Aircraft fuel tank system

Abstract

The invention belongs to the technical field of aircraft fuel tank system design, and particularly relates to an aircraft fuel tank system. An oil supply connector, an oil pumping hose, a fuel pump, an oil supply hose, an oil supply self-sealing connector plug, an oil filling self-sealing connector plug, an oil inlet hose, an oil filling connector, an oil taking hose, an oil taking connector, a breather valve, a circulation hose, a circulation connector and other accessories are integrated on the oil tank, and when the oil tank is assembled on an aircraft, high assembly efficiency can be achieved; the guide groove, the mounting groove, the mounting hole, the communicating cavity and other structures are formed in the oil tank, accessories are mounted, the accessories can be prevented from exceeding the outer envelope of the oil tank, and the mounting space is saved; the oil tank is connected with the outside through a self-sealing quick-release plug or socket, and joints are connected through hoses, so that butt joint and separation are convenient, and the oil tank can be disassembled and assembled in an oil-carrying state; modular design is carried out on the fuel tank, single fuel tank or multiple fuel tanks can be connected in series for use, and the modular design requirement of the aircraft can be well met.

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, resulting in low assembly efficiency.

[0004] In addition, aircraft fuel systems are generally designed based on the available space within the fuselage's internal structure. However, aircraft modular design 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 object of the present application is to provide an aircraft fuel tank system to overcome or alleviate at least one aspect 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 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 circulation hose, and a circulation joint;

[0009] The side wall of the fuel tank is provided with 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 is provided with a first radial guide groove at the end, and the other end of which is provided with a second radial guide groove at the end; the first axial guide groove at the top is provided with 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 is provided with 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 is provided with a flow joint mounting groove; one end of the top axial connecting cavity is provided with a fuel supply joint mounting hole, and the other end of which is provided with 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; 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 of which is provided with a refueling joint mounting groove, and the side wall of the refueling joint mounting groove is provided with 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 is provided with a plug mounting groove; the other end of the first radial guide groove at the end is provided with a breathing valve mounting groove;

[0010] The oil supply connector is installed in the oil supply connector installation 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 formed 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 installation groove, the inlet is connected to one end of the oil extraction hose, and the outlet is connected to the oil supply hose; the other end of the oil extraction hose is connected to the oil supply joint through the top first axial guide groove and the oil supply joint installation groove; the other end of the oil supply hose is connected to the oil supply self-sealing joint plug, and the oil supply self-sealing joint plug is detachably installed in the plug installation 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 top second axial guide groove, and the end second radial guide groove.

[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 axial wiring groove for outer cables and pipelines, and both ends of the axial wiring groove for outer cables and pipelines extend to both ends of the oil tank.

[0016] According to at least one embodiment of the present application, in the above-mentioned 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 above-mentioned aircraft fuel tank system, the fuel supply connector, the refueling connector, and the flow connector are connected to the fuel supply connector mounting groove, the refueling connector mounting groove, and the flow connector mounting groove side walls by screws through flange edges;

[0020] Two sealing grooves are arranged on the outer walls of the oil supply joint, the refueling joint and the circulation joint, and sealing rings are installed, which are interference fit with the oil supply joint mounting hole, the refueling joint mounting hole and the 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 installation groove and the breathing valve installation groove through a clamp;

[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, in the above-mentioned aircraft fuel tank system, when installed on an aircraft:

[0026] The fuel tank is fixed to the aircraft fuel tank compartment by screws and fits with 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 groove 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 circulating 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 joint, fuel extraction hose, fuel pump, fuel supply hose, fuel supply self-sealing joint plug, fuel extraction hose, and fuel extraction joint from the auxiliary integrated fuel tank, install a plug in the fuel supply 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 circulation hose;

[0030] The refueling self-sealing joint plug in the auxiliary integrated oil tank is taken out from the joint installation slot and connected to the oil delivery self-sealing joint socket;

[0031] When installing on an aircraft:

[0032] 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 are taken out from the plug installation slot of the main integrated fuel tank, the fuel supply self-sealing joint plug is connected with 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 with 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 circulating 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, the oil inlet hose and the refueling joint from the auxiliary integrated oil tank, install a plug in the installation hole of the refueling self-sealing joint, install a removable breathing valve in the breathing valve installation groove, and connect the breathing valve to the corresponding end of the circulation hose;

[0036] The oil supply self-sealing joint plug in the auxiliary integrated oil tank is taken out from the joint installation groove and connected 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 with 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 with 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, a circulation joint and the like 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 the like are provided on the fuel tank, and accessories are installed to avoid exceeding the outer envelope of the fuel tank, thereby saving 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 through a hose, so that docking and separation are convenient, and the fuel tank can be disassembled and assembled in a state with oil; the fuel tank is modularly designed, and can be used individually or in series, so as to be well adapted to the modular design requirements of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

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

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

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

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

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

[0046] Figure 6 is a schematic diagram of the installation of an 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 is a schematic diagram of the installation of an aircraft fuel tank system provided in Example 2 of the present application;

[0049] Fig. 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] Fig.10 is a schematic diagram of the installation of an aircraft fuel tank system provided in Embodiment 3 of the present application;

[0051] in:

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

[0053] In order to better illustrate the present 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 construed as limitations on the present application. DETAILED DESCRIPTION

[0054] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related 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 shall have the usual meanings understood by those of ordinary skill in the art to which this application belongs. The words used in the description of this application to indicate orientation 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 indicates 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 specified 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] Embodiment 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 top first axial guide groove, a top axial connecting cavity, a top second axial guide groove, a bottom third axial guide groove, an outer cable and pipeline axial routing groove, one end has an end first radial guide groove, and the other end has an end second radial guide groove.

[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, 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 second radial guide groove at the end has a breathing valve mounting groove. Both ends of the outer cable and pipeline axial routing groove extend to both ends of the fuel tank 1 for external cable and pipeline routing.

[0062] 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 opened in the bottom wall of the top axial communication cavity and is connected to the oil extraction connector 14; the oil extraction 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 lateral inlet that are interconnected and perpendicular to each other.

[0063] The fuel pump 4 is detachably mounted in the fuel pump mounting 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 mounting 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 mounted in the plug mounting groove.

[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 installation 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 installation groove. The circulation joint 17 is installed in the circulation joint installation hole and extends into the oil 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 joint 2, the refueling joint 12, and the circulation joint 17 are connected to the oil supply joint mounting groove, the refueling joint mounting groove, and the circulation joint mounting groove side wall by screws through the flange edge, and the oil supply joint 2, the refueling joint 12, and the circulation joint 17 are provided with two sealing grooves on the outer wall, and the sealing ring is installed, and the oil supply joint mounting hole, the refueling joint mounting hole, and the circulation joint mounting hole are interference fit to ensure the sealing effect. Among them, the assembly relationship between the circulation joint 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-mentioned 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, 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 discharge valve 23 is connected to the other end of the refueling hose 20, and the refueling discharge valve 23 is fixed to the aircraft fuel tank compartment 18 by screws. Figure 5 shown.

[0070] In the above-mentioned embodiment of the disclosed aircraft fuel tank system, when refueling, fuel can be refueled from the refueling and drain valve 23, 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. 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 the smoothness of refueling.

[0071] In the above-mentioned embodiment of the disclosed aircraft fuel tank system, when draining oil, oil can be drawn from the filling and draining 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 draining 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 the smoothness of the 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 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.

[0073] In the above-mentioned embodiment of the disclosed aircraft fuel tank system, during the maneuvering of the aircraft, 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 surface, thereby ensuring the continuity of fuel supply to the engine, and 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 after the inlet end of the oil extraction connector 14 partially contacts the wall of the fuel tank 1, resulting in a situation where fuel cannot be supplied.

[0074] Embodiment 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 by the oil delivery self-sealing joint socket 5.

[0077] In the auxiliary integrated fuel tank, remove 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, and install the plug 11 in the fuel supply connector installation 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 of the main integrated fuel tank and the auxiliary integrated fuel tank is fixed to the aircraft fuel tank compartment 18 by screws, and 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, and the fuel supply self-sealing joint plug 8 is connected to the fuel supply self-sealing joint socket 22, and 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, and 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, and the refueling discharge valve 23 is connected to the other end of the refueling hose 20, and the refueling discharge 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 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 fuel, the fuel enters the fuel tank 1 through the flow joint 17, the flow hose 16, the oil transfer 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 the fuel from the aircraft fuel tank system disclosed in the second embodiment, the fuel can be pumped out from the filling and draining 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 draining 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 to allow air to flow 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 the smoothness of the fuel draining.

[0082] The aircraft fuel tank system disclosed in the second embodiment can use the fuel pump 4 of the main integrated fuel tank to draw fuel from the fuel tank 1 during refueling. 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 flow 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 fuel supply.

[0083] In the aircraft fuel tank system disclosed in the second embodiment, during the maneuvering of the aircraft, the oil extraction connector 14 in the main integrated fuel tank 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 surface, thereby ensuring the continuity of fuel supply to the engine, and 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 after the inlet end of the oil extraction connector 14 partially contacts the wall of the fuel tank 1, resulting in a situation where fuel cannot be supplied.

[0084] Embodiment three:

[0085] 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.

[0086] The breathing valve 15 in the main integrated oil tank is taken out from the breathing valve installation groove and replaced by 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 installation hole of the refueling self-sealing joint. Fig. 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 of 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, and 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 discharge valve 23 is connected to the other end of the refueling hose 20, and the refueling discharge valve 23 is fixed to the aircraft fuel tank compartment 18 by screws, as shown in FIG. Fig.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 fuel, 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 smoothness of refueling.

[0091] When draining the fuel from the aircraft fuel tank system disclosed in the third embodiment, the fuel can be pumped out from the filling and draining 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 draining 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 to allow air to flow 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 the smoothness of the draining.

[0092] The aircraft fuel tank system disclosed in the third embodiment can use the fuel pumps 4 of the main integrated fuel tank and the auxiliary integrated fuel tank to draw fuel from the fuel tank 1 during refueling. 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 flow 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 fuel supply.

[0093] In the aircraft fuel tank system disclosed in the third embodiment, during the maneuvering of the aircraft, 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 movement direction is consistent with the movement direction of the fuel in the fuel tank 1, and can always be located below the liquid surface, thereby ensuring the continuity of fuel supply to the engine, and 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 after the inlet end of the oil extraction connector 14 partially contacts the wall of the fuel tank 1, resulting in a situation where fuel cannot be supplied.

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

[0095] The accessories such as the oil supply connector 2, the oil extraction hose 3, the fuel pump 4, the oil supply hose 6, the oil supply self-sealing connector plug 8, the refueling self-sealing connector plug 9, the oil 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 are integrated on the fuel tank 1, and when assembled on the aircraft, the assembly efficiency can be higher;

[0096] The guide groove, mounting groove, mounting hole, connecting cavity and other structures are provided on the oil tank 1 to install the accessories, so as to avoid exceeding the outer envelope of the oil tank 1 and save the installation space;

[0097] The oil 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 through a hose, which is convenient for docking and separation, and the oil tank 1 can be disassembled and assembled in the oil-containing state;

[0098] The fuel tank 1 is modularly designed and can be used alone 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 substitutions to the relevant technical features, and the technical solutions after these changes or substitutions 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 comprises a fuel tank (1), a fuel supply joint (2), a fuel extraction hose (3), a fuel pump (4), a fuel supply hose (6), a fuel supply self-sealing joint plug (8), a refueling self-sealing joint plug (9), a fuel inlet hose (10), a refueling joint (12), a fuel extraction hose (13), a fuel extraction joint (14), a circulation hose (16), and a circulation joint (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; 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 flow joint mounting groove; one end of the top axial connecting cavity has a fuel supply joint mounting hole, 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; 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 of which 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 (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 an 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 installed in the plug installation 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 installation groove. The refueling joint (12) is installed in the refueling joint installation 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.

2. The aircraft fuel tank system according to claim 1, characterized in that: The two ends of the oil tank (1) adopt a dome design; 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, characterized in that: 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, characterized in that: The pipeline interfaces of the fuel supply joint (2), the refueling joint (12), the circulation joint (17), the fuel pump (4), the breathing valve (15), the fuel supply self-sealing joint plug (8), and the refueling self-sealing joint 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, characterized in that: The oil supply joint (2), the oil filling joint (12), and the circulation joint (17) are connected to the side walls of the oil supply joint installation groove, the oil filling joint installation groove, and the circulation joint installation groove by screws through flange edges; Two sealing grooves are arranged on the outer walls of the oil supply joint (2), the refueling joint (12) and the circulation joint (17), and sealing rings are installed thereon, 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 5, characterized in that: The integrated oil 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).

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

8. The aircraft fuel tank system according to claim 7, characterized in that: 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 part 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 filling and draining valve (23). The filling and draining valve (23) is fixed to the aircraft fuel tank compartment (18) by screws.

9. The aircraft fuel tank system according to claim 1, characterized in that: There are two integrated fuel tanks, one is a main integrated fuel tank and the other is a secondary integrated fuel tank; One end of the circulation 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 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) are removed from the auxiliary integrated fuel tank, a plug (11) is installed in the fuel supply connector installation hole, a breathing valve (15) is detachably installed in the breathing valve installation 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 fuel tank (1) in 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 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.

10. The aircraft fuel tank system according to claim 1, characterized in that: There are two integrated fuel tank packages, one is a main integrated fuel tank and the other is a secondary integrated fuel tank; One end of the circulation 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 installation hole of the refueling self-sealing joint, a removable respirator valve (15) is installed in the respirator valve installation groove, and the respirator 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 fuel tank (1) in 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 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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