Plug-in mounting type high-pressure valve for aviation

Abstract

The utility model belongs to the technical field of aviation valves, and particularly relates to an aviation plug-in mounting type high-pressure valve which comprises a valve seat and a shell, an inner cavity and an outer cavity are formed in the valve seat, a main valve port is installed on one side of the valve seat and communicated with the inner cavity, first sealing rings are installed at the two ends of the outer cavity, and a framework is arranged in the shell. The coil assembly is arranged on the outer side of the framework, the iron core assembly is arranged in the framework, the aviation socket assembly is arranged at the end of the shell, the characteristics of high integration, light weight, miniaturization, easy replacement and easy maintenance needed by an aviation electromagnetic valve are innovatively integrated together, and the aviation electromagnetic valve can be better suitable for national aerospace equipment; the plug-in mounting type high-pressure valve for aviation has the advantages of being compact in structure, stable in function, good in sealing performance, accurate in control and the like, and is an important device for fluid control in the aviation field.

Description

Technical Field

[0001] The utility model belongs to the technical field of aviation valves, and in particular relates to a plug-in high-pressure valve for aviation. Background Art

[0002] The solenoid valve is an actuator in the automatic control system, which is used to control the opening and closing of the fluid and change the direction of the fluid. With the progress of the times and the development of science and technology, the application scenarios of solenoid valves are becoming more and more numerous and complex, and higher and higher requirements are also put forward for the use of solenoid valves; the common general solenoid valves can no longer meet the requirements of increasingly sophisticated scenarios;

[0003] The general solenoid valves in the prior art can often only meet most of the needs of customers. In some special cases, such as in aerospace equipment, there are strict restrictions on the quality and space of each component in the system. At the same time, there are strict requirements on the durability and maintenance of the solenoid valves. It is difficult for the existing solenoid valves to take into account and solve this problem well. In the face of objective difficulties, we can only give in and accept this fact, and use large-volume and high-mass solenoid valves as replacements, and frequently disassemble and maintain them. There is no optimal solution for the entire system or the entire equipment, and the effect will be greatly reduced, or it will not be able to achieve the expected goals, further affecting the progress of aerospace engineering and ensuring system safety. Utility Model Content

[0004] 1. Technical issues to be solved

[0005] The utility model aims at the above-mentioned defects existing in the prior art and specially proposes an aviation plug-in high-pressure valve, which innovatively integrates the high integration, light weight, miniaturization, easy replacement and easy maintenance characteristics required by aviation solenoid valves, and can be better applied to our country's aerospace equipment, solving the various limitations of solenoid valves in aviation equipment in the past.

[0006] 2. Technical Solution

[0007] In order to solve the above technical problems, the utility model provides an aviation plug-in high-pressure valve, including a valve seat and a shell, an inner cavity and an outer cavity are provided on the valve seat, a main valve port is installed on one side of the valve seat, the main valve port is communicated with the inner cavity, a first sealing ring is installed at both ends of the outer cavity, a frame is arranged inside the shell, a coil assembly is arranged outside the frame, an iron core assembly is arranged inside the frame, and an aviation socket assembly is arranged at the end of the shell.

[0008] Preferably, the core assembly comprises a fixed core and a movable core arranged inside the frame, contact surfaces of the fixed core and the movable core are provided with mutually matching conical surfaces, and a spring is provided between the fixed core and the movable core.

[0009] Preferably, a through hole is opened at the end of the movable iron core, a sealing member is arranged below the through hole, the sealing member is a complete section passing through the center of the circle, and the through hole can move up and down in the inner cavity to be connected with or closed to the main valve port.

[0010] Preferably, the edge where the main valve port contacts the inner cavity is a slope structure, and when the seal slides up and down inside the inner cavity to seal the main valve port, impurities on the seal can be scraped off at the edge of the main valve port.

[0011] Preferably, the coil assembly comprises a coil sleeved on the outer wall of the frame, and the lead wire of the coil passes through the frame and is connected to the aviation socket assembly.

[0012] Preferably, the frame is made of stainless steel, the coil is a wound enameled wire, and a nano coating is provided on the outer wall of the coil winding frame.

[0013] Preferably, a second sealing ring is provided between the fixed iron core and the frame, and the fixed iron core and the frame are welded by laser.

[0014] Preferably, the aviation socket assembly includes an aviation plug arranged at the end of the shell, the lead wire of the coil is welded to the aviation plug, and the aviation plug is fixed to the shell by screws.

[0015] 3. Beneficial Effects

[0016] Compared with the prior art, the utility model is an aviation cartridge-type high-pressure valve, which can be better applied to aerospace equipment by integrating the high integration, light weight, miniaturization, easy replacement and easy maintenance characteristics required for aviation solenoid valves. This aviation cartridge-type high-pressure valve has the advantages of compact structure, stable function, good sealing performance and precise control. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 The figure is a cross-sectional view of a cartridge-type high-pressure valve for aviation use.

[0018] Figure 2 A cross-sectional view of the coil core assembly of an aviation plug-in high-pressure valve Figure 1 .

[0019] Figure 3 A cross-sectional view of the coil core assembly of an aviation plug-in high-pressure valve Figure 2 .

[0020] Figure 4 The figure is a cross-sectional view of the core assembly of a plug-in high-pressure valve for aviation.

[0021] Figure 5 This is a cross-sectional view of the main valve port of a plug-in high-pressure valve for aviation.

[0022] Figure 6The present invention is a cross-sectional view of an aviation socket assembly of an aviation plug-in high-pressure valve.

[0023] In the figure:

[0024] 1 is a valve seat; 11 is an inner cavity; 12 is an outer cavity; 2 is a shell; 3 is a main valve port; 4 is a first sealing ring; 5 is a skeleton; 51 is a nano coating; 6 is a coil assembly; 61 is a coil; 7 is an iron core assembly; 71 is a fixed iron core; 72 is a movable iron core; 721 is a through hole; 722 is a sealing member; 73 is a spring; 8 is an aviation socket assembly; 81 is an aviation plug; 9 is a second sealing ring. DETAILED DESCRIPTION

[0025] The following are further detailed descriptions of the specific implementation methods of the present invention as shown in the accompanying drawings and examples. The following examples are used to illustrate the present invention, but cannot be used to limit the scope of the present invention.

[0026] like Figure 1 , Figure 2 , Figure 3 and Figure 4As shown, the aviation plug-in high-pressure valve of this embodiment includes a valve seat 1 and a housing 2. The valve seat 1 is provided with an inner cavity 11 and an outer cavity 12. A main valve port 3 is installed on one side of the valve seat 1. The main valve port 3 is connected to the inner cavity 11. The first sealing ring 4 is installed at both ends of the outer cavity 12. A skeleton 5 is arranged inside the housing 2. A coil assembly 6 is arranged outside the skeleton 5. An iron core assembly 7 is arranged inside the skeleton 5. An aviation socket assembly 8 is arranged at the end of the housing 2. Specifically, the valve seat 1 is made of high-strength and corrosion-resistant materials to ensure that it can remain stable under extreme conditions. The valve seat 1 is provided with an inner cavity 11 and an outer cavity 12. The inner cavity 11 is used for the circulation of fluid and is connected to the main valve port 3 to form a fluid channel. The outer cavity 12 is mainly used to seal and fix the connection between the valve seat 1 and the housing 2. The main valve port 3 is installed on one side of the valve seat 1 and is connected to the inner cavity 11. The opening and closing state of the main valve port 3 determines whether the fluid can flow through the inner cavity 11. By controlling the opening and closing of the main valve port 3, precise control of the fluid flow can be achieved. A first sealing ring 4 is installed at both ends of the outer cavity 12. The first sealing ring 4 is made of highly elastic and wear-resistant material, which can fit the valve seat 1 and the housing 2 tightly when the valve is closed to prevent fluid leakage. Inside the housing 2, a skeleton 5 is provided to support and fix the internal components. A coil assembly 6 is provided on the outside of the skeleton 5. When energized, the coil assembly 6 generates a magnetic field to drive the core assembly 7 to move, thereby controlling the opening and closing of the main valve port 3. The core assembly 7 is located inside the skeleton 5. When the coil assembly 6 is energized to generate a magnetic field, the core assembly 7 moves under the action of the magnetic force. By controlling the current size and direction of the coil assembly 6, precise control of the moving speed and direction of the core assembly 7 can be achieved, thereby achieving precise control of the opening and closing state of the main valve port 3. At the end of the housing 2, an aviation socket assembly 8 is provided. The aviation socket assembly 8 is a connection interface between the valve and the external power supply and control system. It adopts a standard aviation socket design, which is convenient for connection with the aviation power supply and control system. Through the aviation socket assembly 8, the valve can be remotely controlled and monitored, thereby improving the convenience and safety of the valve.

[0027] The core assembly 7 includes a fixed core 71 and a movable core 72 arranged inside the skeleton 5, and the contact surfaces of the fixed core 71 and the movable core 72 are provided with mutually matching conical surfaces, and a spring 73 is provided between the fixed core 71 and the movable core 72. Specifically, the core assembly 7 includes a fixed core 71 and a movable core 72, both of which are arranged inside the skeleton 5. The fixed core 71 is the static part of the core assembly 7, and is usually fixed to the skeleton 5 by screws or other fastening methods. One end or a part of it is designed with a conical surface, and this conical surface matches the conical surface of the movable core 72. It can ensure that when the core assembly 7 moves, the contact between the fixed core 71 and the movable core 72 is tighter and more stable, thereby improving the sealing and control accuracy of the valve. The movable core 72 is the dynamic part of the core assembly 7, and it can move under the action of the magnetic field generated by the coil assembly 6. The other end of the movable core 72 is connected to the control mechanism of the main valve port 3, and the opening and closing of the main valve port 3 can be controlled by its movement. A spring 73 is provided between the fixed iron core 71 and the movable iron core 72. The main function of the spring 73 is to provide a reset force to ensure that when the coil assembly 6 is powered off, the movable iron core 72 can quickly return to the initial position to close the main valve port 3. At the same time, the spring 73 can also play a buffering role to reduce the impact and wear between the movable iron core 72 and the fixed iron core 71 during the movement. When the coil assembly 6 is powered on, a magnetic field is generated to attract the movable iron core 72 to move toward the fixed iron core 71. Due to the conical surface design between the two, the movable iron core 72 can fit tightly on the fixed iron core 71 to form a stable sealing structure. At the same time, the movement of the movable iron core 72 will drive the control mechanism of the main valve port 3 to operate, so that the main valve port 3 is opened and the fluid is allowed to pass. When the coil assembly 6 is powered off, the magnetic field disappears, and the movable iron core 72 quickly returns to the initial position under the reset force of the spring 73, so that the main valve port 3 is closed. In this way, by controlling the power-on and power-off states of the coil assembly 6, precise control of the opening and closing of the main valve port 3 can be achieved.

[0028] Furthermore, a through hole 721 is provided at the end of the movable iron core 72, and a sealing member 722 is provided below the through hole 721. The sealing member 722 is a complete cross section through the center of the circle, and the through hole 721 can move up and down in the inner cavity 11 to communicate with or close the main valve port 3. The through hole 721 is designed at the end of the movable iron core 72, which is a key part of the valve to control the flow of fluid. The opening of the through hole 721 enables the flow state of the fluid in the inner cavity 11 to be directly controlled when the movable iron core 72 moves. A sealing member 722 is provided below the through hole 721. This sealing member 722 adopts a cross section design through the center of the circle to ensure that the through hole 721 can be completely closed when the valve is closed to prevent fluid leakage. At the same time, this design also ensures a close fit between the sealing member 722 and the through hole 721, thereby improving the sealing performance of the valve. When the coil assembly 6 is powered off, the magnetic field disappears, and the movable iron core 72 moves downward under the reset force of the spring 73. During this process, the through hole 721 gradually aligns with and connects with the main valve port 3, allowing the fluid to pass smoothly through the inner cavity 11. When the movable iron core 72 returns to the initial position, the through hole 721 is completely connected with the main valve port 3, at which time the valve is in a fully open state and the fluid flow rate reaches a maximum. On the contrary, when the coil assembly 6 is energized, the movable iron core 72 moves upward under the action of the magnetic field. During this process, the through hole 721 gradually misaligns with the main valve port 3 and closes, and the fluid cannot pass through the inner cavity 11. When the movable iron core 72 moves to a certain position, the through hole 721 is completely closed, at which time the valve is in a closed state and the fluid is completely blocked. The full cross-section design of the sealing member 722 ensures that when the valve is closed, no matter how the position of the movable iron core 72 changes, the sealing member 722 can completely close the through hole 721, thereby preventing fluid leakage. This design greatly improves the sealing performance and reliability of the valve.

[0029] like Figure 1 , Figure 2 , Figure 4 and Figure 5As shown, the edge where the main valve port 3 contacts the inner cavity 11 is a slope structure. When the seal 722 slides up and down inside the inner cavity 11 to seal the main valve port 3, the edge of the main valve port 3 can scrape off impurities on the seal 722. Specifically, the slope structure enables the surface of the seal 722 to fit tightly with the edge of the main valve port 3 when the seal 722 slides up and down inside the inner cavity 11 to seal or open the main valve port 3. This fit not only improves the sealing performance and ensures that the fluid does not leak when the valve is closed, but also makes the seal 722 subject to uniform force distribution during the sliding process, reducing the risk of wear and damage. Secondly, the design of the slope structure enables the edge of the main valve port 3 to scrape off impurities that may be attached to the seal 722. During the long-term use of the valve, some tiny particles, dust or other impurities may accumulate on the seal 722. These impurities may affect the sealing effect of the seal and even cause the valve to fail. When the seal 722 slides on the ramp structure, the edge of the main valve port 3 acts like a scraper, which can scrape off these impurities and keep the seal 722 clean and smooth. In addition, the ramp structure also helps to achieve rapid closing and opening of the valve. When the valve needs to be closed, the movable iron core 72 drives the seal 722 to slide down quickly, and the ramp structure allows the seal 722 to quickly fit with the edge of the main valve port 3 to achieve rapid sealing. Similarly, when the valve needs to be opened, the seal 722 can also be quickly separated from the main valve port 3, allowing the fluid to pass smoothly.

[0030] The coil assembly 6 includes a coil 61 sleeved on the outer wall of the skeleton 5, and the lead of the coil 61 passes through the skeleton 5 and is connected to the aviation socket assembly 8. Specifically, the coil assembly 6 is responsible for generating a magnetic field, thereby driving the movement of the core assembly 7, thereby realizing the control of the main valve port 3. The coil assembly 6 is mainly composed of a coil 61, which is tightly sleeved on the outer wall of the skeleton 5. The skeleton 5 not only provides support for the coil 61, but also ensures the relative position stability between the coil 61 and the core assembly 7. The skeleton 5 is made of stainless steel, and the coil 61 is a wound enameled wire. A nano coating 51 is provided on the outer wall of the skeleton 5 around which the coil 61 is wound. The nano coating 51 can effectively resist chemical corrosion and electrochemical corrosion, and protect the coil 61 and the skeleton 5 from erosion by the external environment. The nano coating 51 has extremely high hardness and wear resistance, and can reduce the wear and damage of the coil 61 and the skeleton 5 in long-term use.

[0031] A second sealing ring 9 is provided between the fixed core 71 and the skeleton 5, and the fixed core 71 and the skeleton 5 are welded by laser. Specifically, the fixed core 71 and the skeleton 5 are connected by laser welding. Laser welding is a high-precision, high-energy welding method that can instantly melt and fuse two materials together through the energy of the laser beam without contacting the surface of the material. This welding method has the advantages of narrow weld, high strength, and small heat-affected zone. It is very suitable for occasions such as aviation plug-in high-pressure valves that have extremely high requirements for sealing and strength. In order to further improve the sealing performance between the fixed core 71 and the skeleton 5, a second sealing ring 9 is also added to the design. The second sealing ring 9 is located between the fixed core 71 and the skeleton 5, which can effectively prevent fluid or gas from leaking from the connection. This sealing ring is usually made of high-temperature resistant and corrosion-resistant materials, and can maintain stable sealing performance in harsh environments for a long time.

[0032] The above are only preferred implementations of the present invention. It should be pointed out that ordinary technicians in this technical field can make several improvements and modifications without departing from the technical principles of the present invention. These improvements and modifications should also be regarded as the protection scope of the present invention.

Claims

1. A plug-in high-pressure valve for aviation, characterized in that: The aviation plug-in high-pressure valve comprises a valve seat (1) and a housing (2); the valve seat (1) is provided with an inner cavity (11) and an outer cavity (12); a main valve port (3) is installed on one side of the valve seat (1); the main valve port (3) and the inner cavity (11) are communicated with each other; first sealing rings (4) are installed at both ends of the outer cavity (12); a frame (5) is arranged inside the housing (2); a coil assembly (6) is arranged outside the frame (5); an iron core assembly (7) is arranged inside the frame (5); and an aviation socket assembly (8) is arranged at the end of the housing (2); The iron core assembly (7) comprises a fixed iron core (71) and a movable iron core (72) arranged inside the frame (5); contact surfaces of the fixed iron core (71) and the movable iron core (72) are provided with mutually matching conical surfaces; and a spring (73) is provided between the fixed iron core (71) and the movable iron core (72).

2. The aviation cartridge high pressure valve according to claim 1, characterized in that: A through hole (721) is provided at the end of the movable iron core (72), a sealing member (722) is provided below the through hole (721), and the sealing member (722) is a complete section passing through the center of a circle. The through hole (721) can move up and down in the inner cavity (11) to communicate with or be closed off from the main valve port (3).

3. The aviation cartridge high pressure valve according to claim 2, characterized in that: The edge where the main valve port (3) contacts the inner cavity (11) is a slope structure, and when the sealing member (722) slides up and down inside the inner cavity (11) to seal the main valve port (3), impurities on the sealing member (722) can be scraped off at the edge of the main valve port (3).

4. The aviation cartridge high pressure valve according to claim 3, characterized in that: The coil assembly (6) comprises a coil (61) sleeved on the outer wall of the frame (5), and a lead wire of the coil (61) passes through the frame (5) and is connected to the aviation socket assembly (8).

5. The aviation cartridge high pressure valve according to claim 4, characterized in that: The frame (5) is made of stainless steel, the coil (61) is a wound enameled wire, and a nano coating (51) is provided on the outer wall of the frame (5) around which the coil (61) is wound.

6. The aviation cartridge high pressure valve according to claim 5, characterized in that: A second sealing ring (9) is provided between the fixed iron core (71) and the frame (5), and the fixed iron core (71) and the frame (5) are welded by laser.

7. The aviation cartridge high pressure valve according to claim 6, characterized in that: The aviation socket assembly (8) comprises an aviation plug (81) arranged at the end of the housing (2), the lead wire of the coil (61) is welded to the aviation plug (81), and the aviation plug (81) is fixed to the housing (2) by screws.

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