Wet wing refueling system for aircraft

Abstract

The present invention belongs to the technical field of aircraft refueling, and specifically discloses a wet wing refueling system for aircraft, including a base, a pipeline assembly, an explosion-proof oil unloading pump and a filter separator, wherein the pipeline assembly, the explosion-proof oil unloading pump and the filter separator are all fixed on the base, the pipeline assembly includes an oil inlet pipe and an oil outlet pipe, the filter separator is connected between the oil inlet pipe and the oil outlet pipe, the inlet pressure of the oil inlet pipe is ≤0.15Mpa, and the outlet pressure of the oil outlet pipe is 0.345Mpa≤P≤0.375Mpa. By adopting the scheme of the present invention, by integrating the base, the pipeline assembly, the explosion-proof oil unloading pump and the filter separator into a refueling system, the refueling system can be carried by a large aircraft, so that in wartime or emergency situations, the refueling system provided by the scheme can realize temporary oil transfer between a large aircraft and an aircraft (small aircraft), thereby effectively coping with ground refueling under special circumstances, and supplementing the current ground refueling method.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft refueling, and in particular relates to a wet wing refueling system for an aircraft. Background Art

[0002] There are two main ways to refuel aircraft: aerial refueling and ground refueling. Whether it is a fighter, bomber, transport aircraft or helicopter, they usually have the ability to refuel in the air. Ground refueling includes gravity refueling and pressure refueling. Gravity refueling refers to the fuel refueling method in which the fuel flows into the aircraft from the refueling port on the top of the fuel tank of a large aircraft by its own weight. Similarly, pressure refueling refers to the fuel refueling method in which the fuel is injected from the fuel supply pipeline or refueling truck into the aircraft tank or external tank through a pressure refueling connector.

[0003] The main advantages of pressure refueling over gravity refueling are that the fuel filling speed is fast, safe, and requires less manpower. Most of the current fighter jets are refueled through pressure refueling, and the pressure refueling method usually uses refueling trucks to supply fuel. However, for some special scenarios, such as wartime emergencies, road blockages, etc., the fuel supply of refueling trucks is blocked and cannot meet the fuel supply in such situations. Based on this, the present application provides a wet wing refueling system for aircraft, which realizes temporary oil transfer between large aircraft and aircraft in wartime or emergency situations, so as to improve the ground refueling method of aircraft under special circumstances. Summary of the invention

[0004] In view of the deficiencies in the prior art, the present invention provides a wet-wing refueling system for aircraft, which enables temporary oil transfer between large aircraft and aircraft in wartime or emergency situations, so as to improve the ground refueling method of aircraft in special circumstances.

[0005] To achieve the above object, the present invention adopts the following technical solutions:

[0006] A wet wing refueling system for an aircraft comprises a base, a pipeline assembly, an explosion-proof oil unloading pump and a filter separator, wherein the pipeline assembly, the explosion-proof oil unloading pump and the filter separator are all fixed on the base, the pipeline assembly comprises an oil inlet pipe and an oil outlet pipe, the filter separator is connected between the oil inlet pipe and the oil outlet pipe, the inlet pressure of the oil inlet pipe is ≤0.15Mpa, and the outlet pressure of the oil outlet pipe is 0.345Mpa≤P≤0.375Mpa.

[0007] Compared with the prior art, the present invention has the following beneficial effects:

[0008] In this solution, a refueling system is integrated with a base, a pipeline assembly, an explosion-proof oil unloading pump and a filter separator. The refueling system can be carried by a large aircraft. In this way, in wartime or emergency situations, the refueling system provided by this solution can achieve temporary oil transfer between large aircraft and aircraft (small aircraft), thereby effectively coping with ground refueling in special circumstances and supplementing the current ground refueling method.

[0009] Furthermore, the base includes a rectangular frame, casters are installed at the bottom of the frame, and a number of limit members are provided on the frame. The limit members include a screw and a limit plate, and the limit plate is fixed to the bottom of the screw. The screw is threadedly connected to the frame, and the screw is threadedly connected to locking nuts located on the upper and lower sides of the frame. The frame is also provided with a number of columns.

[0010] Beneficial effects: On the one hand, the base arranged in this way can move freely, and on the other hand, during operation, the limit plate can be pressed tightly against the ground by adjusting the screw rod, thereby improving the stability of the base.

[0011] Furthermore, the oil inlet of the oil inlet pipe and the oil outlet of the oil outlet pipe are both connected to aviation oil delivery pressure joints.

[0012] Beneficial effect: This ensures that the connector can be matched with the connectors at the large aircraft end and the small aircraft end through the pipeline.

[0013] Furthermore, a flow meter is provided on the oil inlet pipe, and a pressure detection sensor is provided at the oil outlet of the oil outlet pipe.

[0014] Beneficial effects: The flow rate of the oil supply can be accurately controlled by the flow meter, and the pressure of the oil outlet can be detected by the pressure detection sensor to ensure the safety of the oil transfer process.

[0015] Furthermore, a valve I is provided at the oil inlet of the oil inlet pipe, a valve II is provided at the oil outlet of the oil inlet pipe, and a valve III is provided on the oil outlet pipe.

[0016] Beneficial effect: The flow rate and pressure of the oil inlet pipe and the oil outlet pipe can be adjusted by setting multiple valves.

[0017] Furthermore, it also includes an oil and gas recovery component, which includes a first pressure relief exhaust pipe, a second pressure relief exhaust pipe, an explosion-proof oil pump and an oil tank. The first pressure relief exhaust pipe is connected to the oil inlet of the oil inlet pipe, and the first pressure relief exhaust pipe is connected to the explosion-proof oil pump. The first pressure relief exhaust pipe is provided with a valve IV close to the oil inlet and a valve VII close to the explosion-proof oil pump. The second pressure relief exhaust pipe connects the oil outlet pipe and the oil tank. An intermediate pipe is connected between the first pressure relief exhaust pipe and the second pressure relief exhaust pipe. The second pressure relief exhaust pipe is provided with a valve V, a valve VI and a valve VIII. The valve V is arranged close to the intermediate pipe, the valve VI is arranged close to the oil outlet pipe, and the valve VIII is arranged close to the oil tank.

[0018] Beneficial effect: This arrangement can discharge the pressure and residual fuel in the pipelines at the large aircraft end and the small aircraft end into the fuel tank, or extract the fuel in the pipelines through an explosion-proof oil pump.

[0019] Furthermore, the oil and gas recovery component also includes a third pressure relief exhaust pipe, which is connected to the filter separator and the oil tank. A valve IX is provided at the discharge port of the oil tank. A drain pipe is provided on the filter separator, and a valve X is provided on the drain pipe.

[0020] Beneficial effect: In this way, the residual oil and gas in the filter separator can be depressurized into the oil tank, and the oil dirt is discharged from the drain pipe.

[0021] Furthermore, it also includes an explosion-proof distribution box and a fire extinguisher, both of which are fixed on the base, and the explosion-proof oil unloading pump and the explosion-proof oil pump are powered by the explosion-proof distribution box.

[0022] Beneficial effect: This arrangement can improve the safety of the explosion-proof oil unloading pump and the explosion-proof oil pump in the refueling system. In addition, the configuration of the fire extinguisher can be used quickly in the event of a fire, thereby reducing losses. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 The figure is a schematic diagram of a flow chart of an embodiment of a wet wing refueling system for an aircraft according to the present invention.

[0024] Figure 2 It is an isometric view of an embodiment of a wet wing refueling system for an aircraft according to the present invention.

[0025] Figure 3 It is an axonometric view of a base in an embodiment of a wet wing refueling system for an aircraft according to the present invention.

[0026] The figure marks in the drawings of the specification include: small aircraft end 1, large aircraft end 2, base 10, explosion-proof oil unloading pump 11, filter separator 12, explosion-proof distribution box 13, fire extinguisher 14, frame 101, casters 102, screw 103, limit plate 104, locking nut 105, oil inlet pipe 15, oil outlet pipe 16, aviation oil delivery pressure joint 17, valve I 18, valve II 19, valve III 20, first pressure relief exhaust pipe 21, second pressure relief exhaust pipe 22, third pressure relief exhaust pipe 23, explosion-proof oil pump 24, oil tank 25, valve IV 26, valve VII 27, safety valve 28, intermediate pipe 29, valve V 30, valve VI 31, valve VIII 32, valve IX 33, valve X 34, oil bag 35. DETAILED DESCRIPTION

[0027] The present invention is further described in detail below with reference to the accompanying drawings, and specific implementation methods are given.

[0028] The embodiment is basically as follows Figure 1 , Figure 2 and Figure 3 As shown, the wet wing refueling system for an aircraft includes a base 10, a pipeline assembly, an explosion-proof oil unloading pump 11, a filter separator 12, an explosion-proof distribution box 13, a fire extinguisher 14, and an oil and gas recovery assembly. The pipeline assembly, the explosion-proof oil unloading pump 11, the filter separator 12, the explosion-proof distribution box 13, the fire extinguisher 14, and the oil and gas recovery assembly are all fixedly installed on the base 10.

[0029] The model of the explosion-proof oil unloading pump 11 in this embodiment is: CZB80-40 / 40; flow rate: 45m 3 / h; lift: 40m; motor power: 5.5Kw; suction lift: 7m.

[0030] In this embodiment, the base 10 includes a rectangular frame 101, and casters 102 are installed at the four top corners at the bottom of the frame 101. A number of limit members are also provided on the frame 101. In this embodiment, the limit members include a screw 103 and a limit plate 104, wherein the limit plate 104 is fixed to the bottom of the screw 103, and the screw 103 is threadedly connected to the frame 101. The screw 103 is threadedly connected to the locking nut 105 located on the upper and lower sides of the frame 101; a number of columns are also provided on the frame 101 for supporting other components.

[0031] In this embodiment, the pipeline assembly includes an oil inlet pipe 15 and an oil outlet pipe 16, and the filter separator 12 is connected between the oil inlet pipe 15 and the oil outlet pipe 16. The oil inlet of the oil inlet pipe 15 and the oil outlet of the oil outlet pipe 16 are both connected with an aviation fuel pressure joint 17. In this embodiment, the inlet pressure of the oil inlet pipe 15 is ≤0.15Mpa, and the outlet pressure of the oil outlet pipe 16 is 0.345Mpa≤P≤0.375Mpa; in this embodiment, the oil inlet pipe 15 includes an oil inlet pipe I, an oil inlet pipe II and an oil inlet pipe III, and the oil inlet pipe I, the oil inlet pipe II and the oil inlet pipe III are respectively connected by pipeline flanges. A flow meter is provided on the oil inlet pipe I, an explosion-proof oil unloading pump 11 is connected to the oil inlet pipe II, and the oil inlet pipe III is connected to the filter separator 12.

[0032] A pressure detection sensor is provided at the oil outlet of the oil outlet pipe 16. When the pressure exceeds the threshold, an audible and visual alarm is issued. A valve I 18 is provided at the oil inlet of the oil inlet pipe 15, a valve II 19 is provided at the oil outlet of the oil inlet pipe, and a valve III 20 is provided on the oil outlet pipe.

[0033] In this embodiment, the oil and gas recovery assembly includes a first pressure relief exhaust pipe 21, a second pressure relief exhaust pipe 22, a third pressure relief exhaust pipe 23, an explosion-proof oil pump 24 and an oil tank 25, wherein the explosion-proof oil pump 24 has a model of 20GZB-3 / 2.5K, a flow rate of 50L / min, a head of 20m, and a suction range of 5M. The explosion-proof oil unloading pump 11 and the explosion-proof oil pump 24 are both powered by an explosion-proof distribution box 13.

[0034] The first pressure relief exhaust pipe 21 is connected to the oil inlet of the oil inlet pipe 15, and the first pressure relief exhaust pipe 21 is connected to the explosion-proof oil pump 24. A valve IV 26 close to the oil inlet and a valve VII 27 close to the explosion-proof oil pump are provided on the first pressure relief exhaust pipe 21. A safety valve 28 located between the valve IV 26 and the valve VII 27 is also provided on the first pressure relief exhaust pipe 21. When the pressure at the oil inlet exceeds 0.375 MPa, the safety valve 28 performs pressure relief protection to ensure that the pressure at the oil inlet is below 0.375 MPa.

[0035] The second pressure relief exhaust pipe 22 connects the oil outlet pipe 26 and the oil tank 25. An intermediate pipe 29 is connected between the first pressure relief exhaust pipe 21 and the second pressure relief exhaust pipe 22. A valve V30, a valve VI31 and a valve VIII32 are provided on the second pressure relief exhaust pipe 22, wherein the valve V30 is arranged close to the intermediate pipe 29, the valve VI31 is arranged close to the oil outlet pipe 16, and the valve VIII32 is arranged close to the oil tank 25. The third pressure relief exhaust pipe 23 connects the filter separator 12 and the oil tank 25. A valve IX33 is provided at the discharge port of the oil tank 25. A sewage pipe is provided on the filter separator 12, and a valve X34 is provided on the sewage pipe. When the oil and gas recovery assembly is in use, the explosion-proof oil pump 24 is also connected to an oil bag 35.

[0036] The working principles of oil transfer, pressure relief and oil discharge in this embodiment are shown in Table 1 below.

[0037] Table 1 shows the working principle of oil transfer, pressure relief and oil discharge.

[0038]

[0039] ① The process of transferring oil from the large aircraft end 2 to the small aircraft end 1 is as follows: open valves Ⅰ, Ⅱ, Ⅲ, Ⅳ and VI, close valves Ⅴ, Ⅶ, Ⅷ, IX and X, start the explosion-proof oil unloading pump, and transfer the fuel from the large aircraft end 2 to the small aircraft end 1.

[0040] ② Pressure relief of the pipeline at the large aircraft end 2: Open valves IV and VIII, and close other valves. This will allow the pressure in the pipeline at the large aircraft end 2 to be unloaded into the fuel tank.

[0041] ③ Pressure relief of the pipeline at the small aircraft end 1: Open valves V, VII and VIII, and close other valves. This will release the pressure in the pipeline at the small aircraft end 1 into the fuel tank.

[0042] ④ Drain oil from the pipeline at the large aircraft end 2: Open valves IV and VII, close other valves, and use an explosion-proof oil pump to pump the oil and gas in the pipeline at the large aircraft end 2 into the oil bag.

[0043] ⑤ Drain oil from the pipeline at the small aircraft end 1: Open valves V, VI and VII, close other valves, and use an explosion-proof oil pump to pump the oil and gas in the pipeline at the small aircraft end 1 into the oil bag.

[0044] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device.

[0045] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that the technical solution of the present invention can be modified or replaced by equivalents without departing from the purpose and scope of the technical solution of the present invention, which should be included in the scope of the claims of the present invention.

Claims

1. A wet wing refueling system for an aircraft, characterized in that: It includes a base, a pipeline assembly, an explosion-proof oil unloading pump and a filter separator, wherein the pipeline assembly, the explosion-proof oil unloading pump and the filter separator are all fixed on the base, the pipeline assembly includes an oil inlet pipe and an oil outlet pipe, the explosion-proof oil unloading pump is connected to the oil inlet pipe, the filter separator is connected between the oil inlet pipe and the oil outlet pipe, the inlet pressure of the oil inlet pipe is ≤0.15Mpa, and the outlet pressure of the oil outlet pipe is 0.345Mpa≤P≤0.375Mpa; The oil inlet of the oil inlet pipe is provided with a valve I, the oil outlet of the oil inlet pipe is provided with a valve II, and the oil outlet pipe is provided with a valve III; The system also includes an oil and gas recovery component, which includes a first pressure relief exhaust pipe, a second pressure relief exhaust pipe, an explosion-proof oil pump and an oil tank. The first pressure relief exhaust pipe is connected to the oil inlet of the oil inlet pipe, the first pressure relief exhaust pipe is connected to the explosion-proof oil pump, the first pressure relief exhaust pipe is provided with a valve IV close to the oil inlet and a valve VII close to the explosion-proof oil pump, the second pressure relief exhaust pipe is connected to the oil outlet pipe and the oil tank, an intermediate pipe is connected between the first pressure relief exhaust pipe and the second pressure relief exhaust pipe, the second pressure relief exhaust pipe is provided with a valve V, a valve VI and a valve VIII, the valve V is arranged close to the intermediate pipe, the valve VI is arranged close to the oil outlet pipe, and the valve VIII is arranged close to the oil tank; The oil and gas recovery component also includes a third pressure relief exhaust pipe, which is connected to the filter separator and the oil tank. A valve IX is provided at the discharge port of the oil tank. A sewage pipe is provided on the filter separator, and a valve X is provided on the sewage pipe.

2. The wet wing refueling system for an aircraft according to claim 1, characterized in that: The base includes a rectangular frame, casters are installed at the bottom of the frame, and a plurality of limit members are provided on the frame. The limit members include a screw and a limit plate, and the limit plate is fixed to the bottom of the screw. The screw is threadedly connected to the frame, and locking nuts located on the upper and lower sides of the frame are threadedly connected to the screw. The frame is also provided with a plurality of columns.

3. The wet wing refueling system for an aircraft according to claim 1, characterized in that: The oil inlet of the oil inlet pipe and the oil outlet of the oil outlet pipe are both connected with an aviation oil delivery pressure joint.

4. The wet wing refueling system for an aircraft according to claim 3, characterized in that: A flow meter is arranged on the oil inlet pipe, and a pressure detection sensor is arranged at the oil outlet of the oil outlet pipe.

5. The wet wing refueling system for an aircraft according to claim 4, characterized in that: It also includes an explosion-proof distribution box and a fire extinguisher. The explosion-proof distribution box and the fire extinguisher are both fixed on the base. The explosion-proof oil unloading pump and the explosion-proof oil pump are both powered by the explosion-proof distribution box.

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