CN105015793A - Aircraft refueling system and aircraft comprising same - Google Patents

Abstract

The invention discloses an aircraft refueling system and an aircraft comprising the same. The aircraft refueling system comprises a refueling connector (1) and an oil tank assembly (3) connected with the refueling connector (1) through a pipeline (2), and further comprises a stop valve (4) arranged in the pipeline (2) between the refueling connector (1) and the oil tank assembly (3), and the stop valve (4) is electrically connected with a refueling control panel and controlled by the refueling control panel. The stop valve (4) is used for switching on or off the pipeline (2). In the aircraft refueling system, the stop valve is arranged in the pipeline between the refueling connector and the oil tank assembly, electrically connected with the refueling control panel, controlled by the refueling control panel and used for switching on or off the pipeline. Control is achieved through the stop valve, the problem that the number of components of the aircraft refueling system is large is solved, and compared with the prior art, control is easy, and the weight is small.

Description

An aircraft refueling system and an aircraft having the same

technical field

The invention relates to the field of aviation technology, in particular to an aircraft refueling system and an aircraft with the same.

Background technique

In the prior art, the aircraft refueling system has many specific components, which brings many fault points, complicated control, heavy weight and other disadvantages.

Therefore, it is desirable to have a technical solution to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.

Contents of the invention

It is an object of the present invention to provide an aircraft refueling system that overcomes or at least alleviates at least one of the above-mentioned drawbacks of the prior art.

To achieve the above object, the present invention provides an aircraft refueling system. The aircraft refueling system includes a refueling joint and a fuel tank assembly connected to the refueling joint through a pipeline. The aircraft refueling system further includes: a shut-off valve, which is arranged between the refueling joint and the fuel tank assembly. In the pipeline between the components, and the cut-off valve is electrically connected with the refueling control panel and is controlled by the refueling control panel; the cut-off valve is used to open and close the pipeline.

Preferably, the shut-off valve is an electromagnetic shut-off valve.

Preferably, the shut-off valve is an electric shut-off valve.

Preferably, the shut-off valve is a ball valve.

Preferably, the fuel tank assembly includes a plurality of fuel tanks with partitions, the pipelines include multiple branch pipelines, each branch pipeline extends into one of the fuel tanks, and each branch pipeline is provided with a one-way valves, and the one-way valves are configured to allow oil to flow from the filling joints to each of the oil tanks.

Preferably, a diffusion port is provided at the end of each of the branch lines for limiting the flow rate of the oil passing through the diffusion port.

The present invention also provides an aircraft, which includes the above-mentioned aircraft refueling system.

In the aircraft refueling system of the present invention, the cut-off valve is arranged in the pipeline between the refueling joint and the fuel tank assembly, and the cut-off valve is electrically connected with the refueling control panel and is controlled by the refueling control panel; the cut-off valve is used to open and close the pipeline . The invention is controlled by a cut-off valve, which reduces the problem of many components in the aircraft refueling system. Compared with the prior art, the invention has simple control and relatively small weight.

Description of drawings

Fig. 1 is a schematic structural diagram of an aircraft refueling system according to an embodiment of the present invention.

Reference signs:

1 Refueling connector 31 tank 2 pipeline twenty one Branch pipeline 3 Fuel tank assembly twenty two check valve 4 Shut-off valve twenty three Diffusion port

Detailed ways

In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings.

In describing the present invention, it is to be understood that the terms "central", "longitudinal", "transverse", "front", "rear", "left", "right", "vertical", "horizontal", The orientations or positional relationships indicated by "top", "bottom", "inner", "outer", etc. are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying the Means that a device or element must have a specific orientation, be constructed and operate in a specific orientation, and therefore should not be construed as limiting the scope of the invention.

The aircraft refueling system of the present invention comprises a refueling joint, a fuel tank assembly and a cut-off valve, wherein the refueling joint is connected to the fuel tank assembly through a pipeline, the cut-off valve is arranged in the pipeline between the refueling joint and the fuel tank assembly, and the cut-off valve It is electrically connected with the refueling control panel and is controlled by the refueling control panel; the cut-off valve is used to switch on and off the pipeline.

In the aircraft refueling system of the present invention, the cut-off valve is arranged in the pipeline between the refueling joint and the fuel tank assembly, and the cut-off valve is electrically connected with the refueling control panel and is controlled by the refueling control panel; the cut-off valve is used to open and close the pipeline . The invention is controlled by a cut-off valve, which reduces the problem of many components in the aircraft refueling system. Compared with the prior art, the invention has simple control and relatively small weight.

Fig. 1 is a schematic structural diagram of an aircraft refueling system according to an embodiment of the present invention.

The aircraft fueling system shown in FIG. 1 includes a fueling joint 1 , a pipeline 2 , a fuel tank assembly 3 , and a shut-off valve 4 . Wherein, the refueling joint 1 is connected to the fuel tank assembly 3 through the pipeline 2, and the cut-off valve 4 is arranged in the pipeline 2 between the refueling joint 1 and the fuel tank assembly 3, and the cut-off valve 4 is connected to the refueling control panel (not shown in the figure). ) Electric union, controlled by the refueling control panel; the cut-off valve 4 is used for on-off pipeline 2. That is, the operator controls the opening and closing of the shut-off valve through the control panel.

In this embodiment, the shut-off valve 4 is an electromagnetic shut-off valve. That is, in this embodiment, by electromagnetic control.

It can be understood that other control methods can also be selected for the cut-off valve, that is, other types of cut-off valves can also be selected. For example, in an alternative embodiment, the cut-off valve is an electric cut-off valve, and in this case, it is controlled by an electric control method.

Advantageously, in this embodiment, the shut-off valve 4 is a ball valve. It can be understood that the cut-off valve can also adopt other configurations of valves. For example, needle valve etc.

The fuel tank assembly 3 includes a plurality of fuel tanks 31 with partitions, and the pipeline 2 includes a plurality of branch pipelines 21, and each branch pipeline 21 stretches into a fuel tank 31. In this embodiment, except the last fuel tank (Fig. 1 Outside the middle left fuel tank), each branch pipeline 21 is provided with a one-way valve 22, and the one-way valve 22 is set to make oil flow from the refueling joint to each fuel tank direction.

It can be understood that, in another alternative embodiment, the last oil tank (ie the oil tank into which oil flows into last) is provided with a one-way valve.

It should be noted that, in this application, the pipeline 2 refers to the pipeline connecting the refueling joint 1 and each fuel tank 31 in the fuel tank assembly 3 , rather than just including the pipeline between the fuel tank assembly 3 and the shut-off valve 4 .

In this embodiment, the number of oil tanks 31 is four. It can be understood that the number of oil tanks 31 can be set according to needs. For example, the number of fuel tanks is 1, 2, 3 or more.

Advantageously, in this embodiment, the end of each branch pipeline 21 is provided with a diffusion port 23 for limiting the flow rate of the oil passing through the diffusion port 23 . In this way, it can be ensured that the oil enters the oil tank according to the preset flow rate, thereby preventing the oil in the oil tank from generating shock waves.

The present invention also provides an aircraft, which includes the above-mentioned aircraft refueling system.

Finally, it should be pointed out that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that: they can still modify the technical solutions described in the aforementioned embodiments, or perform equivalent replacements for some of the technical features; and these The modification or replacement does not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims (7)

1. an aircraft refuelling system, the fuel tank assembly (3) that described aircraft refuelling system is comprised fueling connection (1) and is connected by pipeline (2) with described fueling connection (1), it is characterized in that, described aircraft refuelling system comprises further:

Shutoff valve (4), described shutoff valve (4) is arranged in the pipeline (2) between described fueling connection (1) and described fuel tank assembly (3), and described shutoff valve (4) and refueling control panel Electricity Federation, control by described refueling control panel; Described shutoff valve (4) is for pipeline described in break-make (2).

2. aircraft refuelling system as claimed in claim 1, it is characterized in that, described shutoff valve (4) is electromagnetic shut-off valve.

3. aircraft refuelling system as claimed in claim 1, it is characterized in that, described shutoff valve (4) is electronic shutoff valve.

4. as the aircraft refuelling system in claims 1 to 3 as described in any one, it is characterized in that, described shutoff valve (4) is ball valve.

5. aircraft refuelling system as claimed in claim 1, it is characterized in that, described fuel tank assembly (3) comprises multiple fuel tank (31) with partition, described pipeline (2) comprises many branch lines (21), every bar branch line (21) stretches to a described fuel tank (31), every bar branch line (21) is provided with a check valve (22), described check valve (22) is configured such that oil from described fueling connection (1) to each described fuel tank direction flowing.

6. aircraft refuelling system as claimed in claim 5, it is characterized in that, described in every bar, the end of branch line (21) is provided with diffusing opening (23), for the flow velocity of restriction through the oil of described diffusing opening (23).

7. an aircraft, is characterized in that, described aircraft comprises as the aircraft refuelling system in claim 1 to 6 as described in any one.