CN212377334U - Helicopter pressure refueling electric valve - Google Patents
Helicopter pressure refueling electric valve Download PDFInfo
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- CN212377334U CN212377334U CN202020689969.5U CN202020689969U CN212377334U CN 212377334 U CN212377334 U CN 212377334U CN 202020689969 U CN202020689969 U CN 202020689969U CN 212377334 U CN212377334 U CN 212377334U
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Abstract
The utility model discloses a helicopter pressure refuels motorised valve. The device comprises an electric mechanism and a gate valve; the gate valve comprises a gate valve shell, a sealing assembly, a sealing plate, a rocker arm assembly and a split pin; the sealing assemblies are respectively arranged on two sides of the gate valve shell; the sealing plate is arranged between the two sealing assemblies; the sealing plate and the sealing assembly form a contact type mechanical seal; the sealing plate is connected with the rocker arm assembly; an output shaft of the electric mechanism is connected with the rocker arm assembly through a cotter pin; a cover plate is fixed at one end of the gate valve shell through a screw. The utility model has the advantages of guarantee that the process of refueling is sealed reliable, shorten the refueling time, reduce the dependence to personnel.
Description
Technical Field
The utility model relates to an aviation technical field, it is helicopter pressure refueling motorised valve that says so more specifically.
Background
The helicopter refueling process is a complex process, and the common refueling mode is gravity refueling. The oil filling port for gravity oil filling is arranged at the upper part of the oil tank, and oil liquid flows into the oil tank by gravity when oil is filled. Gravity refueling has the following problems:
(1) gravity refueling is usually open refueling, a refueling port is communicated with the atmosphere, foreign objects can easily enter an oil tank, and the oil is polluted;
(2) the gravity refueling needs to visually check whether the fuel is full, and the visual check of the liquid level is easy to cause larger errors;
(3) the gravity refueling is to refuel by depending on the self gravity of fuel, so that the refueling speed is slow, and the combat readiness time is influenced;
(4) the demand on the number of personnel is high by gravity refueling.
In summary, the gravity refueling process is complicated. Therefore, the helicopter refueling process is convenient, safe and reliable; the pressure refueling device for the helicopter, which ensures reliable sealing in the refueling process and shortens the refueling time, is urgently needed to be developed.
Disclosure of Invention
The utility model aims at providing a helicopter pressure oiling electric valve which ensures reliable sealing in the oiling process, shortens the oiling time and reduces the dependence on personnel; the utility model is suitable for an among the helicopter pressure refueling system pipeline, realize the switch-on or cut off pressure oil feeding pipeline through the valve switching, still have the pressure release function after the valve is closed, avoid the pressure oil feeding pipeline inner enclosed fuel to make the system superpressure because of the thermal energy.
In order to realize the purpose, the technical scheme of the utility model is that: helicopter pressure refuels motorised valve, its characterized in that: comprises an electric mechanism and a gate valve; the gate valve comprises a gate valve shell, a sealing assembly, a sealing plate, a rocker arm assembly and a split pin;
the sealing assemblies are respectively arranged on two sides of the gate valve shell; the sealing plate is arranged between the two sealing assemblies; the sealing plate and the sealing assembly form a contact type mechanical seal; the sealing plate is connected with the rocker arm assembly;
an output shaft of the electric mechanism is connected with the rocker arm assembly through a cotter pin;
a cover plate is fixed at one end of the gate valve shell through a screw.
In the above technical solution, there is a first O-ring seal disposed at the connection between the insert plate valve housing and the cover plate.
The seal assembly comprises a seal housing and a seal ring; the sealing ring is arranged inside the sealing shell;
a second O-shaped sealing ring is arranged outside the sealing ring;
a disc spring is arranged between the sealing shell and the sealing ring;
a gasket is arranged between the sealing ring and the disc spring;
a third O-ring seal is mounted on the exterior of the seal housing.
The rocker arm assembly comprises a bearing and a rocker arm; a semi-hollow rivet is arranged at the joint of the bearing and the rocker arm; the bearing is arranged at one end of the rocker arm through a semi-hollow rivet;
a kidney-shaped groove is arranged in the sealing plate;
the bearing is mounted in the kidney slot.
In the technical scheme, the electric mechanism comprises a direct current motor, a gear reduction device, a microswitch, a deflector rod, a clutch and an electric mechanism output shaft;
the output shaft of the electric mechanism is arranged on the direct current motor;
the gear reduction device is mounted on the output shaft of the electric mechanism; the clutch is arranged in the gear reduction device; the clutch is connected with the output shaft of the electric mechanism through a flat key; one end of the output shaft of the electric mechanism is provided with the deflector rod; the two sides of the driving lever are respectively provided with one microswitch;
the upper shell components are arranged outside the micro switch and the electric mechanism;
and the upper shell assembly is provided with a filter, and the filter is provided with an electric connector.
In the technical scheme, a safety valve is integrated in the flashboard valve shell.
The utility model has the advantages of as follows:
(1) the utility model mainly adopts an electric mechanism to drive the opening and closing of the gate valve, and the whole process is closed when pressure oiling is carried out, thus ensuring reliable sealing;
(2) the oil full signal of the utility model is the electric signal output without visual inspection; the helicopter is pressurized and oiled by higher pressure, so that the oiling time can be shortened; the pressure refueling of the utility model is controlled by electricity in the whole process, so that the requirement on the number of personnel is reduced;
(3) the utility model adopts the direct current motor to drive, thus ensuring the reliability of opening and closing the valve; the mechanical seal formed by the middle seal assembly and the seal plate ensures the sealing reliability of pressure oiling;
(4) the utility model has the advantages of simple structure, light weight, convenient maintenance, fast opening and closing speed, reliable sealing, etc.; the defects of easy pollution, large visual inspection error, low oiling speed and high personnel number requirement in the prior art are overcome;
(5) the mechanical seal formed by the sealing plate and the sealing component ensures the sealing reliability of the oiling process, and simultaneously, the pressure oiling pipeline is switched on or switched off by the electric signal of the electric connector, so that the oiling time is shortened, and the dependence on personnel is reduced; and simultaneously, the utility model discloses the inside integration of picture peg valve casing has the relief valve, has the pressure release function for the push-pull valve still has the pressure release function after closing, avoids pressure to add the interior confined fuel of oil pipe way and makes the overpressure of system because of the thermal energy.
Drawings
Fig. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a schematic structural view of the middle electric mechanism of the present invention.
Fig. 3 is a schematic structural view of the middle gate valve of the present invention.
Fig. 4 is a schematic structural diagram of the middle sealing assembly of the present invention.
Fig. 5 is a schematic structural diagram of the middle rocker arm assembly of the present invention.
Fig. 6 is a schematic view of the opening and closing positions of the middle gate valve of the present invention.
Fig. 7 is a sectional view taken along line a-a of fig. 6.
In the figure, 1-an electric mechanism, 1.1-a direct current motor, 1.2-a gear reduction device, 1.3-a microswitch, 1.4-a deflector rod, 1.5-a clutch, 1.6-an electric mechanism output shaft, 1.7-an upper shell component, 1.8-a filter, 1.9-an electric connector, 2-a gate valve, 2.1-a gate valve shell, 2.1.1-a sealing shell, 2.1.2-a disc spring, 2.1.3-a sealing ring, 2.1.4-a gasket, 2.1.5-a second O-type sealing ring, 2.1.6-a third O-type sealing ring, 2.1.7-a safety valve, 2.2-a sealing component, 2.3-a sealing plate, 2.3.1-a kidney groove, 2.4-a rocker arm component, 2.4.1-a bearing, 2.4.2-a half hollow rivet, 2.4.3-a rocker arm, 2.5-an opening pin, 2.6-a cover plate, 2.7-a screw, 2.8-first O-ring seal.
Detailed Description
The following detailed description of the embodiments of the present invention will be made with reference to the accompanying drawings, which are not intended to limit the present invention, but are merely exemplary. While the advantages of the invention will be clear and readily appreciated by the description.
With reference to the accompanying drawings: the helicopter pressure refueling electric valve comprises an electric mechanism 1 and a gate valve 2; the motor drives the gate valve 2 to open and close, and the whole process is closed when pressure oiling is carried out, so that reliable sealing is ensured; meanwhile, the full oil signal is output as an electric signal, and visual inspection is not needed; the gate valve 2 comprises a gate valve shell 2.1, a sealing assembly 2.2, a sealing plate 2.3, a rocker arm assembly 2.4 and a cotter pin 2.5;
the two sides of the flashboard valve shell 2.1 are respectively provided with one sealing component 2.2; the sealing plate 2.3 is arranged between the two sealing components 2.2; the sealing plate 2.3 and the sealing component 2.2 form a contact type mechanical seal, so that the sealing reliability of the whole pressure oiling process can be ensured;
the sealing plate 2.3 is connected with the rocker arm assembly 2.4;
an output shaft of the electric mechanism 1 is connected with a rocker arm component 2.4 in the gate valve 2 through a cotter pin 2.5; the rocker arm component 2.4 drives the sealing plate 2.3 to do reciprocating linear motion to control the opening and closing of the gate valve 2;
a cover plate 2.6 is fixed at one end of the flashboard valve shell 2.1 through a bolt 2.7 (shown in figures 1, 3 and 4); the sealing performance of the gate valve 2 is ensured.
Furthermore, a first O-shaped sealing ring 2.8 is arranged at the joint of the gate valve shell 2.1 and the cover plate 2.6; the shell and the cover plate are sealed by an O-shaped sealing ring 2.8.
Further, the sealing assembly 2.2 comprises a sealing housing 2.1.1 and a sealing ring 2.1.3; the sealing ring 2.1.3 is arranged inside the sealing shell 2.1.1;
a second O-shaped sealing ring 2.1.5 is arranged outside the sealing ring 2.1.3; the sealing performance of the sealing shell 2.1.1 and the sealing ring 2.1.3 is ensured;
a disc spring 2.1.2 is arranged between the sealing shell 2.1.1 and the sealing ring 2.1.3; a gasket 2.1.4 is arranged between the sealing ring 2.1.3 and the disc spring 2.1.2; the force value of the disc spring 2.1.2 is properly adjusted through the adjusting gasket 2.1.4;
a third O-ring 2.1.6 is mounted on the outside of the seal housing 2.1.1 (as shown in fig. 3 and 4).
Further, the rocker arm assembly 2.4 comprises a bearing 2.4.1 and a rocker arm 2.4.3; a semi-hollow rivet 2.4.2 is arranged at the joint of the bearing 2.4.1 and the rocker arm 2.4.3; the bearing 2.4.1 is arranged at one end of the rocker arm 2.4.3 through a semi-hollow rivet 2.4.2; the bearing 2.4.1 is connected with the rocker arm 2.4.3 through a semi-hollow rivet 2.4.2;
the bearing 2.4.1 is arranged in a kidney-shaped groove 2.3.1 of the sealing plate 2.3 (as shown in figures 3 and 5); the rocker arm assembly 2.4 drives the sealing plate 2.3 to perform reciprocating linear motion, and controls the opening and closing of the gate valve 2 (as shown in fig. 6).
Further, the electric mechanism 1 comprises a direct current motor 1.1, a gear reduction device 1.2, a microswitch 1.3, a deflector rod 1.4, a clutch 1.5 and an electric mechanism output shaft 1.6;
the electric mechanism output shaft 1.6 is arranged on the direct current motor 1.1;
the gear reduction device 1.2 is arranged on the electric mechanism output shaft 1.6; the direct current motor 1.1 is driven by the gear reduction device 1.2;
the clutch 1.5 is arranged in the gear reduction device 1.2, so that the clutch and the gear reduction device are integrated into a whole, and the clutch can protect the motor during overload;
the clutch 1.5 is connected with the electric mechanism output shaft 1.6 through a flat key; one end of the output shaft 1.6 of the electric mechanism is provided with the deflector rod 1.4; two sides of the driving lever 1.4 are respectively provided with one microswitch 1.3;
the micro switch 1.3 and the electric mechanism 1 are externally provided with an upper shell assembly 1.7;
and the upper shell assembly 1.7 is provided with a filter, and the filter is provided with an electric connector.
Further, a safety valve 2.1.7 (shown in fig. 6 and 7) is integrated in the gate valve housing 2.1, and the safety valve has a pressure relief function, so that overpressure of the system caused by thermal expansion of fuel sealed in a pressure fuel filling pipeline is avoided.
Helicopter pressure refuel motorised valve's theory of operation be: the output shaft of the electric mechanism 1 drives the rocker arm component 2.4 to do rotary motion, and the rocker arm 2.4.3 drives the sealing plate 2.3 to do reciprocating linear motion, so that the on-off of the pressure oil filling pipeline is realized. The included angle of the two swinging limit positions of the rocker arm 2.4.3 is 90 degrees, when the electric mechanism works, a system provides an opening signal, an output shaft of the electric mechanism 1 rotates clockwise (facing to the output shaft end of the electric mechanism, the lower part is the same), meanwhile, the rocker arm 2.4.3 swings clockwise to drive the sealing plate 2.3 to move rightwards to execute an opening action, when the sealing plate 2.3 is fully opened in place, the limit switch outputs a fully opened in place signal, and meanwhile, a direct current motor of the electric mechanism 1 is powered off to stop working; when a closing signal is provided, the output shaft of the electric mechanism 1 rotates anticlockwise, meanwhile, the rocker arm 2.4.3 swings anticlockwise to drive the sealing plate 2.3 to move leftwards to execute a closing action, when the sealing plate 2.3 is completely closed in place, the limit switch outputs a complete closing in place signal, and meanwhile, the direct current motor of the electric mechanism 1 is powered off and stops working. The utility model discloses be equipped with relief valve 2.1.7, when confined fuel when the pressure pipeline steps up to the set pressure value because of the thermal energy, relief valve 2.1.7 is opened and is exported the pressure release, avoids the overpressure of system.
In order to illustrate more clearly the helicopter pressure refueling motorised valve compare the advantage that has with prior art, the staff has compared these two kinds of technical scheme, and its comparison result is as follows:
can know by last table helicopter pressure refuel motorised valve compare with prior art, adopt sealed, pressure to refuel to the helicopter, refuel fastly, realize the switch-on or cut off pressure oil feeding pipeline through the signal of telecommunication, reduce the dependence to personnel.
Other parts not described belong to the prior art.
Claims (6)
1. Helicopter pressure refuels motorised valve, its characterized in that: comprises an electric mechanism (1) and a gate valve (2); the gate valve (2) comprises a gate valve shell (2.1), a sealing assembly (2.2), a sealing plate (2.3), a rocker arm assembly (2.4) and a split pin (2.5);
the two sides of the flashboard valve shell (2.1) are respectively provided with one sealing component (2.2); the sealing plate (2.3) is arranged between the two sealing components (2.2); the sealing plate (2.3) and the sealing component (2.2) form a contact type mechanical seal; the sealing plate (2.3) is connected with the rocker arm assembly (2.4);
an output shaft of the electric mechanism (1) is connected with the rocker arm component (2.4) through a cotter pin (2.5);
a cover plate (2.6) is fixed at one end of the flashboard valve shell (2.1) through a screw (2.7).
2. The helicopter pressure refuelling electrically operated valve of claim 1, characterized in that: a first O-shaped sealing ring (2.8) is arranged at the joint of the flashboard valve shell (2.1) and the cover plate (2.6).
3. The helicopter pressure refuelling electro-valve according to claim 1 or 2, characterized in that: the sealing assembly (2.2) comprises a sealing shell (2.1.1) and a sealing ring (2.1.3); the sealing ring (2.1.3) is mounted inside the sealing housing (2.1.1);
a second O-shaped sealing ring (2.1.5) is arranged outside the sealing ring (2.1.3);
a disc spring (2.1.2) is arranged between the sealing shell (2.1.1) and the sealing ring (2.1.3);
a gasket (2.1.4) is arranged between the sealing ring (2.1.3) and the disc spring (2.1.2);
a third O-shaped sealing ring (2.1.6) is arranged outside the sealing shell (2.1.1).
4. The helicopter pressure refuelling electrically operated valve of claim 3, characterized in that: the rocker arm assembly (2.4) comprises a bearing (2.4.1) and a rocker arm (2.4.3); a semi-hollow rivet (2.4.2) is arranged at the joint of the bearing (2.4.1) and the rocker arm (2.4.3); the bearing (2.4.1) is arranged at one end of the rocker arm (2.4.3) through a semi-hollow rivet (2.4.2);
a kidney-shaped groove (2.3.1) is arranged in the sealing plate (2.3);
the bearing (2.4.1) is mounted in the kidney slot (2.3.1).
5. The helicopter pressure refueling electro-valve of claim 4, characterized in that: the electric mechanism (1) comprises a direct current motor (1.1), a gear reduction device (1.2), a microswitch (1.3), a deflector rod (1.4), a clutch (1.5) and an electric mechanism output shaft (1.6);
the electric mechanism output shaft (1.6) is arranged on the direct current motor (1.1);
the gear reduction device (1.2) is mounted on the electric mechanism output shaft (1.6); the clutch (1.5) is arranged in the gear reduction device (1.2); the clutch (1.5) is connected with the electric mechanism output shaft (1.6) through a flat key; one end of the output shaft (1.6) of the electric mechanism is provided with the deflector rod (1.4); the two sides of the driving lever (1.4) are respectively provided with one microswitch (1.3);
an upper shell assembly (1.7) is arranged outside the microswitch (1.3) and the electric mechanism (1);
and a filter (1.8) is arranged on the upper shell component (1.7), and an electric connector (1.9) is arranged on the filter (1.8).
6. The helicopter pressure refueling electro-valve of claim 5, characterized in that: and a safety valve (2.1.7) is integrated in the flashboard valve shell (2.1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020689969.5U CN212377334U (en) | 2020-04-29 | 2020-04-29 | Helicopter pressure refueling electric valve |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020689969.5U CN212377334U (en) | 2020-04-29 | 2020-04-29 | Helicopter pressure refueling electric valve |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212377334U true CN212377334U (en) | 2021-01-19 |
Family
ID=74161746
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020689969.5U Active CN212377334U (en) | 2020-04-29 | 2020-04-29 | Helicopter pressure refueling electric valve |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212377334U (en) |
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2020
- 2020-04-29 CN CN202020689969.5U patent/CN212377334U/en active Active
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