Passivating electric explosion valve for aerospace craft

Abstract

The invention discloses a passivated electric explosion valve for an aerospace craft. The passivated electric explosion valve comprises an electric explosion pipe, an adapter, a piston, an elastic locking piece, a corrugated pipe assembly, a piston rod, a large spring, a shell and a blind nut. Before the electric explosion valve works, the piston makes contact with the end face of the shell, the V-shaped structure of the shoulder of the piston is not cut off, the piston rod makes contact with a shell spigot under the pretightening force effect of the large spring, and a medium channel is closed. After the electric explosion valve is detonated, the V-shaped groove in the end face of the piston is cut open, the lower end face of the corrugated pipe assembly jacks the upper end face of the piston rod, the medium channel is opened, and the medium cavity communicates with the discharging cavity. High-temperature fuel gas after detonation can be prevented from entering the piston rod side, and the high-temperature fuel gas is prevented from making contact with a propellant.

Description

Technical Field

[0001] The present invention relates to an electric explosion valve, in particular to a spacecraft passivation electric explosion valve, which can be used to discharge tank propellant at the end of a spacecraft mission and is widely used in liquid carrier rocket power systems or spacecraft propulsion systems. Background Art

[0002] Currently, spacecraft primarily use a timed engine drain valve to partially discharge propellant from their tanks after a mission. This method doesn't completely drain the propellant from the tanks. Long-term in-orbit exposure to sunlight can lead to elevated tank pressure, posing a risk of high-pressure rupture and the formation of space debris, potentially impacting the spacecraft. Electric explosive valves are widely used in launch vehicle booster delivery systems due to their high sealing and stability before detonation. However, existing structures cannot meet the requirements for isolating the detonation gas from the propellant, necessitating an urgent design for their structure. Summary of the Invention

[0003] In order to solve the deficiencies of the above-mentioned prior art, the purpose of the present invention is to solve the problem that the existing electric explosion valve is difficult to achieve passivation in a combustible propellant environment, and to provide a spacecraft passivation electric explosion valve, which has a cut-off part (i.e., a shoulder structure) arranged on the explosion chamber side, and a bellows assembly arranged inside to completely isolate the explosion chamber from the medium chamber and the discharge chamber, so as to solve the problem of high-temperature and high-pressure gas contacting and burning with the combustible propellant after the electric explosion valve is detonated.

[0004] To achieve the above object, the present invention is implemented through the following technical solutions:

[0005] A spacecraft passivation electric explosion valve comprises: an electric explosion tube, an adapter, a piston, an elastic locking piece, a bellows assembly, a piston rod, a large spring, a shell and a screw cover;

[0006] The adapter, piston, bellows assembly, piston rod and screw cap are arranged in sequence from top to bottom along the axial direction, and the housing is sleeved on the outside of the piston, bellows assembly, piston rod and screw cap; the lower end surface of the adapter is fixedly connected to the housing;

[0007] The shell is provided with a first chamber, a second chamber and a third chamber from top to bottom respectively;

[0008] A first stepped hole and a second stepped hole are machined from top to bottom in the first chamber, and the inner diameter of the first stepped hole is smaller than that of the second stepped hole;

[0009] The piston is sleeved inside the first stepped hole, the upper end surface of the piston is processed with a countersink, and the cavity between the countersink of the piston and the lower end surface of the adapter serves as the explosion chamber;

[0010] The upper end surface of the piston is processed with a shoulder limiting structure, and the adapter and the housing clamp and fix the shoulder structure, thereby fixing the axial position of the piston;

[0011] The elastic locking piece is connected to the piston and pressed against the inner wall of the first stepped hole, and the electric squib is fixedly mounted on the adapter;

[0012] The electric squib is ignited and detonated, generating high-temperature and high-pressure gas in the explosion chamber, cutting off the shoulder structure on the upper end face of the piston and pushing the piston downward along the axis to a position. The elastic locking member then moves radially outward and abuts against the inner wall of the second stepped hole to achieve locking and fixing, thereby preventing the piston from retracting upward along the axis.

[0013] A buffer ring is fixed to the lower end surface of the piston, and the buffer ring contacts the upper end surface of the bellows assembly to play a buffering role;

[0014] The adapter and the end face of the shell are sealed;

[0015] The outer wall of the piston and the housing are sealed;

[0016] The lower end surface of the shell of the bellows assembly is fixed to the first chamber of the shell by welding, so that the first chamber and the second chamber are isolated and sealed;

[0017] The second chamber serves as a discharge chamber, and the third chamber serves as a medium chamber;

[0018] The piston rod includes a rod section and a barrel section, wherein the rod section is located at the top of the barrel section, the barrel section is sleeved inside the third chamber, and the rod section passes through the second chamber and rests on the actuating rod of the bellows assembly;

[0019] The screw cover is fixedly connected to the bottom of the third chamber, and the bottom of the barrel section is a countersunk hole; one end of the large spring is squeezed and contracted in the countersunk hole at the bottom of the barrel section, and the other end of the large spring rests on the upper end surface of the screw cover, so that before the electric squib ignites and detonates, the upper end surface of the barrel section of the piston rod rests on the top wall of the third chamber, and the medium passage between the discharge chamber and the medium chamber is closed;

[0020] The screw cover and the shell are sealed.

[0021] Preferably, the elastic locking member comprises: a pin and a small spring;

[0022] Two axially symmetrical countersunk holes are machined on the outside of the piston, with small springs and pins placed in the countersunk holes in sequence; the preload force generated by the compression of the small spring is used to tighten the pin radially outward.

[0023] Preferably, the method further comprises: a V-shaped groove is provided on the upper end surface of the piston shoulder structure, and when the electric squib is detonated, the piston shoulder structure is cut along the V-shaped groove, causing the piston to move downward.

[0024] Preferably, it further comprises: a sealing ring;

[0025] The upper end surface of the piston rod barrel section is processed with an annular groove for placing a sealing ring, and the top wall of the third chamber is processed with a stop; before the electric squib is ignited and detonated, the upper end surface of the sealing ring in the annular groove contacts the stop on the inner wall of the shell.

[0026] Preferably, the sealing ring is made of fluoroplastic.

[0027] Preferably, the cylinder section of the piston rod is processed with radial through holes to increase the flow rate of the medium when the medium passage is connected.

[0028] Preferably, it also includes: an end face O-ring, a side face O-ring and a retaining ring;

[0029] The adapter and the shell end face are sealed by an end face O-ring;

[0030] The outer wall of the piston and the housing are sealed by side O-rings and retaining rings;

[0031] The outer wall of the piston is processed with multiple annular sealing grooves, and a set of side O-rings and retaining rings are placed in each annular sealing groove; the retaining ring is located under the side O-ring and is used to limit the side O-ring.

[0032] Preferably, the end face O-ring and the side face O-ring are both made of rubber material, and the retaining ring and the buffer ring are both made of fluoroplastic.

[0033] Preferably, it further comprises: a bolt, a cotter pin and a lock nut;

[0034] The adapter is connected to the housing by means of bolts and locking nuts, and a cotter pin is installed after the bolts and locking nuts are connected to prevent loosening.

[0035] Preferably, it further comprises: a small circle gasket;

[0036] The electric squib and the adapter are connected by threads, and a small circle gasket is used to seal the electric squib and the adapter; a V-shaped groove is processed on the contact surface between the electric squib and the small circle gasket to accommodate the extruded deformed part of the small circle gasket.

[0037] Compared with the prior art, the present invention has the following advantages:

[0038] 1. The present invention is provided with a bellows assembly, which is connected to the shell by welding, thereby achieving physical isolation between the explosion chamber and the medium chamber, solving the problem of contact between high-temperature and high-pressure gas and the medium during detonation, and can meet the requirements of use in methane, liquid hydrogen, and liquid oxygen environments.

[0039] 2. The piston of the present invention is located in the explosion chamber. The upper cavity of the piston not only forms the pressure chamber volume required for detonation, but also can accommodate smoke and unburned materials after detonation; the detonation pressure cut-off position is far away from the medium chamber and does not contact the medium chamber. The distance of the cut-off position can effectively slow down the diffusion of the detonation gas downstream. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Figure 1 The figure is a schematic diagram of the structure of a spacecraft passivation electric explosion valve before detonation according to the present invention.

[0041] Figure 2 The figure is a schematic diagram of the structure of a spacecraft passivation electric explosion valve after detonation according to the present invention.

[0042] Figure 3 The present invention is a schematic diagram illustrating a cavity of a spacecraft passivation electric explosion valve.

[0043] Figure 4 This is a schematic diagram of the welding of the bellows assembly of the present invention.

[0044] Figure 5 It is a schematic diagram of the stopper structure of the present invention.

[0045] Figure markings: 1- electric squib, 2- small circle gasket, 3- adapter, 4- bolt, 5- cotter pin, 6- end O-ring, 7- locking nut, 8- piston, 9- side O-ring, 10- retaining ring, 11- pin, 12- small spring, 13- bellows assembly, 14- piston rod, 15- large spring, 16- housing, 17- large circle gasket, 18- screw cover, 19- buffer ring, 20- sealing ring. DETAILED DESCRIPTION

[0046] The present invention will be described in further detail below with reference to the accompanying drawings.

[0047] To address the difficulty of existing electric explosion valves in meeting the passivation requirements for combustible propellants, the present invention provides a spacecraft passivation electric explosion valve. This passivation electric explosion valve has a cutoff portion located on the explosion chamber side and a bellows assembly installed inside, completely isolating the explosion chamber from the medium chamber and the exhaust chamber. This prevents high-temperature, high-pressure gas from contacting and combusting with the combustible propellant after the electric explosion valve is detonated.

[0048] like Figure 1 As shown, the passivation electric explosion valve provided by the present invention includes: an electric explosion tube 1, an adapter 3, a piston 8, an elastic locking piece, a bellows assembly 13, a piston rod 14, a large spring 15, a shell 16 and a screw cover 18.

[0049] The adapter 3, piston 8, bellows assembly 13, piston rod 14 and screw cap 18 are arranged in sequence from top to bottom along the axial direction, and the housing 16 is sleeved on the outside of the piston 8, bellows assembly 13, piston rod 14 and screw cap 18; the lower end surface of the adapter 3 is fixedly connected to the housing 16;

[0050] An embodiment of the present invention further includes: a bolt 4, a cotter pin 5 and a locking nut 7; the adapter 3 is connected to the housing 16 via the bolt 4 and the locking nut 7, and the bolt 4 and the locking nut 7 are prevented from loosening by the cotter pin 5 after being connected.

[0051] like Figure 3 As shown, the housing 16 is provided with a first chamber, a second chamber and a third chamber from top to bottom respectively;

[0052] A first stepped hole and a second stepped hole are machined from top to bottom in the first chamber, and the inner diameter of the first stepped hole is smaller than that of the second stepped hole;

[0053] The piston 8 is sleeved inside the first stepped hole. A countersink is machined on the upper end surface of the piston 8. The cavity between the countersink of the piston 8 and the lower end surface of the adapter 3 serves as an explosion chamber.

[0054] The elastic locking member (pin 11, small spring 12) is connected to the piston 8 and pressed against the inner wall of the first stepped hole, and the electric squib 1 is fixedly mounted on the adapter 3;

[0055] The upper end surface of the piston 8 is machined with a shoulder limit structure, and the adapter 3 and the housing 16 clamp and fix the shoulder limit structure, thereby fixing the axial position of the piston 8;

[0056] The elastic locking part includes: a pin 11 and a small spring 12; two countersunk holes symmetrical about the axis are processed on the outside of the piston 8, and the small spring 12 and the pin 11 are placed in the countersunk holes in sequence; the preload force generated by the compression of the small spring 12 is used to tighten the pin 11 radially outward.

[0057] The electric squib 1 is ignited and detonated, generating high-temperature and high-pressure gas in the explosion chamber, cutting off the shoulder structure on the upper end face of the piston 8 and pushing the piston 8 downward along the axis to the position. Then, the elastic locking member moves radially outward and abuts against the inner wall of the second stepped hole to achieve locking and fixing, preventing the piston 8 from retracting upward along the axis.

[0058] A buffer ring 19 is fixed to the lower end surface of the piston 8. The buffer ring 19 contacts the upper end surface of the bellows assembly 13 to play a buffering role. The material of the buffer ring 19 is fluoroplastic.

[0059] One embodiment of the present invention further includes: an end O-ring 6, a side O-ring 9, and a retaining ring 10. The connection between the adapter 3 and the housing 16 is sealed by the end O-ring 6; the outer wall of the piston 8 and the housing 16 are sealed by the side O-ring 9 and retaining ring 10. The end O-ring 6 and the side O-ring 9 are made of rubber, while the retaining ring 10 is made of fluoroplastic.

[0060] The outer wall of the piston 8 is processed with multiple annular sealing grooves, and a set of side O-rings 9 and retaining rings 10 are placed in each annular sealing groove; the retaining ring 10 is located below the side O-ring 9 and is used to limit the side O-ring 9.

[0061] The lower end surface of the shell of the bellows assembly 13 is fixed to the first chamber of the housing 16 by welding, so that the first chamber and the second chamber are isolated and sealed;

[0062] The piston rod 14 includes a rod section and a barrel section. The rod section is located at the top of the barrel section, and the barrel section is sleeved inside the third chamber. The rod section passes through the second chamber and rests on the actuating rod of the bellows assembly 13. In the initial state, the upper end surface of the barrel section of the piston rod 14 rests on the top wall of the third chamber, thereby sealing the medium passage between the medium chamber and the discharge chamber.

[0063] like Figure 3 As shown, the second chamber serves as the discharge chamber and the third chamber serves as the medium chamber; the screw cover 18 is fixedly connected to the bottom of the third chamber, and the bottom of the barrel section is a countersunk hole; one end of the large spring 15 is squeezed and contracted in the countersunk hole at the bottom of the barrel section, and the other end of the large spring 15 rests on the upper end face of the screw cover 18, so that the medium passage between the discharge chamber and the medium chamber is closed before the electric squib 1 is ignited and detonated.

[0064] When the electric squib 1 is ignited and detonated, the piston 8 moves downward along the axis, driving the actuating rod of the bellows assembly 13 to push the piston rod 14 to move synchronously, so that the medium passage between the medium chamber and the discharge chamber is changed from a closed state to a connected state;

[0065] The cylinder section of the piston rod 14 is machined with radial through holes to increase the flow rate of the medium when the medium passage is connected.

[0066] One embodiment of the present invention also includes: a small circle gasket 2; the electric squib 1 and the adapter 3 are connected by threads, and the electric squib 1 and the adapter 3 are sealed by the small circle gasket 2; a V-shaped groove is processed on the contact surface between the electric squib 1 and the small circle gasket 2 to accommodate the extruded deformed part of the small circle gasket 2.

[0067] like Figure 4As shown, one embodiment of the present invention further includes a sealing ring 20. The upper end surface of the piston rod 14 is machined with an annular groove for receiving the sealing ring 20, and the top wall of the third chamber is machined with a stopper. Before ignition of the squib 1, the upper end surface of the sealing ring 20 in the annular groove contacts the stopper on the inner wall of the housing 16, sealing the medium passage between the medium chamber and the discharge chamber. The piston rod 14 forms a seal under the preload force of the large spring 15. The sealing ring 20 is made of fluoroplastic.

[0068] The screw cap 18 is fixed to the housing 16 by means of threaded connection and welding. A sealing process is performed between the screw cap 18 and the housing 16. A large circle gasket 17 is provided between the screw cap 18 and the housing 16 to form a sealing structure.

[0069] A bellows assembly 13 is provided between the explosion chamber and the discharge chamber to completely isolate the high-temperature combustion gas in the explosion chamber from the combustible propellant in the discharge chamber after detonation. The bellows assembly 13 is a metal bellows.

[0070] The upper end surface of the piston 8 is processed with a shoulder structure for limiting position, and the upper end surface of the shoulder structure is provided with a V-shaped groove. When the electric squib 1 is detonated, the shoulder structure of the piston 8 is cut along the V-shaped groove, causing the piston 8 to move downward.

[0071] The piston 8 is installed in the explosion chamber, and the sparks cut off by the V-shaped groove will not come into contact with the combustible propellant in the medium chamber during detonation.

[0072] The bellows assembly 13 is connected to the housing 16 by welding. Before detonation, the piston rod 14 contacts the housing 16, sealing the inlet and outlet passages. A V-shaped groove is provided at the contact point between the squib 1 and the small washer 2 to accommodate the deformed portion of the small washer 2. The adapter 3 is connected to the housing 16 via bolts 4 and locknuts 7. The bolts 4 and locknuts 7 are secured by a cotter pin 5. The piston 8 is then installed into the housing 16 after installing a side O-ring 9 and a retaining ring 10 in its sealing groove. The piston 8 then contacts the upper end of the bellows assembly 13, creating a stop. The adapter 3 is then installed after installing an end O-ring 6 in the sealing groove at the upper end of the housing 16. The end O-ring 6 acts as an end seal. The bellows assembly 13 is installed in the housing 16. The contact ends of the bellows assembly 13 and the housing 16 are welded together, forming a sealed structure that isolates the explosion chamber from the discharge chamber. The lower end face of the bellows assembly 13 contacts the upper end face of the piston rod 14 to form a limit; the end of the piston rod 14 contacts the stopper of the shell 16, and a seal is formed under the action of the installation pre-tightening force of the large spring 15; the screw cover 18 and the large circle gasket 17 are installed on the lower end face of the shell 16 and connected by thread + welding, and the three form a sealing structure.

[0073] Figure 1This is a schematic diagram of the structure of a spacecraft passivation electric explosion valve before detonation. Before the electric explosion valve works, the piston 8 contacts the end surface of the housing 16, the V-shaped structure of the shoulder of the piston 8 is not cut off, and the piston rod 14 contacts the stop of the housing 16 under the preload force of the large spring 15, and the medium passage is closed. Figure 5 shown.

[0074] Figure 2 This is a schematic diagram of the structure of the passivation electric explosion valve of a spacecraft after detonation. The V-groove on the end face of the piston 8 is cut, and the pin 11 is pinned to the housing 16 under the joint action of the small spring 12, and the position of the piston 8 remains stationary; the bellows assembly 13 undergoes a certain degree of compression deformation, and the lower end face of the bellows assembly 13 has pushed up the upper end face of the piston rod 14, the medium passage is opened, and the medium chamber is connected to the discharge chamber.

[0075] When the electric explosion valve is working, the electric explosion tube 1 is energized to generate high-temperature and high-pressure gas to push the piston 8 downward. Under the action of the high-temperature and high-pressure gas, the V-groove of the piston 8 is cut off. The downward movement of the piston 8 pushes the bellows assembly 13 to undergo a certain compression deformation. The lower end face of the bellows assembly 13 is pressed against the upper end face of the piston rod 14, opening the medium passage. The pin 11 is pinned to the shell 16 under the joint action of the small spring 12, and the position of the piston 8 remains stationary. The medium chamber and the discharge chamber are always connected, ensuring that the tank pressure is discharged to the outside when it is on track for a long time.

[0076] The piston in the present invention is located on the explosion chamber side, and the upper cavity of the piston not only forms the pressure chamber volume required for detonation, but also can accommodate smoke and unburned materials after detonation; the detonation pressure cut-off position is far away from the medium chamber and does not contact the medium chamber. The distance of the cut-off position can effectively slow down the diffusion of the detonation gas downstream.

[0077] The passivated electric explosion valve of the present invention is provided with a bellows assembly, and the bellows assembly is connected to the shell by welding, thereby realizing physical isolation between the explosion chamber and the medium chamber, solving the problem of contact between high-temperature and high-pressure gas and the medium during detonation, and can meet the requirements of use in methane, liquid hydrogen, and liquid oxygen environments. The passivated electric explosion valve is not affected by factors such as temperature environment, impact, and vibration, and can widely expand the application range of the product.

[0078] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A spacecraft passivation electric explosion valve, characterized in that: include: Electric squib (1), adapter (3), piston (8), elastic locking member, bellows assembly (13), piston rod (14), large spring (15), housing (16) and screw cover (18); The adapter (3), the piston (8), the bellows assembly (13), the piston rod (14) and the screw cover (18) are arranged in sequence from top to bottom along the axial direction, and the housing (16) is sleeved on the outside of the piston (8), the bellows assembly (13), the piston rod (14) and the screw cover (18); the lower end surface of the adapter (3) and the housing (16) are fixedly connected; A first chamber, a second chamber and a third chamber are respectively arranged in the housing (16) from top to bottom; A first stepped hole and a second stepped hole are machined from top to bottom in the first chamber, and the inner diameter of the first stepped hole is smaller than that of the second stepped hole; The piston (8) is sleeved inside the first stepped hole, the upper end surface of the piston (8) is processed with a countersink, and the cavity between the countersink of the piston (8) and the lower end surface of the adapter (3) serves as an explosion chamber; The upper end surface of the piston (8) is processed with a shoulder limiting structure, and the adapter (3) and the housing (16) clamp and fix the shoulder structure, thereby fixing the axial position of the piston (8); The elastic locking member is connected to the piston (8) and abuts against the inner wall of the first stepped hole, and the electric squib (1) is fixedly mounted on the adapter (3); The electric squib (1) is ignited and detonated, generating high-temperature and high-pressure gas in the explosion chamber, cutting off the shoulder structure on the upper end face of the piston (8), and pushing the piston (8) downward along the axis to a position, and then the elastic locking member moves radially outward and abuts against the inner wall of the second stepped hole to achieve locking and fixing, thereby preventing the piston (8) from retracting upward along the axis; A buffer ring (19) is fixed to the lower end surface of the piston (8), and the buffer ring (19) contacts the upper end surface of the bellows assembly (13) to play a buffering role; A sealing process is performed between the end surface of the adapter (3) and the housing (16); A sealing process is performed between the outer wall of the piston (8) and the housing (16); The lower end surface of the shell of the bellows assembly (13) is fixed to the first chamber of the housing (16) by welding, so that the first chamber and the second chamber are isolated and sealed; The second chamber serves as a discharge chamber, and the third chamber serves as a medium chamber; The piston rod (14) comprises a rod section and a barrel section, wherein the rod section is located at the top of the barrel section, the barrel section is sleeved inside the third chamber, and the rod section passes through the second chamber and rests on the actuating rod of the bellows assembly (13); The screw cover (18) is fixedly connected to the bottom of the third chamber, and the bottom of the barrel section is a countersunk hole; one end of the large spring (15) is squeezed and contracted in the countersunk hole at the bottom of the barrel section, and the other end of the large spring (15) is pressed against the upper end surface of the screw cover (18), so that before the electric squib (1) is ignited and detonated, the upper end surface of the barrel section of the piston rod (14) is pressed against the top wall of the third chamber, and the medium passage between the discharge chamber and the medium chamber is closed; A sealing process is performed between the screw cover (18) and the housing (16).

2. The aerospace vehicle passivation electric explosion valve according to claim 1, characterized in that: The elastic locking member comprises: a pin (11) and a small spring (12); The outer side of the piston (8) is processed with two axially symmetrical countersunk holes, in which a small spring (12) and a pin (11) are placed in sequence; the preload force generated by the compression of the small spring (12) is used to tighten the pin (11) radially outward.

3. The aerospace vehicle passivation electric explosion valve according to claim 1, characterized in that: Also includes: The upper end surface of the shoulder structure of the piston (8) is provided with a V-shaped groove. When the electric squib (1) is detonated, the shoulder structure of the piston (8) is cut along the V-shaped groove, causing the piston (8) to move downward.

4. The aerospace vehicle passivation electric explosion valve according to claim 3, characterized in that: Also includes: Sealing ring (20); The upper end surface of the cylinder section of the piston rod (14) is processed with an annular groove for accommodating a sealing ring (20), and the top wall of the third chamber is processed with a stop; before the electric squib (1) is ignited and detonated, the upper end surface of the sealing ring (20) in the annular groove contacts the stop on the inner wall of the shell (16).

5. The aerospace vehicle passivation electric explosion valve according to claim 4, characterized in that: The material of the sealing ring (20) is fluoroplastic.

6. The aerospace vehicle passivation electric explosion valve according to claim 5, characterized in that: The cylinder section of the piston rod (14) is processed with a radial through hole for increasing the flow rate of the medium when the medium passage is in a connected state.

7. The aerospace vehicle passivation electric explosion valve according to any one of claims 1 to 6, characterized in that: Also includes: End face O-ring (6), side face O-ring (9) and retaining ring (10); The adapter (3) and the end face of the housing (16) are sealed by an end face O-ring (6); The outer wall of the piston (8) and the housing (16) are sealed by a side O-ring (9) and a retaining ring (10); The outer wall of the piston (8) is processed with multiple annular sealing grooves, and a set of side O-rings (9) and retaining rings (10) are placed in each annular sealing groove; the retaining ring (10) is located below the side O-rings (9) and is used to limit the side O-rings (9).

8. The aerospace vehicle passivation electric explosion valve according to claim 7, characterized in that: The end face O-ring (6) and the side face O-ring (9) are both made of rubber material, and the retaining ring (10) and the buffer ring (19) are both made of fluoroplastic.

9. The aerospace vehicle passivation electric explosion valve according to claim 8, characterized in that: Also includes: Bolt (4), cotter pin (5) and lock nut (7); The adapter (3) is connected to the housing (16) via a bolt (4) and a locking nut (7). After the bolt (4) and the locking nut (7) are connected, a cotter pin (5) is installed to prevent loosening.

10. The aerospace vehicle passivation electric explosion valve according to claim 9, characterized in that: Also includes: Small circle gasket (2); The electric squib (1) and the adapter (3) are connected via threads, and a small circle gasket (2) is provided between the electric squib (1) and the adapter (3) for sealing. A V-shaped groove is machined on the contact surface between the electric squib (1) and the small circle gasket (2) for accommodating the extruded deformed portion of the small circle gasket (2).

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