A multi-stage buffer device for separating pyrotechnic components for aerospace

Abstract

The present invention discloses a multi-stage buffering device for separating pyrotechnic components for aerospace, which belongs to the field of aerospace separation technology. A sleeve and a sliding assembly are provided to connect the plug-in aerospace component and the ejection piece. The ejection piece is instantly energized by pyrotechnic separation to generate an initial speed and fly out. The support plate and the support column involved in the ejection piece are squeezed by force, and the sliding seat squeezes the telescopic airbag cushion. After the telescopic airbag cushion is compressed, the gas can be introduced into the piston cylinder through the air guide tube to extend the piston rod. At the same time, the gear rotates under the action of the tooth groove, so that the torsion spring provides a reverse force, thereby buffering the plug-in aerospace component, and cooperating with the piston rod to provide reverse support to the fixing frame, which can achieve the purpose of elastic damping. The plug-in aerospace component is protected by a multi-stage buffering method to prevent the plug-in aerospace component and the ejection piece from being affected by the drag restriction affecting the buffering effect, thereby causing the component to be deformed, thereby improving the pyrotechnic separation efficiency and reducing the safety hazards in use.

Description

Technical Field

[0001] The present invention belongs to the field of aerospace separation technology, and in particular relates to a multi-stage buffer device for separating aerospace pyrotechnic components. Background Art

[0002] Spacecraft, operating outside Earth's atmosphere, are free from atmospheric obstructions and can receive all electromagnetic radiation from celestial bodies, opening up full-band astronomical observations. Spacecraft, flying from near-Earth space to interplanetary space, have achieved direct detection of the space environment, as well as close-up and direct sampling observations of the Moon and major planets in the solar system. Spacecraft orbiting Earth observe the Earth from distances ranging from hundreds to tens of thousands of kilometers, rapidly and extensively collecting a wide range of electromagnetic radiation information from Earth's atmosphere, oceans, and landmasses, directly serving meteorological observations, military reconnaissance, and resource exploration. Artificial satellites, acting as space radio relay stations, enable global satellite communications and broadcasting, and as space reference points, enable global satellite navigation and geodetic surveying. Taking advantage of the unique environment of space, such as high vacuum, intense radiation, and weightlessness, various important scientific experiments and research can be conducted on board spacecraft. Most spacecraft do not carry propulsion systems and fly freely in the extremely high vacuum of outer space, relying on inertia. Spacecraft move at speeds of eight to more than ten kilometers per second, provided by their launch vehicles. Their orbits are selected and designed in advance according to the mission.

[0003] A pyrotechnic device refers to a pyrotechnic device that uses the high-pressure gas generated by the explosion to push the mechanism to achieve the required action. Usually, a pyrotechnic device is used on separation surfaces with special requirements. The types of mechanisms used are different, and the actions completed are also different. Compared with other actuators, the pyrotechnic mechanism has the characteristics of lighter weight, smaller size, and higher reliability. Before pyrotechnic separation, engineers often design and install protective involvement mechanisms on aerospace parts such as ejection pieces that are close to the explosion point to connect with other aerospace parts. During separation, the ejection piece instantly obtains great kinetic energy and begins to drive the involved plug until the plug is separated. This acceleration process is usually completed within a few milliseconds.

[0004] The existing protective involvement mechanism is often unable to fully exert the effect of buffering protection due to the limitations of the involvement and dragging structure. During the separation process, the protective involvement mechanism will transmit a huge stress wave, and the driven aerospace parts will also produce a very large impact response. Excessive impact response will affect the normal use of aerospace instruments and even cause deformation of parts, affecting the efficiency of pyrotechnic separation and easily causing safety hazards. In view of this, a multi-stage buffering device for separation of aerospace pyrotechnic parts is proposed to solve the above problems. Summary of the Invention

[0005] In order to overcome the above-mentioned defects, the present invention provides a multi-stage buffering device for separating pyrotechnic components for aerospace, which solves the problem that the existing protective involvement mechanism is often unable to fully exert the buffering protection effect due to the limitations of the involvement and dragging structure. During the separation process, the protective involvement mechanism will transmit a huge stress wave, and the driven aerospace components will also produce a very large impact response. Excessive impact response will affect the normal use of aerospace instruments and even cause deformation of components, affecting the efficiency of pyrotechnic separation and easily causing safety hazards.

[0006] The objects of the present invention are:

[0007] The multi-level buffering method is used to protect the aerospace parts of the plug connector, preventing the drag restriction between the aerospace parts of the plug connector and the ejector from affecting the buffering effect and causing deformation of the parts, thereby improving the efficiency of pyrotechnic separation and reducing safety hazards in use;

[0008] The aerospace component can swing slightly left and right and accelerate the return speed to reduce the amplitude, thereby further improving the cushioning effect.

[0009] To achieve the above-mentioned objectives, the present invention provides the following technical solutions: a multi-stage buffering device for separating pyrotechnic components for aerospace, comprising a plug-in joint aerospace component and a ejection piece, one side of the plug-in joint aerospace component is fixedly connected to the sleeve, the ejection piece is fixedly connected to a sliding component on the side close to the plug-in joint aerospace component, the sliding component is slidably connected in the sleeve, the end of the sliding component close to the plug-in joint aerospace component is overlapped with an energy-absorbing component, the energy-absorbing component is arranged in the sleeve, the energy-absorbing component passes through the sleeve and is connected to four damping mechanisms, the four damping mechanisms are all fixedly connected to the outside of the sleeve, one end of the damping mechanism is overlapped with a buffer component, the other end of the buffer component is fixedly connected to the sliding component, four groups of tooth grooves are opened on the outside of the sleeve corresponding to the positions of the four buffer components, and the buffer component is arranged in the tooth grooves.

[0010] As a further solution of the present invention: the sliding assembly includes a support column, one end of the support column is fixedly connected to a support plate, the support plate is fixed to the throwing piece, the other end of the support column is fixedly connected to a sliding seat, the sliding seat is slidably connected in the sleeve, and four limit bars are fixedly connected to the outside of the support column.

[0011] By adopting the above technical solution, the limit strip can play a supporting and limiting role during the sliding process of the support column, preventing the support column from rotating and increasing the friction between the sliding seat and the telescopic airbag cushion, thereby protecting the telescopic airbag cushion.

[0012] As a further solution of the present invention: the energy absorbing component includes a support ring, a telescopic airbag cushion is provided outside the support ring, and four air guide tubes are connected to the side of the telescopic airbag cushion close to the plug-in aerospace component. The four air guide tubes pass through the sleeve and are respectively connected to the damping mechanism.

[0013] By adopting the above technical solution, the provision of the support ring can limit the telescopic airbag cushion, thereby preventing the telescopic airbag cushion from reducing its inner diameter due to collision and affecting normal air guide work.

[0014] As a further solution of the present invention: the support ring and one side of the telescopic airbag cushion are fixedly connected to the isolation ring, the isolation ring is clamped in the sleeve, and a telescopic rod is provided in the middle of the isolation ring, one end of the telescopic rod is fixed to the sliding assembly, and the other end of the telescopic rod is fixedly connected to one side of the inner wall of the sleeve.

[0015] By adopting the above technical solution, the support bar can play the role of supporting and limiting the support column, preventing the support column from angular deflection during movement and affecting the normal buffer stroke.

[0016] As a further solution of the present invention: the damping mechanism includes a piston cylinder, the end of the piston cylinder close to the plug-in joint aerospace component is connected to the air duct, a piston rod is provided in the piston cylinder, and the end of the piston rod close to the ejection piece is overlapped on the buffer assembly.

[0017] By adopting the above technical solution: after the telescopic airbag cushion is compressed, the gas can be introduced into the piston cylinder through the air guide tube. When the air pressure in the piston cylinder increases, the piston rod extends and contacts the fixing frame, which can play a reverse support role and improve the cushioning effect.

[0018] As a further solution of the present invention: the outside of the piston cylinder is fixedly connected to the outer wall of the sleeve through two fixing blocks, and a spring is connected to the outer cover of the piston rod, one end of the spring is fixed to the sleeve, and the other end of the spring is fixedly connected to one end of the piston rod.

[0019] By adopting the above technical solution: the spring contracts to cause the piston rod to detach from the fixed frame and retract into the piston cylinder, and the gas in the piston cylinder flows back to the telescopic airbag cushion through the air guide tube. The telescopic airbag cushion can push the sliding seat and the support column to prevent excessive pulling between the plug-in aerospace component and the ejection piece, affecting the buffering effect.

[0020] As a further solution of the present invention: the buffer assembly includes a fixing frame, one end of the fixing frame is fixedly connected to the support plate, both sides of the inner wall of the fixing frame are connected to the same gear through bearings, the gear is engaged in the tooth groove, and both sides of the outside of the gear are sleeved with torsion springs, one end of the torsion spring is fixedly connected to the gear, and the other end of the torsion spring is fixedly connected to one side of the inner wall of the fixing frame, and the top of the fixing frame is fixedly connected to the support plate through a reinforcement rod.

[0021] By adopting the above technical solution: providing a reverse force through the torsion spring on the gear, increasing the resistance to the gear rotation, thereby buffering the plug-in aerospace component, and cooperating with the piston rod to provide reverse support to the fixed frame, the purpose of elastic damping can be achieved, and the buffering effect can be further improved. Through the mutual cooperation between the gear and the tooth groove, the gear will not slip during the rotation process, thereby improving the stability of the support buffer.

[0022] As a further solution of the present invention: a groove is provided at one end of the sleeve close to the plug connector aerospace component, four through holes are provided at the bottom of the groove, and the through holes pass through the sleeve, and a plurality of exhaust holes are provided on the inner wall of the groove.

[0023] By adopting the above technical solution, when the sliding seat moves in the sleeve, external air can circulate with the air in the sleeve, preventing the increase of air pressure in the sleeve from affecting the normal use of the telescopic airbag cushion.

[0024] Compared with the prior art, the present invention has the following beneficial effects:

[0025] In the present invention, a sleeve and a sliding assembly are provided to connect the plug-in aerospace component and the throwing piece. The throwing piece is instantly energized and flies out at an initial speed when separated by pyrotechnics. The support plate and the support column involved in the throwing piece are squeezed by force, so that the support column drives the sliding seat to slide in the sleeve, and the sliding seat squeezes the telescopic airbag cushion. After the telescopic airbag cushion is compressed, the gas can be introduced into the piston cylinder through the air guide tube. After the air pressure in the piston cylinder increases, the piston rod extends and contacts the fixed frame. At the same time, when the support plate drives the fixed frame to move, the gear on the fixed frame can rotate under the action of the tooth groove. The torsion spring on the gear provides a reverse force to increase the resistance to gear rotation, thereby buffering the plug-in aerospace component. In conjunction with the piston rod to reversely support the fixed frame, the purpose of elastic damping can be achieved, and the buffering effect can be further improved. The plug-in aerospace component is protected by a multi-stage buffering method to prevent the plug-in aerospace component and the throwing piece from being affected by the drag restriction affecting the buffering effect, thereby causing deformation of the components, thereby improving the pyrotechnic separation efficiency while reducing safety hazards in use.

[0026] In the present invention, a piston rod is provided to support the fixing frame. When the unidirectional force is decomposed, the reaction force of the torsion spring can make the gear rotate in the opposite direction. The gear drives the support plate and the support column to extend out of the sleeve through the fixing frame. The spring contracts to make the piston rod separate from the fixing frame and retract into the piston cylinder. The gas in the piston cylinder flows back to the telescopic airbag cushion through the air guide tube. The telescopic airbag cushion can push the sliding seat and the support column to prevent excessive pulling between the plug-in aerospace component and the ejection piece from affecting the buffering effect. After the gear rotates in the opposite direction for several turns, the torsion spring provides the gear with a reverse force again, thereby enabling the support column to swing slightly left and right and accelerate the return speed of the support column, reducing the amplitude, thereby further improving the buffering effect.

[0027] In the present invention, the gears and the tooth grooves cooperate with each other to prevent the gears from slipping during rotation, thereby improving the stability of the support buffer. The setting of the support ring can limit the telescopic airbag cushion to prevent the telescopic airbag cushion from reducing its inner diameter due to collision and affecting the normal air guide work. Since a telescopic rod is provided, in combination with the setting of four limit strips, it can support and limit the support column to prevent the support column from angular deflection during movement and affecting the normal buffer stroke. Through the setting of the through hole and the exhaust hole, during the movement of the sliding seat in the sleeve, the outside air and the air in the sleeve can be circulated to prevent the increase of air pressure in the sleeve from affecting the normal use of the telescopic airbag cushion. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 It is a schematic diagram of the three-dimensional structure of the present invention;

[0029] Figure 2 It is a schematic diagram of the structure of the present invention when viewed from above;

[0030] Figure 3 It is a schematic structural diagram of the cross section of the present invention;

[0031] Figure 4 It is a schematic structural diagram of the cross section of the sleeve of the present invention;

[0032] Figure 5 This is a schematic structural diagram of the connection between the energy absorbing component and the damping mechanism of the present invention;

[0033] Figure 6 It is a structural schematic diagram of the buffer assembly of the present invention;

[0034] In the figure: 1. Plug connector aerospace component; 2. Ejector; 3. Sliding assembly; 301. Support column; 302. Sliding seat; 303. Support plate; 304. Limiting strip; 4. Sleeve; 5. Energy absorption assembly; 501. Support ring; 502. Telescopic airbag cushion; 503. Air guide tube; 6. Damping mechanism; 601. Piston cylinder; 602. Fixed block; 603. Spring; 604. Piston rod; 7. Buffer assembly; 701. Fixed frame; 702. Gear; 703. Bearing; 704. Torsion spring; 8. Reinforcement rod; 9. Tooth groove; 10. Telescopic rod; 11. Groove; 12. Through hole; 13. Exhaust hole; 14. Isolation ring. Implementation Method

[0035] The technical solution of the present application will be further described in detail below in conjunction with specific implementation methods.

[0036] like Figure 1-6As shown, the present invention provides a technical solution: a multi-stage buffer device for separating pyrotechnic components for aerospace, comprising a plug-in joint aerospace component 1 and a ejection piece 2, one side of the plug-in joint aerospace component 1 is fixedly connected to a sleeve 4, and the ejection piece 2 is fixedly connected to a sliding assembly 3 close to the plug-in joint aerospace component 1, and the sliding assembly 3 comprises a support column 301, one end of the support column 301 is fixedly connected to a support plate 303, the support plate 303 is fixed to the ejection piece 2, and the other end of the support column 301 is fixedly connected to a sliding seat 302, the sliding seat 302 is slidably connected in the sleeve 4, and four limit bars 304 are fixedly connected to the outside of the support column 301. Due to the provision of the limit bars 304, the limit bars 304 can play a supporting and limiting role in the sliding process of the support column 301, thereby preventing the support column 301 from rotating and increasing the friction between the sliding seat 302 and the telescopic airbag cushion 502, thereby protecting the telescopic airbag cushion 502;

[0037] The sliding assembly 3 is slidably connected within the sleeve 4. An energy absorbing assembly 5 is overlapped on one end of the sliding assembly 3 close to the plug-in aerospace component 1. The energy absorbing assembly 5 includes a support ring 501. A telescopic airbag cushion 502 is provided outside the support ring 501. Four air guide tubes 503 are connected to the side of the telescopic airbag cushion 502 close to the plug-in aerospace component 1. The four air guide tubes 503 pass through the sleeve 4 and are respectively connected to the damping mechanism 6. The provision of the support ring 501 can limit the telescopic airbag cushion 502, preventing the telescopic airbag cushion 502 from reducing its inner diameter due to collision and affecting normal air guide operation.

[0038] One side of the support ring 501 and the telescopic airbag cushion 502 is fixedly connected to the isolation ring 14, and the isolation ring 14 is clamped in the sleeve 4. A telescopic rod 10 is provided in the middle of the isolation ring 14. One end of the telescopic rod 10 is fixed to the sliding assembly 3, and the other end of the telescopic rod 10 is fixedly connected to one side of the inner wall of the sleeve 4. Due to the provision of the telescopic rod 10, the four limit bars 304 can play a role in supporting and limiting the support column 301, preventing the support column 301 from angular deflection during movement and affecting the normal buffer stroke;

[0039] The energy absorbing assembly 5 is arranged in the sleeve 4. The energy absorbing assembly 5 passes through the sleeve 4 and is connected to four damping mechanisms 6. The four damping mechanisms 6 are all fixedly connected to the outside of the sleeve 4. The damping mechanism 6 includes a piston cylinder 601. The end of the piston cylinder 601 close to the plug-in joint aerospace component 1 is connected to the air guide tube 503. A piston rod 604 is provided in the piston cylinder 601. The end of the piston rod 604 close to the throwing piece 2 is overlapped on the buffer assembly 7. Through the mutual cooperation between the piston cylinder 601 and the piston rod 604, the telescopic airbag cushion 502 can be compressed to introduce gas into the piston cylinder 601 through the air guide tube 503. When the air pressure in the piston cylinder 601 increases, the piston rod 604 extends and contacts with the fixing frame 701, which can play a role of reverse support and improve the buffering effect.

[0040] The outside of the piston cylinder 601 is fixedly connected to the outer wall of the sleeve 4 through two fixing blocks 602. A spring 603 is connected to the outer surface of the piston rod 604. One end of the spring 603 is fixed to the sleeve 4, and the other end of the spring 603 is fixedly connected to one end of the piston rod 604. Due to the presence of the spring 603, the spring 603 contracts to cause the piston rod 604 to separate from the fixing frame 701 and retract into the piston cylinder 601. The gas in the piston cylinder 601 then flows back into the telescopic airbag cushion 502 through the air guide tube 503. The telescopic airbag cushion 502 can push the sliding seat 302 and the support column 301 to prevent excessive pulling between the plug-in aerospace component 1 and the ejector plate 2 from affecting the buffering effect.

[0041] One end of the damping mechanism 6 is overlapped with a buffer component 7, and the other end of the buffer component 7 is fixedly connected to the sliding component 3. Four groups of tooth grooves 9 are opened on the outside of the sleeve 4 corresponding to the positions of the four buffer components 7. The buffer component 7 is arranged in the tooth groove 9. The buffer component 7 includes a fixed frame 701, one end of the fixed frame 701 is fixedly connected to the support plate 303, and both sides of the inner wall of the fixed frame 701 are connected to the same gear 702 through bearings 703. The gear 702 is engaged in the tooth groove 9, and both sides of the outer side of the gear 702 are sleeved with a torsion spring 704, one end of the torsion spring 704 is fixedly connected to the gear 702, and the other end of the torsion spring 704 is fixedly connected to one side of the inner wall of the fixed frame 701, and the top of the fixed frame 701 is fixedly connected to the support plate 303 through a reinforcing rod 8;

[0042] Because a torsion spring 704 is provided, a reverse force is provided by the torsion spring 704 on the gear 702, which increases the resistance to the rotation of the gear 702, thereby buffering the plug-in aerospace component 1, and cooperating with the piston rod 604 to provide reverse support to the fixed frame 701, which can achieve the purpose of elastic damping and further improve the buffering effect.

[0043] Through the mutual cooperation between the gear 702 and the tooth groove 9, the gear 702 will not slip during the rotation process, thereby improving the stability of the support buffer.

[0044] A groove 11 is provided at one end of the sleeve 4 close to the plug-in connector aerospace component 1, and four through holes 12 are provided at the bottom of the groove 11, and the through holes 12 pass through the sleeve 4. A number of exhaust holes 13 are provided on the inner wall of the groove 11. Through the arrangement of the through holes 12 and the exhaust holes 13, when the sliding seat 302 moves in the sleeve 4, the outside air can circulate with the air in the sleeve 4, thereby preventing the increase of the air pressure in the sleeve 4 from affecting the normal use of the telescopic airbag cushion 502.

[0045] From the above we know that:

[0046] After the telescopic airbag cushion 502 is compressed, it can guide the gas into the piston cylinder 601 through the air guide tube 503. When the air pressure in the piston cylinder 601 increases, the piston rod 604 extends and contacts the fixing frame 701. The torsion spring 704 on the gear 702 provides a reverse force, which increases the resistance to the rotation of the gear 702, thereby buffering the plug-in aerospace component 1. In conjunction with the piston rod 604, the fixing frame 701 is reversely supported, which can achieve the purpose of elastic damping. The plug-in aerospace component 1 is protected by a multi-stage buffering method to prevent the plug-in aerospace component 1 and the ejection piece 2 from affecting the buffering effect due to drag restriction, thereby causing deformation of the components, thereby improving the efficiency of pyrotechnic separation and reducing safety hazards in use.

[0047] The telescopic airbag cushion 502 can push the sliding seat 302 and the support column 301 to prevent excessive pulling between the plug-in space component 1 and the ejector 2 from affecting the buffering effect. After the gear 702 rotates in the opposite direction for several circles, the torsion spring 704 provides the gear 702 with a reverse force again, so that the support column 301 can swing slightly left and right and accelerate the return speed of the support column 301 to reduce the amplitude. During the movement of the sliding seat 302 in the sleeve 4, it can allow the outside air to circulate with the air in the sleeve 4, preventing the increase of air pressure in the sleeve 4 from affecting the normal use of the telescopic airbag cushion 502.

[0048] The working principle of the present invention is:

[0049] During use, the ejector 2 is instantly energized and flies out at an initial speed upon pyrotechnic separation. The supporting plate 303 and the supporting column 301 attached to the ejector 2 are then compressed, causing the supporting column 301 to drive the sliding seat 302 to slide within the sleeve 4. The sliding seat 302 then compresses the telescopic airbag cushion 502. After being compressed, the telescopic airbag cushion 502 can introduce gas into the piston cylinder 601 through the air guide tube 503.

[0050] During the movement of the sliding seat 302 in the sleeve 4, the gas in the piston cylinder 601 can be discharged from the through hole 12 and the exhaust hole 13. When the gas pressure in the piston cylinder 601 increases, the piston rod 604 extends and contacts the fixed frame 701. At the same time, when the support plate 303 drives the fixed frame 701 to move, the gear 702 on the fixed frame 701 can rotate under the action of the tooth groove 9. The torsion spring 704 on the gear 702 provides a reverse force to increase the resistance to the rotation of the gear 702, thereby buffering the plug connector aerospace component 1. In conjunction with the piston rod 604, the fixed frame 701 is reversely supported, thereby achieving the purpose of elastic damping.

[0051] When the unidirectional force is decomposed, the reaction force of the torsion spring 704 can cause the gear 702 to rotate in the opposite direction. The gear 702 drives the support plate 303 and the support column 301 to extend out of the sleeve 4 through the fixing frame 701. With the help of the spring 603 contracting, the piston rod 604 is separated from the fixing frame 701 and retracted into the piston cylinder 601.

[0052] The gas in the piston cylinder 601 flows back to the telescopic airbag cushion 502 through the air guide tube 503, and the telescopic airbag cushion 502 can push the sliding seat 302 and the support column 301. After the gear 702 rotates in the opposite direction for several circles, the torsion spring 704 provides a reverse force to the gear 702 again, so that the support column 301 can swing slightly left and right.

[0053] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed connections, detachable connections, or integral connections; mechanical connections or electrical connections; direct connections or indirect connections through an intermediate medium; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0054] The preferred embodiments of the present application are described in detail above, but the present application is not limited to the above embodiments. Various changes can be made within the scope of knowledge possessed by ordinary technicians in this field without departing from the purpose of the present application.

Claims

1. A multi-stage buffer device for separating aerospace pyrotechnic components, comprising a plug-in aerospace component (1) and a ejector (2), characterized in that: One side of the plug connector aerospace component (1) is fixedly connected to the sleeve (4), and the side of the ejector (2) close to the plug connector aerospace component (1) is fixedly connected to a sliding component (3), and the sliding component (3) is slidably connected in the sleeve (4). One end of the sliding component (3) close to the plug connector aerospace component (1) is overlapped with an energy absorbing component (5), and the energy absorbing component (5) is arranged in the sleeve (4). The energy absorbing component (5) passes through the sleeve (4) and is connected to four damping mechanisms (6). The four damping mechanisms (6) are all fixedly connected to the outside of the sleeve (4). One end of the damping mechanism (6) is overlapped with a buffer component (7), and the other end of the buffer component (7) is fixedly connected to the sliding component (3). The positions of the four buffer components (7) on the outside of the sleeve (4) are corresponding to the positions of the four buffer components (7). Four groups of tooth grooves (9) are provided, the buffer assembly (7) is arranged in the tooth grooves (9), the energy absorbing assembly (5) includes a support ring (501), a telescopic airbag cushion (502) is provided outside the support ring (501), the telescopic airbag cushion (502) is connected to four air guide tubes (503) on the side close to the plug connector aerospace component (1), the four air guide tubes (503) pass through the sleeve (4) and are respectively connected to the damping mechanism (6), the damping mechanism (6) includes a piston cylinder (601), one end of the piston cylinder (601) close to the plug connector aerospace component (1) is connected to the air guide tube (503), a piston rod (604) is provided in the piston cylinder (601), and one end of the piston rod (604) close to the ejection piece (2) is overlapped on the buffer assembly (7).

2. The multi-stage buffer device for separating aerospace pyrotechnic components according to claim 1, characterized in that: The sliding assembly (3) comprises a support column (301), one end of the support column (301) is fixedly connected to a support plate (303), the support plate (303) is fixed to the throwing piece (2), the other end of the support column (301) is fixedly connected to a sliding seat (302), the sliding seat (302) is slidably connected in the sleeve (4), and four limit bars (304) are fixedly connected to the outside of the support column (301).

3. The multi-stage buffer device for separating aerospace pyrotechnic components according to claim 1, characterized in that: One side of the support ring (501) and the telescopic airbag cushion (502) is fixedly connected to the isolation ring (14), and the isolation ring (14) is clamped in the sleeve (4). A telescopic rod (10) is provided in the middle of the isolation ring (14), one end of the telescopic rod (10) is fixed to the sliding assembly (3), and the other end of the telescopic rod (10) is fixedly connected to one side of the inner wall of the sleeve (4).

4. The multi-stage buffer device for separating aerospace pyrotechnic components according to claim 1, characterized in that: The piston cylinder (601) is fixedly connected to the outer wall of the sleeve (4) via two fixing blocks (602). The piston rod (604) is externally connected to a spring (603). One end of the spring (603) is fixed to the sleeve (4), and the other end of the spring (603) is fixedly connected to one end of the piston rod (604).

5. The multi-stage buffer device for separating aerospace pyrotechnic components according to claim 2, characterized in that: The buffer assembly (7) comprises a fixing frame (701), one end of the fixing frame (701) is fixedly connected to the support plate (303), and both sides of the inner wall of the fixing frame (701) are connected to the same gear (702) via bearings (703).

6. The multi-stage buffer device for separating aerospace pyrotechnic components according to claim 5, characterized in that: The gear (702) is meshed in the tooth groove (9), and torsion springs (704) are sleeved on both sides of the outside of the gear (702), and one end of the torsion spring (704) is fixedly connected to the gear (702).

7. The multi-stage buffer device for separating aerospace pyrotechnic components according to claim 6, characterized in that: The other end of the torsion spring (704) is fixedly connected to one side of the inner wall of the fixing frame (701), and the top of the fixing frame (701) is fixedly connected to the support plate (303) via a reinforcing rod (8).

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