Aircraft fuel tank system

Abstract

The present application belongs to the technical field of aircraft fuel tank system design, and specifically relates to an aircraft fuel tank system, in which accessories such as a fuel supply joint, a fuel extraction hose, a fuel pump, a fuel supply hose, a fuel supply self-sealing joint plug, a refueling self-sealing joint plug, a fuel inlet hose, a refueling joint, an oil extraction hose, an oil extraction joint, a breathing valve, a circulation hose, and a circulation joint are integrated on the fuel tank, so that high assembly efficiency can be achieved when assembled on the aircraft; guide grooves, mounting grooves, mounting holes, connecting cavities and other structures are provided on the fuel tank to install the accessories, which can avoid exceeding the outer envelope of the fuel tank and save installation space; the fuel tank is designed to be connected to the outside world through a self-sealing quick-release plug or socket, and the joints are connected by a hose, which is convenient for docking and separation, and the fuel tank can be disassembled and assembled when it is oiled; the fuel tank is modularly designed and can be used individually or in series, which can well adapt to the modular design requirements of the aircraft.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft fuel tank system design, and specifically relates to an aircraft fuel tank system. Background Art

[0002] The aircraft fuel system is used to store fuel and continuously pressurize and supply fuel to the engine during flight. It mainly includes fuel tanks and accessories such as valves, pipelines, and boost pumps.

[0003] Currently, the fuel tank and its valves, pipelines, boost pumps and other accessories in the aircraft fuel system are generally delivered as loose parts. When assembled on the aircraft, the fuel tank and its valves, pipelines, boost pumps and other accessories are installed separately, which leads to low assembly efficiency.

[0004] In addition, aircraft fuel systems are generally designed based on the available space within the fuselage's internal structure. However, the modular design of aircraft requires that different modules be equipped with payloads according to different flight missions. The internal structural space will change, and the corresponding fuel tanks and their valves, pipelines, boost pumps and other accessories will also need to change. Currently, aircraft fuel systems are difficult to adapt well to the modular design requirements of aircraft.

[0005] This application is proposed in view of the above-mentioned technical defects. Summary of the Invention

[0006] The purpose of the present application is to provide an aircraft fuel tank system to overcome or alleviate at least one of the technical deficiencies of the prior art.

[0007] The technical solution of this application is:

[0008] An aircraft fuel tank system includes an integrated fuel tank; the integrated fuel tank includes a fuel tank, a fuel supply connector, a fuel extraction hose, a fuel pump, a fuel supply hose, a fuel supply self-sealing connector plug, a refueling self-sealing connector plug, a fuel inlet hose, a refueling connector, a fuel extraction hose, a fuel extraction connector, a circulation hose, and a circulation connector;

[0009] The side wall of the fuel tank has a first axial guide groove at the top, a top axial connecting cavity, a second axial guide groove at the top, and a third axial guide groove at the bottom, one end of which has a first radial guide groove at the end, and the other end of which has a second radial guide groove at the end; the first axial guide groove at the top has a fuel pump mounting groove, one end of which is connected to one end of the first radial guide groove at the end, and the other end of which has a fuel supply joint mounting groove; one end of the second axial guide groove at the top is connected to one end of the second radial guide groove at the end, and the other end of which has a circulation joint mounting groove; one end of the top axial connecting cavity has a fuel supply joint mounting hole, and the other end has a circulation joint mounting hole, wherein the fuel supply joint mounting hole is connected to the fuel supply joint mounting groove, and the circulation joint mounting hole is connected to the circulation joint mounting groove; one end of the third axial guide groove at the bottom is connected to the other end of the first radial guide groove at the end, and the other end has a refueling joint mounting groove, the side wall of the refueling joint mounting groove has a refueling joint mounting hole, and the refueling joint mounting hole is connected to the inside of the fuel tank; the first radial guide groove at the end has a plug mounting groove; the other end of the first radial guide groove at the end has a breathing valve mounting groove;

[0010] The oil supply connector is installed in the oil supply connector mounting hole and connected to one end of the oil extraction hose; the other end of the oil extraction hose extends into the oil tank through the opening provided in the bottom wall of the top axial communication cavity and is connected to the oil extraction connector;

[0011] The fuel pump is installed in the fuel pump mounting groove, with the inlet connected to one end of the fuel extraction hose and the outlet connected to the fuel supply hose; the other end of the fuel extraction hose is connected to the fuel supply connector through the first axial guide groove at the top and the fuel supply connector mounting groove; the other end of the fuel supply hose is connected to the fuel supply self-sealing connector plug, which is detachably installed in the plug mounting groove;

[0012] The refueling self-sealing joint plug is detachably installed in the plug installation groove and connected to one end of the oil inlet hose. The other end of the oil inlet hose is connected to the refueling joint through the first radial guide groove at the end, the third axial guide groove at the bottom, and the refueling joint installation groove. The refueling joint is installed in the refueling joint installation hole.

[0013] The flow joint is installed in the flow joint installation hole and connected to one end of the flow hose. The other end of the flow hose extends into the breathing valve installation groove through the flow joint installation groove, the second axial guide groove at the top, and the second radial guide groove at the end.

[0014] According to at least one embodiment of the present application, in the above-mentioned aircraft fuel tank system, both ends of the fuel tank adopt a dome design;

[0015] The side wall of the oil tank is provided with an outer axial wiring groove for cables and pipelines, and both ends of the outer axial wiring groove for cables and pipelines extend to both ends of the oil tank.

[0016] According to at least one embodiment of the present application, in the aircraft fuel tank system, the inlet end of the oil extraction connector is tapered;

[0017] The inlet end of the oil extraction joint is provided with an axial inlet, a vertical inlet and a transverse inlet which are interconnected and perpendicular to each other.

[0018] According to at least one embodiment of the present application, in the above-mentioned aircraft fuel tank system, the fuel supply connector, refueling connector, circulation connector, fuel pump, breathing valve, fuel supply self-sealing connector plug, and refueling self-sealing connector plug pipeline interfaces are all pagoda-shaped interfaces, which are directly connected to the corresponding hoses.

[0019] According to at least one embodiment of the present application, in the aircraft fuel tank system, the fuel supply connector, the refueling connector, and the flow connector are connected to the side walls of the fuel supply connector mounting groove, the refueling connector mounting groove, and the flow connector mounting groove by screws through flange edges;

[0020] Two sealing grooves are set on the outer walls of the oil supply joint, refueling joint and circulation joint, and sealing rings are installed, which are interference fit with the oil supply joint mounting hole, refueling joint mounting hole and circulation joint mounting hole.

[0021] According to at least one embodiment of the present application, in the above-mentioned aircraft fuel tank system, the integrated fuel tank further includes a breathing valve;

[0022] The breathing valve is detachably installed in the breathing valve installation groove and connected to the corresponding end of the circulation hose.

[0023] According to at least one embodiment of the present application, in the above-mentioned aircraft fuel tank system, the fuel pump and the breathing valve are installed in the fuel pump mounting groove and the breathing valve mounting groove via clamps;

[0024] The oil supply self-sealing joint plug and the refueling self-sealing joint plug are installed in the plug installation groove through a clamp.

[0025] According to at least one embodiment of the present application, when the above-mentioned aircraft fuel tank system is installed on an aircraft:

[0026] The fuel tank is fixed to the aircraft fuel tank compartment by screws and fits into the inner wall of the aircraft fuel tank compartment. The screw connection part in the fuel tank has a boss. The fuel supply self-sealing joint plug and the refueling self-sealing joint plug are taken out from the plug mounting slot and connected to the fuel supply self-sealing joint socket. The fuel supply self-sealing joint socket is connected to one end of the engine fuel supply hose, and the other end of the engine fuel supply hose is connected to the engine, and the refueling self-sealing joint plug is connected to the refueling self-sealing joint socket. The refueling self-sealing joint socket is connected to one end of the refueling hose, and the other end of the refueling hose is connected to the filling and drain valve. The filling and drain valve is fixed to the aircraft fuel tank compartment by screws.

[0027] According to at least one embodiment of the present application, in the above-mentioned aircraft fuel tank system, there are two integrated fuel tanks, one of which is a main integrated fuel tank and the other is a secondary integrated fuel tank;

[0028] Take out one end of the flow hose in the main integrated oil tank from the breathing valve installation groove and connect it to the oil delivery self-sealing joint socket;

[0029] Remove the fuel supply connector, fuel extraction hose, fuel pump, fuel supply hose, fuel supply self-sealing connector plug, fuel extraction hose, and fuel extraction connector from the auxiliary integrated fuel tank. Install a plug in the fuel supply connector mounting hole. Install a removable breathing valve in the breathing valve mounting groove. Connect the breathing valve to the corresponding end of the flow hose.

[0030] Take out the refueling self-sealing joint plug in the auxiliary integrated fuel tank from the joint installation slot and connect it to the oil delivery self-sealing joint socket;

[0031] When installing on an aircraft:

[0032] The fuel tank in the main integrated fuel tank and the auxiliary integrated fuel tank is fixed to the aircraft fuel tank compartment by screws, the fuel supply self-sealing joint plug and the refueling self-sealing joint plug are taken out from the plug installation slot of the main integrated fuel tank, the fuel supply self-sealing joint plug is connected to the fuel supply self-sealing joint socket, the fuel supply self-sealing joint socket is connected to one end of the engine fuel supply hose, the other end of the engine fuel supply hose is connected to the engine, and the refueling self-sealing joint plug is connected to the refueling self-sealing joint socket, the refueling self-sealing joint socket is connected to one end of the refueling hose, the other end of the refueling hose is connected to the filling and drain valve, and the filling and drain valve is fixed to the aircraft fuel tank compartment by screws.

[0033] According to at least one embodiment of the present application, in the above-mentioned aircraft fuel tank system, there are two integrated fuel tanks, one of which is a main integrated fuel tank and the other is a secondary integrated fuel tank;

[0034] Take out one end of the flow hose in the main integrated oil tank from the breathing valve installation groove and connect it to the oil delivery self-sealing joint socket;

[0035] Remove the refueling self-sealing joint plug, oil inlet hose and refueling joint from the auxiliary integrated fuel tank, install a plug in the refueling self-sealing joint installation hole, install a detachable breathing valve in the breathing valve installation groove, and connect the breathing valve to the corresponding end of the flow hose;

[0036] Take out the oil supply self-sealing joint plug in the auxiliary integrated oil tank from the joint installation slot and connect it to the oil delivery self-sealing joint socket;

[0037] When installing on an aircraft:

[0038] The main integrated fuel tank and the auxiliary integrated fuel tank are fixed to the aircraft fuel tank compartment by screws, the fuel supply self-sealing joint plug and the refueling self-sealing joint plug in the main integrated fuel tank plug installation slot are taken out, the fuel supply self-sealing joint plug is connected to the fuel supply self-sealing joint socket, the fuel supply self-sealing joint socket is connected to one end of the engine fuel supply hose, the other end of the engine fuel supply hose is connected to the engine, and the refueling self-sealing joint plug is connected to the refueling self-sealing joint socket, the refueling self-sealing joint socket is connected to one end of the refueling hose, the other end of the refueling hose is connected to the filling and drain valve, and the filling and drain valve is fixed to the aircraft fuel tank compartment by screws.

[0039] This application has at least the following beneficial technical effects:

[0040] Provided is an aircraft fuel tank system, in which accessories such as a fuel supply joint, a fuel extraction hose, a fuel pump, a fuel supply hose, a fuel supply self-sealing joint plug, a refueling self-sealing joint plug, a fuel inlet hose, a refueling joint, an oil extraction hose, an oil extraction joint, a breathing valve, a circulation hose, and a circulation joint are integrated on the fuel tank, so that high assembly efficiency can be achieved when assembled on the aircraft; guide grooves, mounting grooves, mounting holes, connecting cavities and other structures are provided on the fuel tank to install the accessories, which can avoid exceeding the outer envelope of the fuel tank and save installation space; the fuel tank is designed to be connected to the outside world through a self-sealing quick-release plug or socket, and the joints are connected by a hose, which is convenient for docking and separation, and the fuel tank can be disassembled and assembled when it is oiled; the fuel tank is modularly designed and can be used individually or in series, which can well adapt to the modular design requirements of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] Figure 1 This is a schematic diagram of the appearance of the aircraft fuel tank system provided in Example 1 of the present application;

[0042] Figure 2 is a schematic cross-sectional view of an aircraft fuel tank system provided in Example 1 of the present application;

[0043] Figure 3 This is a schematic diagram of the oil extraction connector provided in Example 1 of the present application;

[0044] Figure 4 This is a schematic diagram of the assembly of the flow joint and the sealing ring provided in Example 1 of the present application;

[0045] Figure 5 This is a schematic diagram of the installation of the aircraft fuel tank system provided in Example 1 of the present application;

[0046] Figure 6 This is a schematic diagram of the installation of the aircraft fuel tank system provided in Example 1 of the present application;

[0047] Figure 7is a schematic diagram of a secondary integrated fuel tank in an aircraft fuel tank system provided in Example 2 of the present application;

[0048] Figure 8 This is a schematic diagram of the installation of an aircraft fuel tank system provided in Example 2 of the present application;

[0049] Figure 9 is a schematic diagram of a secondary integrated fuel tank in an aircraft fuel tank system provided in Example 3 of the present application;

[0050] Figure 10 This is a schematic diagram of the installation of an aircraft fuel tank system provided in Example 3 of the present application;

[0051] in:

[0052] 1-Fuel tank; 2-Fuel supply connector; 3-Fuel extraction hose; 4-Fuel pump; 5-Fuel delivery self-sealing connector socket; 6-Fuel supply hose; 7-; 8-Fuel supply self-sealing connector plug; 9-Fueling self-sealing connector plug; 10-Fuel inlet hose; 11-Block; 12-Fueling connector; 13-Fuel extraction hose; 14-Fuel extraction connector; 15-Breathing valve; 16-Circulation hose; 17-Circulation connector; 18-Aircraft fuel tank compartment; 19-Fueling self-sealing connector socket; 20-Fueling hose; 21-Engine fuel supply hose; 22-Fuel supply self-sealing connector socket; 23-Filling and drain valve.

[0053] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be understood as limiting this application. DETAILED DESCRIPTION

[0054] To make the technical solution and its advantages of this application more clear, the technical solution of this application will be further described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described here are only some of the embodiments of this application and are only used to explain this application, not to limit this application. It should be noted that for ease of description, only the parts relevant to this application are shown in the accompanying drawings, and other relevant parts can refer to the general design.

[0055] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should have the usual meanings understood by those skilled in the art in the field to which this application belongs. The words indicating orientation used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application means that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0056] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0057] An embodiment of the present application provides an aircraft fuel tank system.

[0058] Example 1:

[0059] like Figure 1-2 As shown, the aircraft fuel tank system includes an integrated fuel tank, which further includes a fuel tank 1, a fuel supply connector 2, an oil extraction hose 3, a fuel pump 4, a fuel supply hose 6, a fuel supply self-sealing connector plug 8, a refueling self-sealing connector plug 9, an oil inlet hose 10, a refueling connector 12, an oil extraction hose 13, an oil extraction connector 14, a breathing valve 15, a circulation hose 16, and a circulation connector 17.

[0060] Both ends of the oil tank 1 adopt a dome design to increase the pressure-bearing capacity. The side wall has a first axial guide groove at the top, a top axial connecting cavity, a second axial guide groove at the top, a third axial guide groove at the bottom, and an outer cable and pipeline axial routing groove. One end has a first radial guide groove at the end, and the other end has a second radial guide groove at the end.

[0061] The first axial guide groove at the top has a fuel pump mounting groove, one end of which is connected to one end of the first radial guide groove at the end, and the other end has a fuel supply joint mounting groove. The second axial guide groove at the top has one end connected to one end of the second radial guide groove at the end, and the other end has a flow joint mounting groove. The top axial connecting cavity has a fuel supply joint mounting hole at one end, and a flow joint mounting hole at the other end, wherein the fuel supply joint mounting hole is connected to the fuel supply joint mounting groove, and the flow joint mounting hole is connected to the flow joint mounting groove. The third axial guide groove at the bottom has one end connected to the other end of the first radial guide groove at the end, and the other end has a refueling joint mounting groove, and the side wall of the refueling joint mounting groove has a refueling joint mounting hole, which is connected to the interior of the fuel tank 1. The first radial guide groove at the end has a plug mounting groove; the other end of the second radial guide groove at the end has a breathing valve mounting groove. The two ends of the external cable and pipeline axial routing groove extend to both ends of the fuel tank 1 for routing external cables and pipelines.

[0062] The oil supply connector 2 is installed in the oil supply connector mounting hole and connected to one end of the oil hose 13. The other end of the oil hose 13 extends into the oil tank 1 through the opening opened in the bottom wall of the top axial communication cavity and is connected to the oil connector 14; the oil connector 14 is a pagoda-shaped pipe connector, such as Figure 3As shown, the inlet end of the oil extraction joint 14 is tapered, and has an axial inlet, a vertical inlet, and a transverse inlet that are interconnected and perpendicular to each other.

[0063] The fuel pump 4 is removably mounted in the fuel pump mounting slot. Its inlet is connected to one end of the fuel extraction hose 3, and its outlet is connected to the fuel supply hose 6. The other end of the fuel extraction hose 3 is connected to the fuel supply connector 2 via the top first axial guide groove and the fuel supply connector mounting slot. The other end of the fuel supply hose 6 is connected to the self-sealing fuel supply connector plug 8, which is removably mounted in the plug mounting slot.

[0064] The refueling self-sealing joint plug 9 is detachably installed in the plug mounting groove and connected to one end of the oil inlet hose 10. The other end of the oil inlet hose 10 is connected to the refueling joint 12 through the first radial guide groove at the end, the third axial guide groove at the bottom, and the refueling joint mounting groove. The refueling joint 12 is installed in the refueling joint mounting hole.

[0065] The breathing valve 15 is detachably installed in the breathing valve mounting groove and connected to one end of the circulation hose 16. The other end of the circulation hose 16 is connected to the circulation joint 17 through the second radial guide groove at the end, the second axial guide groove at the top, and the circulation joint mounting groove. The circulation joint 17 is installed in the circulation joint mounting hole and extends into the fuel tank 1 through the opening on the side wall of the axial connecting cavity.

[0066] The pipeline interfaces of the fuel supply connector 2, the refueling connector 12, the circulation connector 17, the fuel pump 4, the breathing valve 15, the fuel supply self-sealing connector plug 8, and the refueling self-sealing connector plug 9 are all pagoda-shaped interfaces, which can be directly connected to the hose for easy disassembly and assembly.

[0067] The oil supply connector 2, the refueling connector 12, and the circulation connector 17 are connected to the side walls of the oil supply connector mounting groove, the refueling connector mounting groove, and the circulation connector mounting groove by screws through the flange edge. Two sealing grooves are set on the outer walls of the oil supply connector 2, the refueling connector 12, and the circulation connector 17 to install the sealing ring, which is interference fit with the oil supply connector mounting hole, the refueling connector mounting hole, and the circulation connector mounting hole to ensure the sealing effect. Among them, the assembly relationship between the circulation connector 17 and the sealing ring is as follows Figure 4 shown.

[0068] The fuel pump 4 and the breathing valve 15 are installed in the fuel pump mounting groove and the breathing valve mounting groove through clamps, and the fuel supply self-sealing joint plug 8 and the refueling self-sealing joint plug 9 are installed in the plug mounting groove through clamps.

[0069] When the aircraft fuel tank system disclosed in the above embodiment 1 is installed on an aircraft, the fuel tank 1 is fixed to the aircraft fuel tank compartment 18 by screws, and fits with the inner wall of the aircraft fuel tank compartment 18. The screw connection part in the fuel tank 1 has a boss to perform local reinforcement and ensure sealing. The fuel supply self-sealing joint plug 8 and the refueling self-sealing joint plug 9 are taken out from the plug installation groove, and the fuel supply self-sealing joint plug 8 is connected to the fuel supply self-sealing joint socket 22. The fuel supply self-sealing joint socket 22 is connected to one end of the engine fuel supply hose 21, and the other end of the engine fuel supply hose 21 is connected to the engine. The refueling self-sealing joint plug 9 is connected to the refueling self-sealing joint socket 19, and the refueling self-sealing joint socket 19 is connected to one end of the refueling hose 20. The refueling and drain valve 23 is connected to the other end of the refueling hose 20. The refueling and drain valve 23 is fixed to the aircraft fuel tank compartment 18 by screws, as shown in FIG. Figure 5 shown.

[0070] In the aircraft fuel tank system disclosed in the above embodiment, fuel can be added from the filling and drain valve 23 during refueling. The fuel enters the fuel tank 1 through the refueling hose 20, the refueling self-sealing joint socket 19, the refueling self-sealing joint plug 9, the oil inlet hose 10 and the refueling joint 12. During the refueling process, the gas in the fuel tank 1 can be discharged through the flow joint 17, the flow hose 16 and the breathing valve 15 to maintain the pressure balance inside and outside the fuel tank 1 and ensure smooth refueling.

[0071] In the aircraft fuel tank system disclosed in the above embodiment, when draining oil, oil can be drawn from the filling and drain valve 23, and the fuel in the fuel tank 1 flows out through the refueling connector 12, the oil inlet hose 10, the refueling self-sealing connector plug 9, the refueling self-sealing connector socket 19, the refueling hose 20, and the filling and drain valve 23. At this time, the pressure in the fuel tank 1 is reduced, the breathing valve 15 can be opened, and air is introduced into the fuel tank 1 through the flow hose 16 and the flow connector 17 to maintain the pressure balance inside and outside the fuel tank 1 and ensure smooth oil draining.

[0072] In the above-mentioned embodiment of the disclosed aircraft fuel tank system, when supplying fuel, the fuel pump 4 can suck the fuel in the fuel tank 1, and the fuel in the fuel tank 1 is supplied to the engine through the oil extraction joint 14, the oil extraction hose 13, the fuel supply joint 2, the oil extraction hose 3, the fuel pump 4, the fuel supply hose 6, the fuel supply self-sealing joint plug 8, the fuel supply self-sealing joint socket 22, and the engine fuel supply hose 21. As the fuel is consumed, the pressure in the fuel tank 1 will decrease, and the breathing valve 15 can be opened to allow air to enter the fuel tank 1 through the circulation hose 16 and the circulation joint 17 to maintain the pressure balance inside and outside the fuel tank 1 and ensure the smooth supply of fuel.

[0073] In the aircraft fuel tank system disclosed in the first embodiment, during aircraft maneuvers, the oil extraction connector 14 will move with the flight overload, and the movement direction is consistent with the movement direction of the fuel in the fuel tank 1, and can always be located below the liquid level, thereby ensuring the continuity of fuel supply to the engine. The inlet end of the oil extraction connector 14 is designed with an axial inlet, a vertical inlet, and a transverse inlet that are interconnected and perpendicular to each other, thereby preventing the oil hole from being blocked due to partial contact between the inlet end of the oil extraction connector 14 and the wall of the fuel tank 1, resulting in a situation where fuel supply cannot be supplied.

[0074] Example 2:

[0075] Different from the aircraft fuel tank system disclosed in the above-mentioned embodiment 1, there are two integrated fuel tanks, one of which is a main integrated fuel tank and the other is a secondary integrated fuel tank.

[0076] The breathing valve 15 in the main integrated oil tank is taken out from the breathing valve installation groove and replaced with the oil delivery self-sealing joint socket 5.

[0077] Remove the fuel supply connector 2, fuel extraction hose 3, fuel pump 4, fuel supply hose 6, fuel supply self-sealing connector plug 8, fuel extraction hose 13, and fuel extraction connector 14 from the auxiliary integrated fuel tank, and install a plug 11 in the fuel supply connector mounting hole. Figure 7 shown.

[0078] The refueling self-sealing joint plug 9 in the auxiliary integrated oil tank is taken out from the joint installation groove and connected to the oil delivery self-sealing joint socket 5.

[0079] When the aircraft fuel tank system disclosed in the above-mentioned embodiment 2 is installed on an aircraft, the fuel tank 1 among the main integrated fuel tank and the auxiliary integrated fuel tank is fixed to the aircraft fuel tank compartment 18 by screws, the fuel supply self-sealing joint plug 8 and the refueling self-sealing joint plug 9 are taken out from the main integrated fuel tank plug installation slot, the fuel supply self-sealing joint plug 8 is connected to the fuel supply self-sealing joint socket 22, the fuel supply self-sealing joint socket 22 is connected to one end of the engine fuel supply hose 21, the other end of the engine fuel supply hose 21 is connected to the engine, and the refueling self-sealing joint plug 9 is connected to the refueling self-sealing joint socket 19, the refueling self-sealing joint socket 19 is connected to one end of the refueling hose 20, and the refueling and drain valve 23 is connected to the other end of the refueling hose 20, and the refueling and drain valve 23 is fixed to the aircraft fuel tank compartment 18 by screws, as shown in FIG. Figure 8 shown.

[0080] The aircraft fuel tank system disclosed in the second embodiment can be refueled from the filling and drain valve 23 during refueling, and the fuel enters the fuel tank 1 through the refueling hose 20, the refueling self-sealing joint socket 19, the refueling self-sealing joint plug 9, the oil inlet hose 10 and the refueling joint 12 of the main integrated fuel tank. After the fuel tank 1 of the main integrated fuel tank is full of oil, the fuel enters the fuel tank 1 through the flow joint 17, the flow hose 16, the oil delivery self-sealing joint socket 5 of the main integrated fuel tank, and the refueling self-sealing joint plug 9, the oil inlet hose 10 and the refueling joint 12 of the auxiliary integrated fuel tank. During the refueling process, the gas in the fuel tank 1 of the main integrated fuel tank and the auxiliary integrated fuel tank can be discharged through the flow joint 17, the flow hose 16 and the breathing valve 15 of the auxiliary integrated fuel tank to maintain the pressure balance inside and outside the fuel tank 1 and ensure the smoothness of refueling.

[0081] When draining fuel from the aircraft fuel tank system disclosed in the second embodiment, fuel can be drawn from the filling and drain valve 23, and the fuel in the fuel tank 1 of the main integrated fuel tank and the auxiliary integrated fuel tank can flow out in sequence through the filling and drain valve 23. At this time, the pressure in the fuel tank 1 of the main integrated fuel tank and the auxiliary integrated fuel tank is reduced, and the breathing valve 15 of the auxiliary integrated fuel tank can be opened, and air can be introduced into the fuel tank 1 through the flow hose 16 and the flow joint 17 to maintain the pressure balance inside and outside the fuel tank 1 and ensure smooth draining of the fuel.

[0082] When the aircraft fuel tank system disclosed in the second embodiment is supplied with fuel, the fuel pump 4 of the main integrated fuel tank can suck the fuel in the fuel tank 1, and the fuel in the main integrated fuel tank and the auxiliary integrated fuel tank 1 can be supplied to the engine in sequence through the engine fuel supply hose 21. As the fuel is consumed, the pressure in the main integrated fuel tank and the auxiliary integrated fuel tank 1 will decrease, and the breathing valve 15 of the auxiliary integrated fuel tank can be opened to allow air to enter the fuel tank 1 through the flow hose 16 and the flow joint 17 to maintain the pressure balance inside and outside the fuel tank 1 and ensure the smoothness of the fuel supply.

[0083] In the aircraft fuel tank system disclosed in the second embodiment, during aircraft maneuvers, the oil extraction connector 14 in the main integrated fuel tank will move with the flight overload, and the direction of movement is consistent with the direction of movement of the fuel in the fuel tank 1, and can always be located below the liquid level, thereby ensuring the continuity of fuel supply to the engine. The inlet end of the oil extraction connector 14 is designed with an axial inlet, a vertical inlet, and a lateral inlet that are interconnected and perpendicular to each other, thereby preventing the oil hole from being blocked due to partial contact between the inlet end of the oil extraction connector 14 and the wall of the fuel tank 1, resulting in a situation where fuel supply cannot be supplied.

[0084] Example 3:

[0085] Different from the aircraft fuel tank system disclosed in the above-mentioned embodiment 1, the integrated fuel tank system includes two integrated fuel tanks, one of which is a main integrated fuel tank and the other is a secondary integrated fuel tank.

[0086] The breathing valve 15 in the main integrated oil tank is taken out from the breathing valve installation groove and replaced with the oil delivery self-sealing joint socket 5.

[0087] Remove the refueling self-sealing joint plug 9, the oil inlet hose 10 and the refueling joint 12 from the auxiliary integrated fuel tank, and install the plug 11 in the refueling self-sealing joint installation hole. Figure 9 shown.

[0088] The oil supply self-sealing joint plug 8 in the auxiliary integrated oil tank is taken out from the joint installation groove and connected to the oil delivery self-sealing joint socket 5.

[0089] When the aircraft fuel tank system disclosed in the third embodiment is installed on an aircraft, the fuel tank 1 among the main integrated fuel tank and the auxiliary integrated fuel tank is fixed to the aircraft fuel tank compartment 18 by screws, the fuel supply self-sealing joint plug 8 and the refueling self-sealing joint plug 9 are taken out from the main integrated fuel tank plug installation slot, the fuel supply self-sealing joint plug 8 is connected to the fuel supply self-sealing joint socket 22, the fuel supply self-sealing joint socket 22 is connected to one end of the engine fuel supply hose 21, the other end of the engine fuel supply hose 21 is connected to the engine, and the refueling self-sealing joint plug 9 is connected to the refueling self-sealing joint socket 19, the refueling self-sealing joint socket 19 is connected to one end of the refueling hose 20, the refueling and drain valve 23 is connected to the other end of the refueling hose 20, and the refueling and drain valve 23 is fixed to the aircraft fuel tank compartment 18 by screws, as shown in FIG. Figure 10 shown.

[0090] The aircraft fuel tank system disclosed in the third embodiment can be refueled from the refueling and drain valve 23 during refueling, and the fuel enters the fuel tank 1 through the refueling hose 20, the refueling self-sealing joint socket 19, the refueling self-sealing joint plug 9, the oil inlet hose 10 and the refueling joint 12 of the main integrated fuel tank. After the fuel tank 1 of the main integrated fuel tank is full of oil, the fuel enters the fuel tank 1 through the flow joint 17, the flow hose 16, the oil delivery self-sealing joint socket 5 of the main integrated fuel tank, and the oil supply self-sealing joint plug 8, the fuel pump 4, the oil extraction hose 3, the oil supply joint 2, the oil extraction hose 13 and the oil extraction joint 14 of the auxiliary integrated fuel tank. During the refueling process, the gas in the fuel tank 1 of the main integrated fuel tank and the auxiliary integrated fuel tank can be discharged through the flow joint 17, the flow hose 16 and the breathing valve 15 of the auxiliary integrated fuel tank to maintain the pressure balance inside and outside the fuel tank 1 and ensure the smooth refueling.

[0091] When draining fuel from the aircraft fuel tank system disclosed in the third embodiment, fuel can be drawn from the filling and drain valve 23, and the fuel in the main integrated fuel tank and the auxiliary integrated fuel tank 1 can flow out through the filling and drain valve 23 in sequence. At this time, the pressure in the main integrated fuel tank and the auxiliary integrated fuel tank 1 is reduced, and the breathing valve 15 of the auxiliary integrated fuel tank can be opened, allowing air to enter the fuel tank 1 through the flow hose 16 and the flow joint 17 to maintain the pressure balance between the inside and outside of the fuel tank 1 and ensure smooth draining of the fuel.

[0092] When the aircraft fuel tank system disclosed in the third embodiment is supplied with fuel, the fuel pumps 4 of the main integrated fuel tank and the auxiliary integrated fuel tank can suck the fuel in the fuel tank 1, and the fuel in the fuel tank 1 of the main integrated fuel tank and the auxiliary integrated fuel tank can be supplied to the engine in sequence through the engine fuel supply hose 21. As the fuel is consumed, the pressure in the fuel tank 1 of the main integrated fuel tank and the auxiliary integrated fuel tank will decrease, and the breathing valve 15 of the auxiliary integrated fuel tank can be opened to allow air to enter the fuel tank 1 through the flow hose 16 and the flow joint 17 to maintain the pressure balance inside and outside the fuel tank 1 and ensure the smoothness of the fuel supply.

[0093] In the aircraft fuel tank system disclosed in the third embodiment, during aircraft maneuvers, the oil extraction connector 14 in the main integrated fuel tank and the auxiliary integrated fuel tank will move with the flight overload, and the direction of movement is consistent with the direction of movement of the fuel in the fuel tank 1, and can always be located below the liquid level, thereby ensuring the continuity of fuel supply to the engine. The inlet end of the oil extraction connector 14 is designed with an axial inlet, a vertical inlet, and a lateral inlet that are interconnected and perpendicular to each other, thereby preventing the oil hole from being blocked due to partial contact between the inlet end of the oil extraction connector 14 and the wall of the fuel tank 1, resulting in a situation where fuel supply cannot be supplied.

[0094] The aircraft fuel tank system disclosed in the above embodiment has the following advantages:

[0095] The fuel supply connector 2, the oil extraction hose 3, the fuel pump 4, the fuel supply hose 6, the fuel supply self-sealing connector plug 8, the refueling self-sealing connector plug 9, the fuel inlet hose 10, the refueling connector 12, the oil extraction hose 13, the oil extraction connector 14, the breathing valve 15, the circulation hose 16, the circulation connector 17 and other accessories are integrated on the fuel tank 1, which can achieve high assembly efficiency when assembled on the aircraft;

[0096] The fuel tank 1 is provided with guide grooves, mounting grooves, mounting holes, communicating cavities and other structures to install the accessories, which can avoid exceeding the outer envelope of the fuel tank 1 and save installation space;

[0097] The fuel tank 1 is designed to be connected to the outside world through a self-sealing quick-release plug or socket, and the joints are connected by a hose, which makes it easy to connect and separate, and the fuel tank 1 can be disassembled and assembled when it is oiled;

[0098] The fuel tank 1 is modularly designed and can be used singly or in series, which can well adapt to the modular design requirements of the aircraft.

[0099] The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referenced to each other. In the absence of conflict, the embodiments in this application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0100] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. An aircraft fuel tank system, characterized in that: The integrated fuel tank includes a fuel tank (1), a fuel supply connector (2), a fuel extraction hose (3), a fuel pump (4), a fuel supply hose (6), a fuel supply self-sealing connector plug (8), a refueling self-sealing connector plug (9), a fuel inlet hose (10), a refueling connector (12), a fuel extraction hose (13), a fuel extraction connector (14), a circulation hose (16), and a circulation connector (17); The side wall of the fuel tank (1) has a first axial guide groove at the top, a top axial connecting cavity, a second axial guide groove at the top, and a third axial guide groove at the bottom, one end of which has a first radial guide groove at the end, and the other end of which has a second radial guide groove at the end; the first axial guide groove at the top has a fuel pump mounting groove, one end of which is connected to one end of the first radial guide groove at the end, and the other end of which has a fuel supply joint mounting groove; the second axial guide groove at the top has one end of which is connected to one end of the second radial guide groove at the end, and the other end of which has a flow joint mounting groove; the top axial connecting cavity has a fuel supply joint mounting hole at one end, and the other end of which has a flow joint mounting hole, wherein the fuel supply joint mounting hole is connected to the fuel supply joint mounting groove, and the flow joint mounting hole is connected to the flow joint mounting groove; the third axial guide groove at the bottom has one end of which is connected to the other end of the first radial guide groove at the end, and the other end of which has a refueling joint mounting groove, the refueling joint mounting groove has a refueling joint mounting hole on the side wall, and the refueling joint mounting hole is connected to the inside of the fuel tank (1); the first radial guide groove at the end has a plug mounting groove; the other end of the first radial guide groove at the end has a breathing valve mounting groove; The oil supply connector (2) is installed in the oil supply connector installation hole and connected to one end of the oil extraction hose (13); the other end of the oil extraction hose (13) extends into the oil tank (1) through the opening formed in the bottom wall of the top axial communication cavity and is connected to the oil extraction connector (14); The fuel pump (4) is installed in the fuel pump installation groove, the inlet is connected to one end of the oil extraction hose (3), and the outlet is connected to the oil supply hose (6); the other end of the oil extraction hose (3) is connected to the oil supply connector (2) through the top first axial guide groove and the oil supply connector installation groove; the other end of the oil supply hose (6) is connected to the oil supply self-sealing connector plug (8), and the oil supply self-sealing connector plug (8) is detachably installed in the plug installation groove; The refueling self-sealing joint plug (9) is detachably mounted in the plug mounting groove and connected to one end of the oil inlet hose (10). The other end of the oil inlet hose (10) is connected to the refueling joint (12) through the first radial guide groove at the end, the third axial guide groove at the bottom, and the refueling joint mounting groove. The refueling joint (12) is mounted in the refueling joint mounting hole. The circulation joint (17) is installed in the circulation joint installation hole and connected to one end of the circulation hose (16). The other end of the circulation hose (16) extends into the breathing valve installation groove through the circulation joint installation groove, the second axial guide groove at the top, and the second radial guide groove at the end. The integrated fuel tank also includes a breathing valve (15); The breathing valve (15) is detachably mounted in the breathing valve mounting groove and connected to the corresponding end of the circulation hose (16).

2. The aircraft fuel tank system according to claim 1, wherein: The fuel tank (1) has a dome design at both ends; The side wall of the oil tank (1) has an outer cable and pipeline axial wiring groove, and both ends of the outer cable and pipeline axial wiring groove extend to both ends of the oil tank (1).

3. The aircraft fuel tank system according to claim 2, wherein: The inlet end of the oil extraction joint (14) is tapered; The inlet end of the oil extraction joint (14) has an axial inlet, a vertical inlet, and a transverse inlet which are interconnected and perpendicular to each other.

4. The aircraft fuel tank system according to claim 3, wherein: The pipeline interfaces of the oil supply connector (2), the refueling connector (12), the circulation connector (17), the fuel pump (4), the breathing valve (15), the oil supply self-sealing connector plug (8), and the refueling self-sealing connector plug (9) are all pagoda-shaped interfaces, which are directly connected to the corresponding hoses.

5. The aircraft fuel tank system according to claim 4, wherein: The oil supply joint (2), the refueling joint (12), and the circulation joint (17) are connected to the side walls of the oil supply joint mounting groove, the refueling joint mounting groove, and the circulation joint mounting groove by screws through the flange edges; Two sealing grooves are provided on the outer walls of the oil supply joint (2), the refueling joint (12), and the circulation joint (17), and sealing rings are installed therein, which are interference-fitted with the oil supply joint mounting hole, the refueling joint mounting hole, and the circulation joint mounting hole.

6. The aircraft fuel tank system according to claim 1, wherein: The fuel pump (4) and the breathing valve (15) are installed in the fuel pump installation groove and the breathing valve installation groove via clamps; The oil supply self-sealing joint plug (8) and the refueling self-sealing joint plug (9) are installed in the plug installation groove through a clamp.

7. The aircraft fuel tank system according to claim 6, wherein: When installing on an aircraft: The fuel tank (1) is fixed to the aircraft fuel tank compartment (18) by screws and is fitted with the inner wall of the aircraft fuel tank compartment (18). The screw connection portion in the fuel tank (1) has a boss. The fuel supply self-sealing joint plug (8) and the refueling self-sealing joint plug (9) are taken out from the plug installation groove and connected to the fuel supply self-sealing joint socket (22). The fuel supply self-sealing joint socket (22) is connected to one end of the engine fuel supply hose (21). The other end of the engine fuel supply hose (21) is connected to the engine. The refueling self-sealing joint plug (9) is connected to the refueling self-sealing joint socket (19). The refueling self-sealing joint socket (19) is connected to one end of the refueling hose (20). The other end of the refueling hose (20) is connected to the refueling discharge valve (23). The refueling discharge valve (23) is fixed to the aircraft fuel tank compartment (18) by screws.

8. The aircraft fuel tank system according to claim 1, wherein: There are two integrated fuel tanks, one is the main integrated fuel tank and the other is the auxiliary integrated fuel tank; One end of the circulating hose (16) in the main integrated oil tank is taken out from the breathing valve installation groove and connected to the oil delivery self-sealing joint socket (5); In the auxiliary integrated fuel tank, the fuel supply connector (2), the fuel extraction hose (3), the fuel pump (4), the fuel supply hose (6), the fuel supply self-sealing connector plug (8), the fuel extraction hose (13), and the fuel extraction connector (14) are removed, a plug (11) is installed in the fuel supply connector mounting hole, a removable breathing valve (15) is installed in the breathing valve mounting groove, and the breathing valve (15) is connected to the corresponding end of the circulation hose (16); The refueling self-sealing joint plug (9) in the auxiliary integrated oil tank is taken out from the joint installation groove and connected to the oil delivery self-sealing joint socket (5); When installing on an aircraft: The main integrated fuel tank and the auxiliary integrated fuel tank (1) are fixed to the aircraft fuel tank compartment (18) by screws, the fuel supply self-sealing joint plug (8) and the refueling self-sealing joint plug (9) are taken out from the plug installation groove of the main integrated fuel tank, the fuel supply self-sealing joint plug (8) is connected to the fuel supply self-sealing joint socket (22), the fuel supply self-sealing joint socket (22) is connected to one end of the engine fuel supply hose (21), the other end of the engine fuel supply hose (21) is connected to the engine, and the refueling self-sealing joint plug (9) is connected to the refueling self-sealing joint socket (19), the refueling self-sealing joint socket (19) is connected to one end of the refueling hose (20), the other end of the refueling hose (20) is connected to the refueling discharge valve (23), and the refueling discharge valve (23) is fixed to the aircraft fuel tank compartment (18) by screws.

9. The aircraft fuel tank system according to claim 1, wherein: There are two integrated fuel tanks, one is the main integrated fuel tank and the other is the auxiliary integrated fuel tank; One end of the circulating hose (16) in the main integrated oil tank is taken out from the breathing valve installation groove and connected to the oil delivery self-sealing joint socket (5); The refueling self-sealing joint plug (9), the oil inlet hose (10) and the refueling joint (12) are removed from the auxiliary integrated oil tank, a plug (11) is installed in the refueling self-sealing joint installation hole, a removable breathing valve (15) is installed in the breathing valve installation groove, and the breathing valve (15) is connected to the corresponding end of the circulation hose (16); The oil supply self-sealing joint plug (8) in the auxiliary integrated oil tank is taken out from the joint installation groove and connected to the oil delivery self-sealing joint socket (5); When installing on an aircraft: The main integrated fuel tank and the auxiliary integrated fuel tank (1) are fixed to the aircraft fuel tank compartment (18) by screws, the fuel supply self-sealing joint plug (8) and the refueling self-sealing joint plug (9) are taken out from the main integrated fuel tank plug installation groove, the fuel supply self-sealing joint plug (8) is connected to the fuel supply self-sealing joint socket (22), the fuel supply self-sealing joint socket (22) is connected to one end of the engine fuel supply hose (21), the other end of the engine fuel supply hose (21) is connected to the engine, and the refueling self-sealing joint plug (9) is connected to the refueling self-sealing joint socket (19), the refueling self-sealing joint socket (19) is connected to one end of the refueling hose (20), the other end of the refueling hose (20) is connected to the refueling discharge valve (23), and the refueling discharge valve (23) is fixed to the aircraft fuel tank compartment (18) by screws.

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