Integrated fuel supply device for aircraft negative overload and aircraft fuel system

Abstract

The present invention provides an integrated fuel supply device and an aircraft fuel system for negative overload aircraft. The integrated fuel supply device includes a first fuel suction assembly and a second fuel suction assembly. The first fuel suction assembly includes a cover, a connecting pin, and a first fuel suction pipe. The cover is connected to the first fuel suction port via the connecting pin, allowing the cover to rotate around the connecting pin relative to the first fuel suction pipe. The second fuel suction assembly is connected to the bottom of the oil collecting tank and includes a valve body, a second fuel suction pipe, and an fuel outlet pipe. The second fuel suction pipe and the fuel outlet pipe extend from the valve body, respectively. The first fuel suction pipe is connected to the valve body so that: the valve body is connected to the first fuel suction pipe, the second fuel suction pipe, and the fuel outlet pipe, the axis of the first fuel suction pipe and the axis of the fuel outlet pipe are located in the same plane, and the second fuel suction port on the second fuel suction pipe is higher than the plane. The integrated fuel supply device of the present invention, through a simple principle and structure, achieves uninterrupted fuel supply to the engine of the aircraft under negative overload conditions, has good stability, high integration, and simple assembly.

Description

Technical Field

[0001] The present invention relates to the technical field of aviation machinery control, and in particular to an integrated fuel supply device for aircraft negative overload and an aircraft fuel system comprising the integrated fuel supply device for aircraft negative overload. Background Art

[0002] During flight, when negative overload occurs, the fuel in the fuel tank will fall out of the bottom of the tank and onto the top due to changes in flight attitude. To minimize unusable fuel, the fuel intake is typically located at the bottom of the tank. If no measures are taken, the intake will be exposed to the oil surface during negative overload, resulting in an interruption in engine fuel supply and the aircraft being unable to fly normally. Therefore, it is necessary to ensure uninterrupted fuel supply to the engine under continuous negative overload conditions. Current negative overload fuel supply systems used on aircraft, such as multi-pump high-low position layout, dual-end fuel supply pumps, accumulator tanks, and overload tanks, are complex, increasing aircraft weight and cost and making them unsuitable for some lightweight aircraft.

[0003] Chinese patent CN201922143192.2 provides a negative overload oil supply device for a small drone. The negative overload oil supply device includes an oil inlet pipe, a sealing ring, a bearing, a connecting shaft, a fastening screw, and an oil outlet pipe. The device, which includes multiple components such as bearings, has a complex principle and requires high calculations for bearing design, making assembly of the device complex.

[0004] Therefore, there is a need to improve the aircraft negative overload fuel supply device. Summary of the Invention

[0005] The technical problem to be solved by the present invention is to overcome the defects of the existing aircraft negative overload fuel supply device, such as complex principles and structures, high design and calculation requirements, and complex assembly, and to provide an integrated fuel supply device for aircraft negative overload and an unmanned aerial vehicle fuel system including the integrated fuel supply device for aircraft negative overload, which is particularly suitable for light aircraft with strict requirements on cost and weight.

[0006] The technical solution of the present invention is:

[0007] An integrated oil supply device for aircraft negative overload, the special feature of which is that the integrated oil supply device is used to be installed at the bottom of the aircraft's oil collecting tank and includes a first oil suction assembly and a second oil suction assembly;

[0008] The first oil suction assembly includes a cover, a connecting pin and a first oil suction pipe,

[0009] a cover connected to the first oil suction port at a bottom of the first oil suction port at one end of the first oil suction pipe via a connecting pin, such that the cover can rotate relative to the first oil suction pipe about the connecting pin, thereby moving the cover between a closed position that closes the first oil suction port and an open position that opens the first oil suction port;

[0010] The second oil suction assembly is used to be connected to the bottom of the oil collecting tank and includes a valve body, a second oil suction pipe and an oil outlet pipe.

[0011] The second oil suction pipe and the oil outlet pipe extend from the valve body respectively.

[0012] The second oil suction port at one end of the second oil suction pipe is open;

[0013] The other end of the first oil suction pipe of the first oil suction assembly is connected to the valve body of the second oil suction assembly, so that: the valve body is in communication with the first oil suction pipe, the second oil suction pipe and the oil outlet pipe, the axis of the first oil suction pipe and the axis of the oil outlet pipe are located in the same plane, and the second oil suction port on the second oil suction pipe is higher than the plane.

[0014] Furthermore, the other end of the first oil suction pipe is provided with a first flange protruding radially outward; the valve body of the second oil suction assembly is provided with a second flange opposite to the first flange; and the first flange is connected to the second flange.

[0015] Furthermore, the integrated oil supply device also includes a fastening assembly and a sealing gasket, the sealing gasket is located between the first flange and the second flange, and the first flange, the sealing gasket and the second flange are connected via the fastening assembly.

[0016] Furthermore, the first oil suction pipe of the first oil suction assembly and the valve body of the second oil suction assembly are formed integrally.

[0017] Furthermore, the oil outlet pipe of the second oil suction assembly is provided with a connecting portion for connecting to the oil collecting tank. The connecting portion includes a groove located on the oil outlet pipe and a convex portion protruding radially outward from the oil outlet pipe. The groove and the convex portion are used to jointly limit the wall of the oil collecting tank.

[0018] Furthermore, a hole is provided on the convex portion, and the hole is used to insert a fuse to prevent the integrated oil supply device from rotating loose.

[0019] An aircraft fuel system comprising the above-mentioned integrated fuel supply device for aircraft negative overload.

[0020] The beneficial effects of the present invention are:

[0021] 1. The integrated fuel supply device for aircraft under load according to the present invention comprises a first oil suction assembly and a second oil suction assembly. The first oil suction assembly has a cover at its first oil suction port that automatically closes when the aircraft is under load. The second oil suction port of the second oil suction assembly is open, and the oil outlet is provided on the second oil suction assembly. During normal flight, the cover of the first oil suction assembly is open, and oil from the bottom of the oil collection tank can be supplied through either the first or second oil suction assembly. During under load, the cover of the first oil suction assembly automatically closes, and oil from the top of the oil collection tank is supplied through the second oil suction port of the second oil suction assembly. Therefore, the integrated fuel supply device for aircraft under load, through a simple principle and structure, achieves uninterrupted fuel supply to the engine under under load conditions, exhibits excellent stability, and requires only the first and second oil suction assemblies to be connected, resulting in a high level of integration and simple assembly.

[0022] 2. When the first oil suction pipe is provided with a flange, the first oil suction assembly is a commercially available part. The integrated oil supply device of the present invention can be obtained by only processing the second oil suction assembly and connecting it to the flange of the first oil suction pipe, thereby saving processing time and labor costs.

[0023] 3. By integrally forming the first oil suction pipe of the first oil suction assembly and the valve body of the second oil suction assembly, the integrated oil supply device of the present invention is more integrated, does not require assembly during use, is more convenient to use, and has better stability.

[0024] 4. The oil outlet pipe of the second oil suction assembly is provided with a connection portion connected to the oil collecting tank, so that the integrated oil supply device for aircraft negative overload of the present invention can be quickly connected to the existing aircraft fuel system.

[0025] 5. The aircraft fuel system of the present invention incorporates an integrated fuel supply device for negative overload conditions. When the aircraft is negatively overloaded, the cover of the first oil suction assembly automatically closes, and oil from the top of the oil collection tank is supplied through the second oil suction port of the second oil suction assembly. This simple principle and structure ensures uninterrupted fuel supply to the engine even under sustained negative overload conditions. Furthermore, the aircraft fuel system of the present invention requires only drilling a hole in the oil collection tank to connect to the integrated fuel supply device, making it easy to implement, cost-effective, and highly adaptable. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The features and advantages of the present invention will become more readily understood through the following description with reference to the accompanying drawings, which are not drawn to scale and in which some features are exaggerated or minimized to show details of particular components.

[0027] Figure 1 is a front view showing a working state of an integrated fuel supply device for negative overload of an aircraft according to an exemplary embodiment of the present invention when the aircraft is in normal flight;

[0028] Figure 2 is a front view showing a working state of an integrated fuel supply device for negative overload of an aircraft according to an exemplary embodiment of the present invention when the aircraft is negatively overloaded;

[0029] Figure 3 4 is a schematic exploded perspective view of an integrated fuel supply device for negative overload of an aircraft according to an exemplary embodiment of the present invention.

[0030] Reference numerals:

[0031] 1-first oil suction assembly, 101-cover, 102-connecting pin, 103-first oil suction pipe, 1031-first oil suction port, 1032-first flange;

[0032] 2 - second oil suction assembly, 201 - valve body, 2011 - second flange, 202 - second oil suction pipe, 2021 - second oil suction port, 203 - oil outlet pipe, 2031 - oil outlet, 2032 - connecting portion, 20321 - groove, 20322 - convex portion, 20323 - hole in the convex portion;

[0033] 3-fastening assembly, 301-bolt, 302-nut, 303-washer;

[0034] 4-Sealing gasket. DETAILED DESCRIPTION

[0035] The present invention will be described in detail below with reference to the accompanying drawings by way of exemplary embodiments of the present invention. It should be noted that the following detailed description of the present invention is for illustrative purposes only and is not intended to limit the present invention. In addition, the same reference numerals are used throughout the accompanying drawings to represent the same components.

[0036] The present invention provides an integrated oil supply device for aircraft negative overload and an aircraft fuel system comprising the integrated oil supply device for aircraft negative overload.

[0037] First refer to Figures 1 to 3 The integrated oil supply device for aircraft negative overload provided by the present invention is described. Figure 1 1 is a front view showing a working state of an integrated oil supply device for negative overload of an aircraft according to an exemplary embodiment of the present invention when the aircraft is in normal flight. Figure 2 1 is a front view showing a working state of an integrated fuel supply device for negative overload of an aircraft according to an exemplary embodiment of the present invention when the aircraft is negatively loaded. Figure 3 4 is a schematic exploded perspective view of an integrated fuel supply device for negative overload of an aircraft according to an exemplary embodiment of the present invention.

[0038] like Figures 1 to 3As shown, the integrated oil supply device for aircraft negative overload as an exemplary embodiment of the present invention can be installed at the bottom of an aircraft oil collecting tank, and can include a first oil suction assembly 1 and a second oil suction assembly 2 .

[0039] The first oil suction assembly 1 includes a cover 101, a connecting pin 102, and a first oil suction pipe 103. One end of the first oil suction pipe 103 is provided with a first oil suction port 1031 for receiving fuel from the aircraft's fuel collection tank. The cover 101 is connected to the bottom of the first oil suction port 1031 via the connecting pin 102. The cover 101 can rotate relative to the first oil suction pipe 103 about the connecting pin 102, allowing the cover 101 to move between a closed position, which seals the first oil suction port 1031, and an open position, which opens the first oil suction port 1031. When the aircraft is negatively loaded, the cover 101 automatically closes under the effect of the overload, thereby sealing the first oil suction port 1031. As shown, as a more optimal solution, the end surface of the first oil suction port 1031 can be inclined so that the cover 101 can rotate around the connecting pin 102 under the action of gravity when there is no overload, so that the first oil suction port 1031 is open, and when there is a negative overload, the cover 101 can fit tightly and reliably with the end surface of the first oil suction port 1031.

[0040] The second oil suction assembly 2 can be connected to the bottom of an aircraft's fuel collection tank and includes a valve body 201, a second oil suction pipe 202, and an oil outlet pipe 203. The valve body 201 can have any hollow interior shape and is shown as a square in the figure. An outlet port 2031 at one end of the oil outlet pipe 203 can be connected to the aircraft's fuel delivery pipeline to supply fuel from the fuel collection tank to the aircraft's engines. Those skilled in the art will appreciate that one end of the outlet port 2031 of the oil outlet pipe 203 is provided with external threads for connection to the fuel delivery pipeline. Furthermore, the distal end of the outlet pipe 203 is tapered to facilitate connection to the fuel delivery pipeline.

[0041] In some embodiments, the oil outlet pipe 203 of the second oil suction assembly 2 may be provided with a connection portion 2032 for connecting to the oil collection tank. Connection portion 2032 may include a groove 20321 located on the oil outlet pipe 203 and a protrusion 20322 protruding radially outward from the oil outlet pipe 203. Groove 20321 may circumscribe the oil outlet pipe 203, and protrusion 20322 may be positioned between groove 20321 and valve body 201. The shape of protrusion 20322 is not limited, and is specifically a hexagonal shape as shown. In this case, the form of connection portion 2032 is similar to a frame joint known in the art. Groove 20321 and protrusion 20322 are used to jointly constrain the wall of the oil collection tank, allowing the integrated oil supply device to be mounted thereto. Preferably, the connection portion 2032 is installed such that the axis of the oil outlet pipe 203 lies within a horizontal plane. By providing a connection portion 2032 connected to the oil collecting tank on the oil outlet pipe 203 of the second oil suction assembly 2, the integrated oil supply device for aircraft negative overload of the present invention can be quickly connected to the existing aircraft fuel system.

[0042] Those skilled in the art will understand that the installation method of the oil outlet pipe 203 of the second oil suction assembly 2 and the oil collecting tank is not limited to the above method, but can be changed according to actual conditions. For example, a flange can also be designed on the oil outlet pipe 203 to be threadedly connected to the oil collecting tank.

[0043] In an optional embodiment of the present invention, protrusion 20322 may be provided with a hole 20323 for inserting a fuse to prevent the integrated oil supply device from rotating loose. Specifically, a fuse installation component may be provided at a corresponding location on the wall of the oil collection tank, and the fuse may be connected to the component and hole 20323 in protrusion 20322 to prevent the integrated oil supply device from rotating loose.

[0044] The second oil suction pipe 202 and the oil outlet pipe 203 may extend from different sides of the valve body 201 in different directions.

[0045] The second oil suction port 2021 at one end of the second oil suction pipe 202 can remain open. The other end of the first oil suction pipe 103 of the first oil suction assembly 1 can be connected to the valve body 201 of the second oil suction assembly 2, such that: the valve body 201 is in communication with the first oil suction pipe 103, the second oil suction pipe 202, and the oil outlet pipe 203; the axis of the first oil suction pipe 103 and the axis of the oil outlet pipe 203 are located in the same plane, specifically, the axis of the first oil suction pipe 103 is parallel to the axis of the oil outlet pipe 203; and the second oil suction port 2021 on the second oil suction pipe 202 is above the plane. This allows, when the aircraft is under negative overload, oil from the top of the aircraft's fuel collection tank to be drawn into the integrated fuel supply device through the second oil suction port 2021 and to leave the integrated fuel supply device through the oil outlet port 2031 of the oil outlet pipe 203, thereby supplying fuel to the aircraft's engine.

[0046] According to the integrated oil supply device for aircraft negative overload of the present invention, the diameters of the first oil suction pipe 103 and the second oil suction pipe 202 can be determined according to the oil supply requirements of the aircraft engine, and it is necessary to ensure that the diameter of any one of the oil suction ports can meet the oil supply requirements of the engine when working alone.

[0047] The installation position of the second oil suction pipe 202 on the oil collecting tank can be based on installation and use requirements, and can be installed as much as possible so that the first oil suction port 1031 is located at the bottom of the oil collecting tank, thereby minimizing unusable oil.

[0048] The length of second oil suction pipe 202 can be calculated by first calculating the required oil volume for negative overload based on the negative overload time requirement, and then by considering the cross-sectional area (i.e., horizontal cross-sectional area) of the oil collection tank. Specifically, assuming the engine's fuel consumption during negative overload is X, the cross-sectional area of ​​the oil collection tank is S, the distance from the fuel level in the oil collection tank to the top of the oil collection tank at the onset of negative overload is h, and the distance from the cross-sectional area of ​​the second oil suction port to the bottom of the oil collection tank is n, then n = X / S + h.

[0049] The diameter and length of the first oil suction pipe 103 and the second oil suction pipe 202 should be designed so that: when the aircraft is in a normal flight state, the fuel in the oil collecting tank is at the bottom of the oil collecting tank. Figure 1 As shown, the first oil suction port 1031 and the second oil suction port 2021 of the integrated oil supply device are both immersed in oil and work at the same time; when the aircraft is in a negative overload flight state, the fuel in the oil collecting tank is located at the top of the oil collecting tank, as shown in FIG. Figure 2 As shown, the first oil suction port 1031 is exposed to the oil and is closed by the cover 101, and the second oil suction port 2021 is immersed in the oil to operate.

[0050] In an optional embodiment of the present invention, the other end of the first oil suction pipe 103 is provided with a first flange 1032 protruding radially outward. Figure 3 As can be clearly seen, the first flange 1032 is shown as having a triangular cross-section. However, this is merely an example and is not intended to limit the present invention. The cross-section of the first flange 1032 may be circular, rectangular, or the like. When the first oil suction pipe 103 is provided with a flange, the first oil suction assembly 1 is a commercially available part. The integrated oil supply device of the present invention can be obtained by simply machining the second oil suction assembly 2 and connecting it to the flange of the first oil suction pipe 103, thus saving machining time and labor costs.

[0051] The valve body 201 of the second oil suction assembly 2 may be provided with a second flange 2011 opposite to the first flange 1032 , and the shape of the second flange 2011 may match that of the first flange 1032 .

[0052] The first flange 1032 can be connected to the second flange 2011. The connection method between the first flange 1032 and the second flange 2011 is not limited. For example, the first flange 1032 can be welded to the second flange 2011 or can be connected to the second flange 2011 in a detachable manner, which will be described below.

[0053] In some embodiments of the present invention, the integrated oil supply device may further include a fastening assembly 3 and a sealing gasket 4. The sealing gasket 4 may be located between the first flange 1032 and the second flange 2011. The shape of the sealing gasket 4 corresponds to the shape of the second flange 2011 of the first flange 1032. The first flange 1032, the sealing gasket 4 and the second flange 2011 may be connected via the fastening assembly 3.

[0054] Specifically, the fastening assembly 3 may include a bolt 301, a nut 302, and a washer 303. The bolt 301 sequentially passes through the hole in the first flange 1032, the hole in the sealing gasket 4, the hole in the second flange 2011, and the hole in the gasket 303, and is threadedly connected to the nut 302. The number of fastening assemblies 3 is not limited. For example, if the cross-sections of the first flange 1032 and the second flange 2011 are triangular, the number of fastening assemblies 3 may be three, and the number of holes in the first flange 1032, the holes in the sealing gasket 4, and the holes in the second flange 2011 is three, corresponding to the number of fastening assemblies 3.

[0055] As described above, the integrated fuel supply device for aircraft negative overload of the present invention realizes uninterrupted fuel supply to the engine of the aircraft under negative overload conditions through a simple principle and structure, has good stability, and during assembly, only the first oil suction assembly needs to be connected to the second oil suction assembly. It has high integration, simple assembly, light weight, and low cost.

[0056] Furthermore, in certain embodiments of the present invention, the first oil suction pipe 103 of the first oil suction assembly 1 and the valve body 201 of the second oil suction assembly 2 can be integrally formed. In this case, the first oil suction pipe 103 extends directly from one side of the valve body 201. This makes the integrated oil supply device of the present invention more integrated, requires no assembly, and is more convenient to use and more stable.

[0057] The aircraft fuel system provided by the present invention and including the above-mentioned integrated fuel supply device for aircraft negative overload will now be described.

[0058] An aircraft fuel system, as an exemplary embodiment of the present invention, may include an oil collection tank, an oil pump, an oil pipeline, and the aforementioned integrated oil supply device for aircraft negative overload. The integrated oil supply device is mounted to the bottom of the oil collection tank. One end of the oil pipeline is connected to the oil outlet of the integrated oil supply device, and the other end is connected to the aircraft engine. The oil pump pumps the oil in the oil collection tank to deliver it to the engine via the oil pipeline.

[0059] The aircraft fuel system of the present invention, when in use, requires only drilling a hole in the existing fuel system's oil collection tank to connect to the integrated fuel supply device. This makes it easy to implement, cost-effective, and highly adaptable. Furthermore, due to the addition of the integrated fuel supply device for aircraft negative overload, the aircraft fuel system of the present invention automatically closes the cover of the first oil suction assembly during negative overload, allowing oil from the top of the oil collection tank to be supplied through the second oil suction port of the second oil suction assembly. This simple principle and structure ensures uninterrupted fuel supply to the engine even under sustained negative overload conditions.

[0060] The features mentioned and / or illustrated in the above description of the exemplary embodiments of the present invention may be incorporated into one or more other embodiments in the same or similar manner, combined with the features in other embodiments, or substituted for the corresponding features in other embodiments. The technical solutions obtained by such combination or substitution shall also be deemed to be included in the scope of protection of the present invention.

Claims

1. An integrated oil supply device for aircraft negative overload, characterized in that: The integrated oil supply device is used to be installed at the bottom of the oil collecting tank of the aircraft, and includes a first oil suction assembly and a second oil suction assembly; The first oil suction assembly includes a cover, a connecting pin and a first oil suction pipe, the cover being connected to the first oil suction port at a bottom portion of the first oil suction port at one end of the first oil suction pipe via the connecting pin, such that the cover is rotatable relative to the first oil suction pipe about the connecting pin, thereby moving the cover between a closed position that closes the first oil suction port and an open position that opens the first oil suction port; The second oil suction assembly is used to be connected to the bottom of the oil collecting tank and includes a valve body, a second oil suction pipe and an oil outlet pipe. The second oil suction pipe and the oil outlet pipe extend from the valve body respectively. The second oil suction port at one end of the second oil suction pipe is open; The other end of the first oil suction pipe of the first oil suction assembly is connected to the valve body of the second oil suction assembly, so that: the valve body is in communication with the first oil suction pipe, the second oil suction pipe, and the oil outlet pipe, the axis of the first oil suction pipe and the axis of the oil outlet pipe are located in the same plane, and the second oil suction port on the second oil suction pipe is higher than the plane.

2. The integrated fuel supply device for aircraft negative overload according to claim 1, characterized in that: The other end of the first oil suction pipe is provided with a first flange protruding radially outward; The valve body of the second oil suction assembly is provided with a second flange opposite to the first flange; The first flange is connected to the second flange.

3. The integrated oil supply device for aircraft negative overload according to claim 2, characterized in that The invention also includes a fastening assembly and a sealing gasket, wherein the sealing gasket is located between the first flange and the second flange, and the first flange, the sealing gasket and the second flange are connected via the fastening assembly.

4. The integrated fuel supply device for aircraft negative overload according to claim 1, characterized in that: The first oil suction pipe of the first oil suction assembly and the valve body of the second oil suction assembly are integrally formed.

5. The integrated fuel supply device for aircraft negative overload according to any one of claims 1 to 4, characterized in that: The oil outlet pipe of the second oil suction assembly is provided with a connecting portion for connecting to the oil collecting tank. The connecting portion includes a groove located on the oil outlet pipe and a convex portion protruding radially outward from the oil outlet pipe. The groove and the convex portion are used to jointly limit the wall of the oil collecting tank.

6. The integrated oil supply device for aircraft negative overload according to claim 5, characterized in that: The convex portion is provided with a hole, and the hole is used to insert a fuse to prevent the integrated oil supply device from rotating loose.

7. An aircraft fuel system comprising the integrated fuel supply device for aircraft negative overload according to any one of claims 1 to 6.

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