the spherical-type non-pyrotechnic aerodynamic separation and unlocking device of the launch vehicle further includes: A positioning cavity is disposed inside the stop block, and the positioning cavity extends through the side of the stop block that contacts the return spring; A guide rod is disposed within the sliding cavity, and the guide rod slides in conjunction with the positioning cavity.

[0012] Optionally, the bottom surface of the inflatable end cap is formed with a convex ring, and when the return spring supports the stop block and contacts the convex ring, the end of the guide rod is located in the positioning cavity.

[0013] Optionally, the sum of the radius of the limiting hole and the length of the limiting cavity is equal to the length of the ball column.

[0014] The above-described solution of the present invention has at least the following beneficial effects: The above-described solution of the present invention can achieve separation and unlocking of the separator and the cup body through pneumatic drive, without causing damage to the separation and unlocking device and the separator, and is conducive to reuse. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the locked state of the spherical non-pyrotechnic aerodynamic separation and unlocking device of the launch vehicle provided in the embodiment of the present invention; Figure 2 This is a schematic diagram of the unlocking state of the spherical non-pyrotechnic aerodynamic separation and unlocking device for a launch vehicle provided in an embodiment of the present invention; Figure 3 This is a schematic diagram of the pneumatic components in the spherical non-pyrotechnic pneumatic separation and unlocking device for a launch vehicle provided in an embodiment of the present invention; Figure 4 This is a schematic diagram of the locking bolt in the spherical non-pyrotechnic pneumatic separation and unlocking device of a launch vehicle provided in an embodiment of the present invention.

[0016] Explanation of reference numerals in the attached figures: 1. Locking nut; 2. Inflation end cap; 21. Inflation port; 22. Connecting ring; 23. Protruding ring; 3. Air passage component; 31. Connecting boss; 32. First sealing ring; 33. Air passage; 34. Guide cavity; 35. Second sealing ring; 36. Limiting hole; 4. Locking stud; 41. Sliding cavity; 42. Limiting cavity; 5. Stop block; 51. Positioning cavity; 52. Third sealing ring; 6. Guide rod; 7. Return spring; 8. Ball column; 9. Thrust rod; 91. Limiting ring; 92. Rod body; 93. Sliding block; 94. Fourth sealing ring; 10. Separator; 11. Main body. Detailed Implementation

[0017] Exemplary embodiments of the invention will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the invention are shown in the drawings, it should be understood that the invention may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this invention will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

[0018] like Figures 1 to 4 As shown, an embodiment of the present invention proposes a spherical-type non-pyrotechnic aerodynamic separation and unlocking device for a launch vehicle, comprising: The air passage component 3 has an annular structure. The inner wall of the air passage component 3 is formed with multiple limiting holes 36. The multiple limiting holes 36 have a hemispherical structure and are evenly distributed around the axis of the air passage component 3. Inflatable end cap 2 is detachably connected to the upper part of air passage component 3. Inflatable end cap 2 has an inflation port 21 at its center. The inflation port 21 is connected to the inner cavity of air passage component 3. The inflation port 21 is connected to the air supply device through an air pipe. Multiple thrust rods 9, the first end of the multiple thrust rods 9 is connected to the separator 10, and the second end of the multiple thrust rods 9 is slidably connected to the air passage component 3; The locking stud 4 has its first end passing through the through hole of the separator 10 and the main body 11, and the first end of the locking stud 4 slides in the inner cavity of the air passage component 3. The locking stud 4 has a sliding cavity 41 inside, which passes through the end face of the first end of the locking stud 4. Multiple limiting cavities 42 are provided on the outer side of the first end of the locking stud 4. The multiple limiting cavities 42 are distributed radially along the locking stud 4 and are connected to the sliding cavity 41. The second end of the locking stud 4 is threadedly connected to a locking nut 1, which abuts against the main body 11. Multiple ball columns 8 are slidably disposed within multiple limiting cavities 42. The outer ends of the multiple ball columns 8 are hemispherical and are adapted to multiple limiting holes 36. The stop block 5 is slidably disposed in the sliding cavity 41, and a return spring 7 is provided between the stop block 5 and the inner bottom surface of the sliding cavity 41.

[0019] In this embodiment, during connection, the separator 10 is fitted to the body 11, the air passage 3 is coaxially arranged with the through holes of the separator 10 and the body 11, the locking nut 1 is screwed onto the second end of the locking bolt, pressure is applied to the stop block 5, causing the return spring 7 to contract, and the stop block 5 to slide into the sliding cavity 41, exposing multiple limiting cavities 42. Multiple ball columns 8 are placed in the multiple limiting cavities 42 respectively, with the outer ends of the multiple ball columns 8 completely entering the multiple limiting cavities 42 and the inner ends of the multiple ball columns 8 entering the sliding cavity 41. The pressure on the stop block 5 is released, the return spring 7 supports the stop block 5, the stop block 5 abuts against the inner ends of the multiple ball columns 8, and the first end of the locking stud 4 penetrates through the separator 10 and the body 11. A through hole is formed, and the first end of the locking stud 4 extends into the inner cavity of the air passage component 3. The locking nut 1 fits against the body 11, and multiple ball studs 8 correspond to multiple limiting holes 36 respectively. Pushing the inner ends of the multiple ball studs 8 causes the outer ends of the multiple ball studs 8 to be inserted into the multiple limiting holes 36 respectively. The return spring 7 supports the stop block 5, causing the stop block 5 to abut against the inner ends of the multiple ball studs 8, thereby limiting and fixing the outer ends of the multiple ball studs 8 in the multiple limiting holes 36, thus fixing the locking stud 4 and connecting the separator 10 and the body 11. The inflation end cap 2 is connected to the air passage component 3, and the inflation port 21 is connected to the inner cavity of the air passage component 3. The inflation port 21 is connected to the air supply device arranged on the body 11 through the air pipe. Figure 1 As shown; When separation of the separator 10 from the main body 11 is required, the solenoid valve of the air supply device opens, injecting gas with a preset pressure value into the inner cavity of the air passage component 3 through the air pipe and the air inlet 21. The gas pressure applies pressure to the stop block 5, causing the return spring 7 to contract. The stop block 5 slides into the sliding cavity 41 until the stop block 5 is completely disengaged from the inner ends of the multiple ball joints 8. When the return spring 7 is contracted to its shortest state, the air pressure acts on the air inlet cap 2, causing the air inlet cap 2 to move the air passage component 3 away from the separator 10. Multiple push rods 9 are slidably connected to the air passage component 3, providing limiting guidance. As the air passage component 3 moves away from the separator 10, multiple limiting holes 36 apply force to the multiple ball joints 8, causing the multiple ball joints 8 to slide along multiple limiting cavities 42 until the outer ends of the multiple ball joints 8 are completely inside the multiple limiting cavities 42, releasing the locking screw 4. Figure 2 As shown, under the action of air pressure, the locking stud 4 slides away from the air passage 3 until the first end of the locking stud 4 is completely separated from the through hole of the separator 10 and the body 11, thereby releasing the connection between the separator 10 and the body 11, which facilitates the separation of the separator 10 and the body 11. The entire separation and unlocking process is achieved by using pneumatic drive to separate and unlock the separator 10 from the cup body, which will not cause damage to the separation and unlocking device or the separator 10, and is conducive to reuse.

[0020] In this embodiment, the main body 11 is the main body of the launch vehicle, and the separation body 10 can be a booster, fairing, etc.; the gas supply device is installed on the main body 11.

[0021] This embodiment uses high-pressure gas controlled by a solenoid valve or an electro-explosive valve as a power source for separation and unlocking. In specific applications, the power source can include, but is not limited to, chemical energy generated by a gas generator, mechanical energy generated by a shape memory alloy, and high-pressure gas controlled by a solenoid valve or an electro-explosive valve. For example, the power source can be chemical energy generated by a gas generator. The gas generator is connected to the inflation port 21, and the chemical energy generated by the gas generator acts on the stop block 5, causing the stop block 5 to slide inside the sliding cavity 41, thereby realizing the separation and unlocking process. Alternatively, the power source can be mechanical energy generated by a shape memory alloy. The mechanical energy output end of the shape memory alloy device is inserted into the inflation port 21, and the mechanical energy output end abuts against the stop block 5. The mechanical energy of the shape memory alloy device drives the stop block 5 to slide inside the sliding cavity 41, thereby realizing the separation and unlocking process.

[0022] like Figure 1 and Figure 3 As shown, in an optional embodiment of the present invention, the spherical non-pyrotechnic aerodynamic separation and unlocking device of the launch vehicle further includes: Connecting ring 22 is formed on the bottom surface of the inflatable end cap 2; Connecting boss 31 is formed on the upper surface of air passage component 3, and connecting ring 22 is threadedly connected to connecting boss 31. The first sealing ring 32 is embedded in the first annular groove on the surface of the connecting boss 31, and the first sealing ring 32 is in close contact with the bottom surface of the inflatable end cap 2.

[0023] In this embodiment, the threaded connection between the connecting ring 22 and the connecting boss 31 facilitates the detachable connection between the inflatable end cap 2 and the air passage component 3. By setting the first sealing ring 32 on the surface of the connecting boss 31, the connection between the inflatable end cap 2 and the air passage component 3 can be sealed to prevent air leakage and ensure smooth separation and unlocking.

[0024] like Figure 3 As shown, in an optional embodiment of the present invention, the plurality of thrust rods 9 include: Limiting ring 91 is located at the bottom end of guide cavity 34 on the bottom surface of air passage component 3; Sliding block 93 is slidably disposed within guide cavity 34; The rod 92 is integrally formed with the sliding block 93. The end of the rod 92 passes through the limiting ring 91 and is connected to the separator 10.

[0025] In this embodiment, the sliding block 93 is limited by the limiting ring 91 to prevent the sliding block 93 from disengaging from the guide cavity 34. Through the sliding engagement of the sliding block 93 and the guide cavity 34, the thrust rod 9 and the air passage component 3 are slidably connected. The end of the rod body 92 is connected to the separator 10, thereby realizing the connection between the air passage component 3 and the separator 10, which facilitates the reuse of the air passage component 3 and the separator 10.

[0026] like Figure 1 and Figure 3 As shown, in an optional embodiment of the present invention, the spherical non-pyrotechnic aerodynamic separation and unlocking device of the launch vehicle further includes: Multiple air passages 33, the first end of each of the multiple air passages 33 is connected to the inner cavity of the air passage component 3, and the second end of each of the multiple air passages 33 is connected to the inner cavity of the multiple guide cavities 34 away from the limiting ring 91. The fourth sealing ring 94 is embedded in the fourth annular groove on the outside of the sliding block 93, and the fourth sealing ring 94 is in close contact with the inner wall of the guide cavity 34.

[0027] In this embodiment, gas enters multiple guide cavities 34 through multiple air passages 33 and acts on multiple thrust rods 9, which can accelerate the relative sliding distance between the air passage component 3 and the multiple thrust rods 9, and help to speed up the separation and unlocking process; by setting a fourth sealing ring 94, the sealing between the sliding block 93 and the guide cavity 34 can be improved to avoid air leakage.

[0028] like Figure 1 and Figure 3 As shown, in an optional embodiment of the present invention, the spherical non-pyrotechnic aerodynamic separation and unlocking device of the launch vehicle further includes: Multiple second sealing rings 35 are respectively embedded in multiple second annular grooves on the inner wall of the gas passage component 3, and the multiple second sealing rings 35 are distributed on both sides of multiple limiting holes 36.

[0029] In this embodiment, by providing multiple second sealing rings 35 on the inner wall of the gas passage component 3, the sealing between the locking stud 4 and the gas passage component 3 can be improved, preventing air leakage and ensuring that the gas pressure can fully act on the stop block 5 and the locking stud 4, ensuring that separation and unlocking can proceed smoothly.

[0030] like Figure 2 and Figure 4 As shown, in an optional embodiment of the present invention, the spherical non-pyrotechnic aerodynamic separation and unlocking device of the launch vehicle further includes: Multiple third sealing rings 52 are embedded in multiple third annular grooves on the outer side of the stop block 5. The multiple third sealing rings 52 are in close contact with the inner wall of the sliding cavity 41. The multiple third sealing rings 52 are close to both ends of the stop block 5.

[0031] In this embodiment, by providing multiple third sealing rings 52 on the outside of the stop 5, the sealing between the stop 5 and the sliding cavity 41 can be improved, preventing air leakage and ensuring that the gas pressure can fully act on the stop 5, thus ensuring smooth separation and unlocking.

[0032] like Figure 1 , Figure 2 and Figure 4 As shown, in an optional embodiment of the present invention, the spherical non-pyrotechnic aerodynamic separation and unlocking device of the launch vehicle further includes: The positioning cavity 51 is located inside the stop block 5 and extends through the side of the stop block 5 that contacts the return spring 7. Guide rod 6 is disposed in sliding cavity 41 and slides with positioning cavity 51.

[0033] In this embodiment, the guide rod 6 and the positioning cavity 51 can slide together to limit and guide the stop block 5, ensuring that the stop block 5 slides accurately and that the separation and unlocking are carried out smoothly.

[0034] like Figure 1 As shown, in an optional embodiment of the present invention, the bottom surface of the inflatable end cap 2 is formed with a protruding ring 23. When the return spring 7 supports the stop block 5 and contacts the protruding ring 23, the end of the guide rod 6 is located in the positioning cavity 51.

[0035] In this embodiment, the protruding ring 23 allows for movement between the inflation end cap 2 and the locking stud 4, facilitating the entry of gas into the inner cavity of the gas passage component 3 and into multiple guide cavities 34 through multiple air passages 33, ensuring smooth separation and unlocking. The protruding ring 23 limits the stop block 5, ensuring that when the return spring 7 supports the stop block 5 and contacts the protruding ring 23, the end of the guide rod 6 is located in the sliding cavity 41, preventing the guide rod 6 from disengaging from the positioning cavity 51. This ensures that the guide rod 6 and the positioning cavity 51 can limit and guide the stop block 5, ensuring accurate sliding of the stop block 5 and smooth separation and unlocking.

[0036] like Figure 1 As shown, in an optional embodiment of the present invention, the sum of the radius of the limiting hole 36 and the length of the limiting cavity 42 is equal to the length of the ball column 8.

[0037] In this embodiment, the sum of the radius of the limiting hole 36 and the length of the limiting cavity 42 is equal to the length of the ball post 8, so that when the outer ends of the multiple ball posts 8 are fully inserted into the multiple limiting holes 36, the stop block 5 contacts the inner ends of the multiple ball posts 8. The stop block 5 limits the multiple ball posts 8, ensuring that the outer ends of the multiple ball posts 8 are fully and accurately in contact with the multiple limiting holes 36, thus ensuring the locking effect of the multiple ball posts 8 on the locking stud 4.

[0038] The ball-and-cylinder type non-pyrotechnic pneumatic separation and unlocking device for a launch vehicle provided in the above embodiments of the present invention, through the opening of the solenoid valve of the gas supply device, injects gas with a preset pressure value into the inner cavity of the gas passage component 3 through the gas pipe and the gas inlet 21. The pressure of the gas applies pressure to the stop block 5, causing the return spring 7 to contract. The stop block 5 slides into the sliding cavity 41 until the stop block 5 is completely separated from the inner ends of the multiple ball columns 8. When the return spring 7 is contracted to its shortest state, the gas pressure acts on the gas inlet cap 2, causing the gas inlet cap 2 to drive the gas passage component 3 away from the separation body 10. Through the sliding connection of multiple thrust rods 9 with the gas passage component 3, the gas passage component 3 is limited and guided. When the gas passage component 3 is away from the separation body 10, multiple limiting holes 36 apply force to the multiple ball columns 8, causing the multiple ball columns 8 to slide along multiple limiting cavities 42 until the outer ends of the multiple ball columns 8 are completely entered into the multiple limiting cavities 42, releasing the locking and fixing of the locking stud 4. Figure 2 As shown, under the action of air pressure, the locking stud 4 slides away from the air passage component 3 until the first end of the locking stud 4 is completely disengaged from the through hole of the separator 10 and the body 11, thereby releasing the connection between the separator 10 and the body 11, facilitating the separation of the separator 10 from the body 11; the separation and unlocking of the separator 10 from the cup can be achieved by pneumatic drive, without causing damage to the separation and unlocking device or the separator 10, which is conducive to reuse; sealant is applied to the threaded connection between the connecting ring 22 and the connecting boss 31 to ensure the confidentiality of the connection between the connecting ring 22 and the connecting boss 31. The first sealing ring 32 ensures the sealing of the connection between the inflation end cap 2 and the air passage component 3. Multiple second sealing rings 35 improve the sealing between the locking stud 4 and the air passage component 3. Multiple third sealing rings 52 improve the sealing between the stop block 5 and the sliding cavity 41. The fourth sealing ring 94 improves the sealing between the sliding block 93 and the guide cavity 34. Thus, a sealed cavity is formed inside the ball-and-cylinder type non-pyrotechnic pneumatic separation and unlocking device of the launch vehicle. There is only one power source inlet, the inflation port 21, which ensures that the power source can accurately and fully act on the stop block 51 and ensures that the separation and unlocking process proceeds smoothly.

[0039] The above description represents the preferred embodiments of the present invention. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A spherical-type non-pyrotechnic aerodynamic separation and unlocking device for a launch vehicle, characterized in that, include: The gas passage component (3) has an annular structure. The inner wall of the gas passage component (3) is formed with multiple limiting holes (36). The multiple limiting holes (36) have a hemispherical structure and are evenly distributed around the axis of the gas passage component (3). An inflation end cap (2) is detachably connected to the upper part of the air passage component (3). An inflation port (21) is provided in the center of the inflation end cap (2). The inflation port (21) is connected to the inner cavity of the air passage component (3). The inflation port (21) is connected to the air supply device through an air pipe. Multiple thrust rods (9), the first end of the multiple thrust rods (9) is connected to the separator (10), and the second end of the multiple thrust rods (9) is slidably connected to the air passage component (3); A locking stud (4) is provided inside a sliding cavity (41). The first end of the locking stud (4) passes through the through hole of the separator (10) and the body (11), and the first end of the locking stud (4) slides in the inner cavity of the air passage component (3). The locking stud (4) is provided with a sliding cavity (41), which passes through the end face of the first end of the locking stud (4). Multiple limiting cavities (42) are provided on the outer side of the first end of the locking stud (4). The multiple limiting cavities (42) are distributed radially along the locking stud (4) and are connected to the sliding cavity (41). The second end of the locking stud (4) is threaded with a locking nut (1), which abuts against the body (11). Multiple ball columns (8) are slidably disposed in multiple limiting cavities (42). The outer ends of the multiple ball columns (8) are hemispherical and are adapted to multiple limiting holes (36). A stop block (5) is slidably disposed in the sliding cavity (41), and a return spring (7) is provided between the stop block (5) and the inner bottom surface of the sliding cavity (41).

2. The spherical-type non-pyrotechnic aerodynamic separation and unlocking device for a launch vehicle according to claim 1, characterized in that, Also includes: A connecting ring (22) is formed on the bottom surface of the inflatable end cap (2); A connecting boss (31) is formed on the upper surface of the gas passage component (3), and the connecting ring (22) is threadedly connected to the connecting boss (31). The first sealing ring (32) is embedded in the first annular groove on the surface of the connecting boss (31), and the first sealing ring (32) is in close contact with the bottom surface of the inflatable end cap (2).

3. The spherical-type non-pyrotechnic aerodynamic separation and unlocking device for a launch vehicle according to claim 1, characterized in that, The multiple thrust rods (9) include: A limiting ring (91) is provided at the bottom end of the guide cavity (34) on the bottom surface of the air passage component (3); A sliding block (93) is slidably disposed within the guide cavity (34); The rod (92) is integrally formed with the sliding block (93), the end of the rod (92) passes through the limiting ring (91), and the end of the rod (92) is connected to the separator (10).

4. The spherical-type non-pyrotechnic aerodynamic separation and unlocking device for a launch vehicle according to claim 3, characterized in that, Also includes: Multiple air passages (33), the first end of each of the multiple air passages (33) is connected to the inner cavity of the air passage component (3), and the second end of each of the multiple air passages (33) is connected to the inner cavity of the multiple guide cavities (34) away from the limiting ring (91); The fourth sealing ring (94) is embedded in the fourth annular groove on the outside of the sliding block (93), and the fourth sealing ring (94) is in close contact with the inner wall of the guide cavity (34).

5. The spherical-type non-pyrotechnic aerodynamic separation and unlocking device for a launch vehicle according to claim 1, characterized in that, Also includes: Multiple second sealing rings (35) are respectively embedded in multiple second annular grooves on the inner wall of the gas passage component (3), and the multiple second sealing rings (35) are distributed on both sides of multiple limiting holes (36).

6. The spherical-type non-pyrotechnic aerodynamic separation and unlocking device for a launch vehicle according to claim 1, characterized in that, Also includes: Multiple third sealing rings (52) are embedded in multiple third annular grooves on the outer side of the stop block (5). The multiple third sealing rings (52) are in close contact with the inner wall of the sliding cavity (41). The multiple third sealing rings (52) are close to both ends of the stop block (5).

7. The spherical-type non-pyrotechnic aerodynamic separation and unlocking device for a launch vehicle according to claim 1, characterized in that, Also includes: The positioning cavity (51) is disposed inside the stop (5) and extends through the side of the stop (5) that contacts the return spring (7); Guide rod (6) is disposed in the sliding cavity (41) and slides in cooperation with the positioning cavity (51).

8. The spherical-type non-pyrotechnic aerodynamic separation and unlocking device for a launch vehicle according to claim 7, characterized in that, The bottom surface of the inflatable end cap (2) is formed with a protruding ring (23). When the return spring (7) supports the stop block (5) and contacts the protruding ring (23), the end of the guide rod (6) is located in the positioning cavity (51).

9. The spherical-type non-pyrotechnic aerodynamic separation and unlocking device for a launch vehicle according to claim 1, characterized in that, The sum of the radius of the limiting hole (36) and the length of the limiting cavity (42) is equal to the length of the ball column (8).

Images