阅读说明：本技术 直升机压力加油电动阀 (Helicopter pressure refueling electric valve ) 是由 张月 王启龙 于 2020-04-29 设计创作，主要内容包括：本发明公开了一种直升机压力加油电动阀。它包括电动机构和插板阀；所述插板阀包括插板阀壳体、密封组件、密封板、摇臂组件和开口销；所述插板阀壳体两侧各安装一个所述密封组件；二个所述密封组件之间安装有所述密封板；密封板和密封组件组成接触式机械密封；所述密封板与所述摇臂组件连接；所述电动机构的输出轴通过开口销与所述摇臂组件连接；有盖板通过螺钉固定在所述插板阀壳体一端。本发明具有保证加油过程密封可靠、缩短加油时间、降低对人员的依赖的优点。(The invention discloses a helicopter pressure refueling electric 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 invention has the advantages of ensuring reliable sealing in the refueling process, shortening the refueling time and reducing the dependence on personnel.)

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).

Technical Field

The invention relates to the technical field of aviation, in particular to a helicopter pressure refueling electric valve.

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 invention aims to provide a helicopter pressure refueling electric valve, which ensures reliable sealing in a refueling process, shortens refueling time and reduces dependence on personnel; the invention is suitable for the pipeline of the helicopter pressure refueling system, the pressure refueling pipeline is switched on or off by opening and closing the valve, and the valve also has the pressure relief function after being closed, so that the overpressure of the system caused by the thermal expansion of the fuel oil sealed in the pressure refueling pipeline is avoided.

In order to achieve the purpose, the technical scheme of the invention is as follows: 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 method of claim, wherein: 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 method of claim, wherein: 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 invention has the following advantages:

(1) the electric mechanism is mainly adopted to drive the opening and closing of the gate valve, and the whole process is closed during pressure oiling, so that the sealing reliability is ensured;

(2) the full oil signal is output as an electric signal, and visual inspection is not needed; the helicopter is pressurized and oiled by higher pressure, so that the oiling time can be shortened; the pressure refueling process is electrically controlled, so that the requirement on the number of personnel is reduced;

(3) the invention adopts the direct current motor for driving, thus ensuring the reliability of opening and closing the valve; the mechanical seal formed by the seal assembly and the seal plate ensures the sealing reliability of pressure refueling;

(4) the invention has the advantages of simple structure, light weight, convenient maintenance, high opening and closing speed, reliable sealing and the like; 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 assembly ensures reliable sealing in the oiling process, and meanwhile, the pressure oiling pipeline is switched on or off by the electric signal of the electric connector, so that the oiling time is shortened, and the dependence on personnel is reduced; meanwhile, the safety valve is integrated in the flashboard valve shell, and the flashboard valve has a pressure relief function, so that the flashboard valve also has the pressure relief function after being closed, and the overpressure of a system caused by the thermal expansion of fuel oil sealed in a pressure oil filling pipeline is avoided.

Drawings

FIG. 1 is a schematic structural diagram of the present invention.

Fig. 2 is a schematic structural diagram of the electric mechanism of the present invention.

Fig. 3 is a schematic structural view of the gate valve of the present invention.

Fig. 4 is a schematic structural view of the seal assembly of the present invention.

Fig. 5 is a schematic structural view of the rocker arm assembly of the present invention.

FIG. 6 is a schematic view of the open and closed positions of the 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 embodiments of the present invention will be described in detail 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 understood 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.

The working principle of the helicopter pressure oiling electric valve is as follows: 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 invention is provided with the safety valve 2.1.7, when the closed fuel in the pressure pipeline is boosted to a set pressure value due to thermal expansion, the safety valve 2.1.7 is opened to release pressure to the outlet, and the overpressure of the system is avoided.

In order to more clearly illustrate the advantages of the helicopter pressure refueling electric valve of the present invention compared with the prior art, the two technical solutions are compared by the staff, and the comparison results are as follows:

compared with the prior art, the helicopter pressure oiling electric valve disclosed by the invention has the advantages that the helicopter is hermetically and pressure oiled, the oiling speed is high, the pressure oiling pipeline is switched on or off through an electric signal, and the dependence on personnel is reduced.

Other parts not described belong to the prior art.