CN113932039A - Valve head assembly of aviation electromagnetic valve and aviation electromagnetic valve - Google Patents
Valve head assembly of aviation electromagnetic valve and aviation electromagnetic valve Download PDFInfo
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- CN113932039A CN113932039A CN202111151472.3A CN202111151472A CN113932039A CN 113932039 A CN113932039 A CN 113932039A CN 202111151472 A CN202111151472 A CN 202111151472A CN 113932039 A CN113932039 A CN 113932039A
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- 230000013011 mating Effects 0.000 claims description 10
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- 238000009434 installation Methods 0.000 description 7
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- 229910000831 Steel Inorganic materials 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 229910052710 silicon Inorganic materials 0.000 description 2
- 239000010703 silicon Substances 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
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- 125000002777 acetyl group Chemical class [H]C([H])([H])C(*)=O 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K11/00—Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves
- F16K11/02—Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves with all movable sealing faces moving as one unit
- F16K11/04—Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves with all movable sealing faces moving as one unit comprising only lift valves
- F16K11/048—Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves with all movable sealing faces moving as one unit comprising only lift valves with valve seats positioned between movable valve members
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01D—SEPARATION
- B01D29/00—Filters with filtering elements stationary during filtration, e.g. pressure or suction filters, not covered by groups B01D24/00 - B01D27/00; Filtering elements therefor
- B01D29/0097—Curved filtering elements, e.g. concave filtering elements
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/232—Fuel valves; Draining valves or systems
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K31/00—Actuating devices; Operating means; Releasing devices
- F16K31/02—Actuating devices; Operating means; Releasing devices electric; magnetic
- F16K31/06—Actuating devices; Operating means; Releasing devices electric; magnetic using a magnet, e.g. diaphragm valves, cutting off by means of a liquid
- F16K31/0644—One-way valve
- F16K31/0655—Lift valves
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K31/00—Actuating devices; Operating means; Releasing devices
- F16K31/02—Actuating devices; Operating means; Releasing devices electric; magnetic
- F16K31/06—Actuating devices; Operating means; Releasing devices electric; magnetic using a magnet, e.g. diaphragm valves, cutting off by means of a liquid
- F16K31/0675—Electromagnet aspects, e.g. electric supply therefor
Abstract
The invention relates to the technical field of aviation power systems, and discloses a valve head assembly of an aviation electromagnetic valve and the aviation electromagnetic valve, wherein the valve head assembly comprises: the base, the valve body, the case, seal cover and filter screen, the base has fore-and-aft first flow channel, the lateral wall of first flow channel has first fitting surface, the periphery of base is located to the valve body cover, the lower part of valve body has aligns second flow channel with first flow channel, the first side of valve body is opened has the control hole, the second side of valve body is opened has the oil gallery, control hole and oil gallery all communicate with second flow channel, the oil gallery is located the top of control hole, the lateral wall of second flow channel has the second fitting surface, case swing joint is in first flow channel and second flow channel, the upper portion side of case has the third fitting surface with second fitting surface complex, the lower part side of case has the fourth fitting surface with first fitting surface complex, the seal cover cup joints in the periphery of valve body, two sides that the seal cover is relative have the side hole respectively, the filter screen is fixed in the lower extreme of valve body.
Description
Technical Field
The invention relates to the technical field of aviation power systems, in particular to a valve head assembly of an aviation electromagnetic valve and the aviation electromagnetic valve.
Background
The two-position three-way electromagnetic valve is widely applied to fuel metering devices of aero-engines and used for realizing the function of switching main backup oil paths, and each engine of a certain type needs to be provided with 10 pieces. In order to improve the thrust-weight ratio and the system reliability of the aviation device, the requirements on the pollution resistance, the sealing capability and the structural lightweight of the electromagnetic valve are provided.
In recent years, the self-developed aircraft engine in China has higher requirement on the pollution resistance of the electromagnetic valve, so the filter screen becomes an indispensable component in the aircraft electromagnetic valve, but most of the existing aircraft electromagnetic valve products are split filter screens, namely the filter screen and the valve body are split, the filter screen is installed on the valve body when in use, in order to ensure the sealing property between the filter screen and the valve body, a sealing part is required to be added to realize the sealing between the filter screen and the valve body, the structure leads the aircraft electromagnetic valve to have more complex structure and larger size structure, the structural size and the weight of the aircraft electromagnetic valve are increased, in addition, the requirement on the pollution resistance of the aircraft electromagnetic valve is higher, the sealing requirement on the oil inlet and outlet position of the electromagnetic valve is higher, the sealing structure of the oil inlet and outlet position is also complex, and the weight and the size of the aircraft electromagnetic valve are increased, thus the requirement of light structure is countered.
Disclosure of Invention
The invention provides a valve head assembly of an aviation electromagnetic valve and the aviation electromagnetic valve, which simplify the product structure size and weight of the aviation electromagnetic valve by improving the sealing structure of the aviation electromagnetic valve, and simultaneously realize the functions of filtering oil and switching oil ways in an aviation power system under different flight conditions to meet the product requirements of the aviation electromagnetic valve.
The invention provides a valve head component of an aviation electromagnetic valve, which comprises:
the base is provided with a longitudinal first flow channel, and the side wall of the first flow channel is provided with a first matching surface;
the valve body is sleeved on the periphery of the base, a second flow channel aligned with the first flow channel is arranged at the lower part of the valve body, a control hole is formed in the first side surface of the valve body, an oil return hole is formed in the second side surface, opposite to the first side surface, of the valve body, the control hole and the oil return hole are communicated with the second flow channel, the oil return hole is located above the control hole, and a second matching surface is formed in the side wall of the second flow channel;
the valve core is movably connected in the first flow channel and the second flow channel, the side surface of the upper part of the valve core is provided with a third matching surface matched with the second matching surface so that the valve core blocks the second flow channel, and the side surface of the lower part of the valve core is provided with a fourth matching surface matched with the first matching surface so that the valve core blocks the first flow channel;
the sealing sleeve is sleeved on the periphery of the valve body, and two opposite side surfaces of the sealing sleeve are respectively provided with a side hole;
the filter screen is fixed at the lower end of the valve body.
Optionally, the third mating surface and the fourth mating surface are both conical surfaces with a chamfer angle of 30-60 °.
Optionally, the valve core is cylindrical.
Optionally, the lower end of the valve body comprises a small valve body head, and the upper end of the filter screen is fixed at the inner side of the closing opening of the small valve body head.
Optionally, the bottom of the filter screen is provided with filter holes, and the aperture of each filter hole is 0.05mm-0.5 mm.
The invention also provides an aviation electromagnetic valve, which comprises:
the mounting sleeve is internally provided with a cavity;
the coil assembly is fixed in the cavity;
the magnet assembly is connected in the cavity in a sliding mode along the longitudinal direction and located on the inner side of the coil assembly, and the lower end of the magnet assembly is fixedly connected with the push rod;
the valve core of the valve head assembly is fixedly connected with the push rod.
Optionally, the magnet assembly comprises:
the electromagnet sleeve is fixed in the cavity;
the electromagnet is arranged in the electromagnet sleeve, the electromagnet is in sliding fit with the inner wall of the electromagnet sleeve along the longitudinal direction, a spring hole is formed above the electromagnet, and a spring is fixed in the spring hole.
Optionally, the coil assembly includes:
the coil framework is wound with an insulating tape at the bottom, and insulating washers are arranged on two sides of the coil framework;
the enameled wires are uniformly wound on the periphery of the coil framework;
the coil shell is sleeved outside the coil framework and fixed in the mounting sleeve;
one end of the lead is connected to the leading-out port of the coil framework, and the two ends of the lead are communicated with a power supply.
Optionally, the mounting sleeve has an external thread on its outer circumference.
Compared with the prior art, the invention has the beneficial effects that: according to the invention, through the integrated design of the filter screen and the valve body, a sealing part between the filter screen and the valve body is omitted, the structure between the filter screen and the valve body is simplified, meanwhile, a sealing sleeve is sleeved outside the valve body, and a first flow channel or a second flow channel is sealed at different positions by matching with a valve core, so that the circulation paths between the side hole on the sealing sleeve and the first flow channel and the second flow channel are realized, the oil filtering and oil path switching functions in an aviation power system under different flight conditions can be realized while the sealing structure of an oil path inlet and an oil path outlet is simplified, the product requirements of the aviation solenoid valve are met, the structural size and the weight of the aviation solenoid valve are further simplified, the structural lightweight is maximally ensured, and the aviation solenoid valve is more suitable for the aviation power system.
Drawings
FIG. 1 is a schematic overall structure diagram of an aviation solenoid valve provided in an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a valve head assembly of an aircraft solenoid valve according to an embodiment of the present invention;
FIG. 3 is a first operational state diagram of a valve head assembly of an aircraft solenoid valve according to an embodiment of the present invention;
FIG. 4 is a second operational condition of a valve head assembly of an aircraft solenoid valve according to an embodiment of the present invention;
FIG. 5 is a schematic structural diagram of a magnet assembly according to an embodiment of the present invention;
fig. 6 is a schematic structural diagram of a coil assembly according to an embodiment of the present invention.
Description of reference numerals:
1-a valve head component, 11-a base, 110-a first flow channel, 111-a first matching surface, 12-a valve core, 13-a sealing sleeve, 131-a side hole, 14-a valve body, 140-a second flow channel, 141-a second matching surface, 142-a control hole, 143-an oil return hole, 144-a valve body small end, 15-a filter screen, 2-a magnet component, 21-an electromagnet sleeve, 22-an electromagnet, 221-a spring hole, 3-a push rod, 4-a coil component, 41-a coil framework, 411-a leading-out opening, 42-a coil shell, 43-an enameled wire, 44-an insulating washer, 45-an insulating tape, 46-a conducting wire, 47-a pin hole, 5-a mounting sleeve, 6-a spring, 7-a pin and 8-a steel wire retainer ring.
Detailed Description
An embodiment of the present invention will be described in detail below with reference to the accompanying drawings, but it should be understood that the scope of the present invention is not limited to the embodiment.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "axial", "radial", "circumferential", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of describing technical solutions of the present invention and simplifying the description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
The two-position three-way electromagnetic valve is widely applied to fuel metering devices of aero-engines and used for realizing the function of switching main backup oil paths, and each engine of a certain type needs to be provided with 10 pieces. In order to improve the thrust-weight ratio and the system reliability of the aviation device, the requirements on the pollution resistance, the sealing capability and the structural lightweight of the electromagnetic valve are provided.
In recent years, the self-developed aircraft engine in China has higher requirement on the pollution resistance of the electromagnetic valve, so the filter screen becomes an indispensable component in the aircraft electromagnetic valve, but most of the existing aircraft electromagnetic valve products are split filter screens, namely the filter screen and the valve body are split, the filter screen is installed on the valve body when in use, in order to ensure the sealing property between the filter screen and the valve body, a sealing part is required to be added to realize the sealing between the filter screen and the valve body, the structure leads the aircraft electromagnetic valve to have more complex structure and larger size structure, the structural size and the weight of the aircraft electromagnetic valve are increased, in addition, the requirement on the pollution resistance of the aircraft electromagnetic valve is higher, the sealing requirement on the oil inlet and outlet position of the electromagnetic valve is higher, the sealing structure of the oil inlet and outlet position is also complex, and the weight and the size of the aircraft electromagnetic valve are increased, thus the requirement of light structure is countered.
In view of the above technical problems, the present invention provides a valve head assembly of an aircraft solenoid valve and an aircraft solenoid valve, and the technical solution of the present invention will be described in detail below with reference to the accompanying drawings, wherein,
as shown in fig. 1, an embodiment of the present invention provides a valve head assembly of an aircraft solenoid valve, including: the valve comprises a base 11, a valve body 14, a valve core 12, a sealing sleeve 13 and a filter screen 15, wherein the base 11 is provided with a longitudinal first flow passage 110, the side wall of the first flow passage 110 is provided with a first matching surface 111, the valve body 14 is sleeved on the periphery of the base 11, the lower part of the valve body 14 is provided with a second flow passage 140 aligned with the first flow passage 110, the first side surface of the valve body 14 is provided with a control hole 142, the second side surface of the valve body 14 opposite to the first side surface is provided with an oil return hole 143, the control hole 142 and the oil return hole 143 are both communicated with the second flow passage 140, the oil return hole 143 is positioned above the control hole 142, the side wall of the second flow passage 140 is provided with a second matching surface 141, the valve core 12 is movably connected in the first flow passage 110 and the second flow passage 140, the upper side surface of the valve core 12 is provided with a third matching surface matched with the second matching surface 141 so that the valve core 12 blocks the second flow passage 140, the lower side surface of the valve core 12 is provided with a fourth matching surface matched with the first matching surface 111, so that the valve core 12 blocks the first flow passage 110, the sealing sleeve 13 is sleeved on the periphery of the valve body 14, two opposite side surfaces of the sealing sleeve 13 are respectively provided with a side hole 131, the centers of the through holes are in the same horizontal line, the maximum aperture is ensured that when the sealing sleeve 13 is installed on the valve body 14, a proper position can be found, liquid flowing out of the oil return hole 142 can pass through the side hole 131, liquid flowing out of the control hole 143 cannot pass through the side hole 131, and the filter screen 15 is fixed at the lower end of the valve body 14.
The use method and the working principle are as follows: as shown in fig. 5, the lower portion of the filter screen 15 is connected to a high-pressure oil path, the position of the sealing sleeve 13 is adjusted to enable the control hole 142 to be completely communicated with the side hole 131 of the sealing sleeve 13 and to be connected to the control oil path, the oil return hole 143 is completely communicated with the other side hole 131 of the sealing sleeve 13 and to be connected to the oil return path, when the valve is in operation, the valve element 12 is driven to move upwards to press the second matching surface 141 of the valve body 14, a set of sealing surfaces is formed after the pressing, the second flow channel is blocked, the first flow channel 110 is opened, oil flows through the filter screen 15 first, is filtered and then passes through the first flow channel 110, the valve element 12, the control hole 142 and the side hole 131, and flows into the control oil path, and at this time, the control oil path is high-pressure oil. As shown in fig. 6, after the power is off, the spool 12 moves downward to press the first engagement surface 111, and another set of sealing surfaces is formed after the pressing, and at this time, oil flows in from the oil return hole 143 and flows out from the control hole 142, and the control oil path is low pressure oil.
According to the invention, through the integrated design of the filter screen and the valve body, a sealing part between the filter screen and the valve body is omitted, the structure between the filter screen and the valve body is simplified, meanwhile, a sealing sleeve is sleeved outside the valve body, and a first flow channel or a second flow channel is sealed at different positions by matching with a valve core, so that the circulation paths between the side hole on the sealing sleeve and the first flow channel and the second flow channel are realized, the oil filtering and oil path switching functions in an aviation power system under different flight conditions can be realized while the sealing structure of an oil path inlet and an oil path outlet is simplified, the product requirements of the aviation solenoid valve are met, the structural size and the weight of the aviation solenoid valve are further simplified, the structural lightweight is maximally ensured, and the aviation solenoid valve is more suitable for the aviation power system.
Optionally, the third mating surface and the fourth mating surface are both tapered surfaces with a chamfer angle of 30 ° to 60 °, and are respectively mated with the second mating surface 141 and the first mating surface 111.
Optionally, the spool 12 is cylindrical.
Optionally, the lower end of the valve body 14 includes a valve body small end 144, and the upper end of the filter screen 15 is fixed to the inner side of the closing opening of the valve body small end 144, and meanwhile, it is ensured that the filter screen 15 cannot be squeezed during closing to avoid deformation.
Optionally, the bottom of the filter screen 15 is provided with filter holes, the aperture of each filter hole is 0.05mm-0.5mm, the number of the filter holes is generally not more than ten thousand, and the specific aperture is determined according to the filter requirement and the flow resistance requirement.
Referring to fig. 2, an embodiment of the present invention further provides an aviation solenoid valve, including: installation cover 5, coil pack 4, magnet assembly 2 and foretell valve head assembly 1, 5 inside cavitys that have of installation cover, and in coil pack 4 was fixed in the cavity, magnet assembly 2 along longitudinal sliding connection in the cavity, magnet assembly 2 was located coil pack 4's inboard, and magnet assembly 2's lower extreme has linked firmly push rod 3, and valve head assembly 1's case 12 links firmly with push rod 3, and push rod 3's major diameter end allows to grind for a short time.
With particular reference to fig. 3, the magnet assembly 2 comprises: the electromagnet assembly comprises an electromagnet sleeve 21 and an electromagnet 22, wherein the electromagnet sleeve 21 is fixed in the cavity, the electromagnet 22 is arranged in the electromagnet sleeve 21, the electromagnet 22 is in sliding fit with the inner wall of the electromagnet sleeve 21 along the longitudinal direction, a spring hole 221 is formed above the electromagnet 22, a spring 6 is fixed in the spring hole 221, and the spring force is transmitted to the magnet assembly 2 through the spring 6.
Referring to fig. 4, the coil block 4 includes: the coil comprises a coil framework 41, an enameled wire 43, a coil shell 42 and a lead 46, wherein two layers of insulating belts 45 are wound at the bottom of the coil framework 41, insulating washers 44 are placed at two sides of the coil framework 41, the number of the insulating washers 44 can be adjusted in an increasing and decreasing mode according to assembly requirements, the enameled wire 43 is uniformly wound on the periphery of the coil framework 41, the enameled wire 43 is uniformly and tightly bundled around 1800 +/-200 layers on the coil framework 41, short circuit is not allowed, the coil shell 42 is sleeved outside the coil framework 41 and plays a role in fixing a coil component 4, the coil shell 42 is fixed in an installation sleeve 5, one end of the lead 46 is connected to a leading-out opening 411 of the coil framework 41, two ends of the lead are communicated with a power supply, a pin 7 is fixed with other components through a pin hole 47, a positioning groove is formed in the position, which is higher than the installation sleeve 5, a steel wire retainer ring 8 is installed at the groove to fix the relative position of the coil framework 41, the joint of the insulating washer 44 and the enameled wire 43 is bonded by W30-4 organic silicon insulating paint, two leads 46 are respectively welded with the beginning end and the end of the coil by tin-lead brazing filler metal, the welding position is wound by an insulating tape 45 for three-layer insulation, the insulating paint is coated, the leads 46 are wound by one circle on the coil, the insulating tape 45 is tightly wound by two layers, the ramie wire is tightly tied, the leads 46 are bonded on the leading-out opening 411 of the coil framework 41 by acetal glue solution, the coil is impregnated by the organic silicon insulating paint 30-4 or each layer of the coil is coated with the W30-4 insulating paint instead of impregnation, and the valve head assembly 1 is fixed on the coil framework 41 by adopting a laser welding method after the coil is wound and debugged.
Optionally, the outer circumference of the mounting sleeve 5 has an external thread.
The use method and the working principle are as follows:
the lower part of the filter screen 15 is connected with a high-pressure oil path, the position of the sealing sleeve 13 is adjusted to ensure that the control hole 142 is completely communicated with the side hole 131 of the sealing sleeve 13 and is connected with the control oil path, and the oil return hole 143 is completely communicated with the other side hole 131 of the sealing sleeve 13 and is connected with the oil return path.
After the electromagnetic valve is debugged and assembled, the electromagnetic valve is fixed in a pipeline needing to be installed with the electromagnetic valve through the external thread of the installation sleeve 5, the installation sleeve 5 is screwed, the sealing sleeve 13 moves upwards along the lower part of the valve body 14 at the same time, after the installation sleeve 5 is screwed, the position of the sealing sleeve 13 can ensure that the side hole 131 is simultaneously communicated with the oil return hole 143 and the control hole 142, as shown in fig. 5, when the electromagnetic valve works, the coil is electrified through the lead 46 to generate a magnetic field to enable the electromagnet 22 to move upwards, the valve core 12 is driven by the push rod 3 to press the second matching surface 141 of the valve body 14 to form a group of sealing surfaces after the pressing, at the moment, the spring 6 is in a compression state, the second flow channel is blocked, the first flow channel 110 is opened, oil flows through the filter screen 15 and then sequentially passes through the first flow channel 110, the valve core 12, the control hole 142 and the side hole 131 to flow into a control oil path, and the control oil path is high-pressure oil at the moment. As shown in fig. 6, after the power is cut off, the spool 12 moves downward under the action of the spring 6 to press the first mating surface 111, and another set of sealing surfaces is formed after the pressing, at this time, oil flows in from the oil return hole 143 and flows out from the control hole 142, and the control oil path is low-pressure oil.
The above disclosure is only for a few specific embodiments of the present invention, however, the present invention is not limited to the above embodiments, and any variations that can be made by those skilled in the art are intended to fall within the scope of the present invention.
Claims (9)
1. A valve head assembly for an aircraft solenoid valve, comprising:
a base (11) having a longitudinal first flow channel (110), a side wall of the first flow channel (110) having a first mating face (111);
the valve body (14) is sleeved on the periphery of the base (11), a second flow channel (140) aligned with the first flow channel (110) is arranged at the lower part of the valve body (14), a control hole (142) is formed in a first side surface of the valve body (14), an oil return hole (143) is formed in a second side surface, opposite to the first side surface, of the valve body (14), the control hole (142) and the oil return hole (143) are both communicated with the second flow channel (140), the oil return hole (143) is located above the control hole (142), and a second matching surface (141) is formed in the side wall of the second flow channel (140);
the valve core (12) is movably connected in the first flow channel (110) and the second flow channel (140), the upper side surface of the valve core (12) is provided with a third matching surface matched with the second matching surface (141) so that the valve core (12) blocks the second flow channel (140), and the lower side surface of the valve core (12) is provided with a fourth matching surface matched with the first matching surface (111) so that the valve core (12) blocks the first flow channel (110);
the sealing sleeve (13) is sleeved on the periphery of the valve body (14), and two opposite side surfaces of the sealing sleeve (13) are respectively provided with a side hole (131);
and the filter screen (15) is fixed at the lower end of the valve body (14).
2. The valve head assembly of an aircraft solenoid valve according to claim 1, wherein the third mating surface and the fourth mating surface are tapered surfaces chamfered at 30 ° to 60 °.
3. The valve head assembly of an aircraft solenoid valve according to claim 2, characterized in that the valve cartridge (12) is cylindrical.
4. Valve head assembly of an aircraft electromagnetic valve according to claim 1, characterized in that the lower end of the valve body (14) comprises a valve body small head (144), and the upper end of the sieve (15) is fixed inside the closing in of the valve body small head (144).
5. The valve head assembly of an aviation electromagnetic valve according to claim 1, wherein the bottom of the filter screen (15) is provided with filter holes, and the diameter of the filter holes is 0.05mm-0.5 mm.
6. An airborne solenoid valve, comprising:
a mounting sleeve (5) having a cavity therein;
a coil assembly (4) secured within the cavity;
the magnet assembly (2) is connected in the cavity in a sliding mode along the longitudinal direction, the magnet assembly (2) is located on the inner side of the coil assembly (4), and the lower end of the magnet assembly (2) is fixedly connected with a push rod (3);
the valve head assembly (1) according to any one of claims 1 to 5, wherein the valve core (12) of the valve head assembly (1) is fixedly connected with the push rod (3).
7. The airborne solenoid valve according to claim 6, characterized in that the magnet assembly (2) comprises:
an electromagnet sleeve (21) fixed in the cavity;
the electromagnet (22) is arranged in the electromagnet sleeve (21), the electromagnet (22) is in sliding fit with the inner wall of the electromagnet sleeve (21) along the longitudinal direction, a spring hole (221) is formed above the electromagnet (22), and a spring (6) is fixed in the spring hole (221).
8. The airborne solenoid valve according to claim 6, characterized in that the coil assembly (4) comprises:
the coil comprises a coil framework (41), wherein an insulating tape (45) is wound at the bottom of the coil framework, and insulating gaskets (44) are placed on two sides of the coil framework (41);
the enameled wire (43) is uniformly wound on the periphery of the coil framework (41);
the coil shell (42) is sleeved outside the coil framework (41), and the coil shell (42) is fixed in the mounting sleeve (5);
and one end of the lead (46) is connected to the leading-out opening (411) of the coil framework (41), and the two ends of the lead are communicated with a power supply.
9. The airborne solenoid valve according to claim 6, characterized in that the outer periphery of the mounting sleeve (5) has an external thread.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111151472.3A CN113932039A (en) | 2021-09-29 | 2021-09-29 | Valve head assembly of aviation electromagnetic valve and aviation electromagnetic valve |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111151472.3A CN113932039A (en) | 2021-09-29 | 2021-09-29 | Valve head assembly of aviation electromagnetic valve and aviation electromagnetic valve |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113932039A true CN113932039A (en) | 2022-01-14 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111151472.3A Pending CN113932039A (en) | 2021-09-29 | 2021-09-29 | Valve head assembly of aviation electromagnetic valve and aviation electromagnetic valve |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102338231A (en) * | 2011-08-26 | 2012-02-01 | 北京航天动力研究所 | Two-position three-way electromagnetic valve |
| WO2015037351A1 (en) * | 2013-09-10 | 2015-03-19 | 日立オートモティブシステムズ株式会社 | Solenoid valve |
| CN109185541A (en) * | 2018-11-21 | 2019-01-11 | 中国航发贵州红林航空动力控制科技有限公司 | A kind of two-bit triplet with buffer gear miniature fuel solenoid valve open in usual |
| CN109253279A (en) * | 2018-11-21 | 2019-01-22 | 中国航发贵州红林航空动力控制科技有限公司 | A kind of two-position three way normal close minisize solenoid valve of anti-vibration |
| JP2019219006A (en) * | 2018-06-20 | 2019-12-26 | アズビルＴａｃｏ株式会社 | Electromagnetic valve |
| CN110886871A (en) * | 2019-12-09 | 2020-03-17 | 行益科技(宁波)有限公司 | Multipurpose electromagnetic valve |
-
2021
- 2021-09-29 CN CN202111151472.3A patent/CN113932039A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102338231A (en) * | 2011-08-26 | 2012-02-01 | 北京航天动力研究所 | Two-position three-way electromagnetic valve |
| WO2015037351A1 (en) * | 2013-09-10 | 2015-03-19 | 日立オートモティブシステムズ株式会社 | Solenoid valve |
| JP2019219006A (en) * | 2018-06-20 | 2019-12-26 | アズビルＴａｃｏ株式会社 | Electromagnetic valve |
| CN109185541A (en) * | 2018-11-21 | 2019-01-11 | 中国航发贵州红林航空动力控制科技有限公司 | A kind of two-bit triplet with buffer gear miniature fuel solenoid valve open in usual |
| CN109253279A (en) * | 2018-11-21 | 2019-01-22 | 中国航发贵州红林航空动力控制科技有限公司 | A kind of two-position three way normal close minisize solenoid valve of anti-vibration |
| CN110886871A (en) * | 2019-12-09 | 2020-03-17 | 行益科技(宁波)有限公司 | Multipurpose electromagnetic valve |
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