CN219325923U

CN219325923U - Aircraft negative overload oil supply system

Info

Publication number: CN219325923U
Application number: CN202321416144.6U
Authority: CN
Inventors: 叶成海; 郝树奇; 任航; 高文文
Original assignee: Shaanxi Dexin Intelligent Technology Co ltd
Current assignee: Shaanxi Dexin Intelligent Technology Co ltd
Priority date: 2023-06-06
Filing date: 2023-06-06
Publication date: 2023-07-11
Anticipated expiration: 2033-06-06

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to an aircraft negative overload oil supply system, which comprises an oil supply tank, a negative overload oil tank and an oil supply unit communicated with the negative overload oil tank, wherein the oil supply unit is connected with the oil supply tank; the negative overload oil tank is positioned at the bottom of the oil supply tank, a gravity check valve is arranged on the inner wall of the top of the negative overload oil tank, and a first turning plate check valve is arranged on the side wall of the negative overload oil tank; through setting up gravity check valve and first board check valve that turns over, can make the aircraft supply oil tank when normal flight and be the oil feed of burden overload oil tank, also can avoid the oil inflow supply oil tank in the burden overload oil tank simultaneously, gravity check valve closes when the aircraft produces the burden overload, and the oil of supply oil tank can supply oil to the burden overload oil tank through first board check valve, guarantees that the oil of burden overload oil tank can stabilize the oil feed through the oil supply unit, simple structure with low costs for the oil feed is reliable and stable when the aircraft burden is overloaded.

Description

Aircraft negative overload oil supply system

Technical Field

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a negative overload oil supply system of an aircraft.

Background

For a motorized fuel aircraft, corresponding actions are generally completed as required, and the aircraft may be overloaded negatively, such as by tipping over, when the corresponding actions are completed; when the aircraft is in negative overload, the fuel system of the aircraft is generally required to have certain negative overload oil supply resistance, so that the oil supply tank can ensure stable oil supply for the aircraft when the aircraft flies in negative overload.

The conventional practice is to isolate a negative overload oil tank from the oil supply tank, and ensure the stable oil absorption of the aircraft under the negative overload through a follow-up flexible oil extractor. The follow-up flexible oil extractor consists of a balancing weight and a rubber hose, can shake with the aircraft in a maneuvering way, but has high requirements on the quality of the rubber hose of the follow-up flexible oil extractor, high cost, and can reduce the service life and the storage life of the rubber hose due to the fact that the rubber hose is in an oil immersion state for a long time, so that the rubber hose is easy to age and lose efficacy, the shaking degree of the follow-up aircraft is reduced, the oil supply of the aircraft is unstable, the anti-negative overload capacity of the aircraft is invalid, dangerous actions of air parking can occur during flying, the maneuvering performance of the aircraft is reduced, the reliability of oil supply is reduced, and the use requirement cannot be met.

Disclosure of Invention

The utility model aims to provide an aircraft negative overload oil supply system, which solves the problem of low oil supply reliability when a fuel aircraft is in negative overload.

The technical scheme for achieving the purposes is as follows:

the aircraft negative overload oil supply system is characterized by comprising an oil supply tank, a negative overload oil tank arranged in the oil supply tank and an oil supply unit communicated with the negative overload oil tank; the negative overload oil tank is positioned at the bottom of the oil supply tank, the top of the negative overload oil tank is provided with a gravity check valve, and the side wall of the negative overload oil tank is provided with a first turning plate check valve.

Further defined, the side wall of the negative overload oil tank is connected or disconnected with the side wall of the oil supply tank.

Further limited, when the side wall of the negative overload oil tank is connected with the side wall of the oil supply tank, the negative overload oil tank comprises a top plate and three side plates, one top plate and three side plates are connected with the bottom of the oil supply tank and any side wall of the oil supply tank to form the negative overload oil tank in a surrounding mode, the gravity check valves are arranged on the top plate, the number of the first turning plate check valves is three, and the three first turning plate check valves are respectively arranged on the three side plates.

Further limited, when the side wall of the negative overload oil tank is not connected with the side wall of the oil supply tank, the negative overload oil tank comprises a top plate and four side plates, one top plate and four side plates are connected with the bottom of the oil supply tank to form the negative overload oil tank in a surrounding mode, the gravity check valves are arranged on the top plate, the number of the first turning plate check valves is four, and the four first turning plate check valves are respectively arranged on the four side plates.

Further limited, the oil supply unit includes oil supply pipe and the oil pump of being connected with oil supply pipe, the oil pump sets up in the outside of oil supply tank, oil supply pipe's head end is from the outside of oil tank to the inside of burden overload oil tank, and first oil inlet has been seted up to oil supply pipe's head end, first oil inlet is relative with the roof, be provided with the branch pipe with oil supply pipe intercommunication on the oil supply pipe, the second oil inlet has been seted up on the branch pipe, the second oil inlet is located the below of first oil inlet, and the terminal surface of second oil inlet is relative to the bottom slope setting of oil supply tank, and the second oil inlet is relative with the bottom of oil supply tank, is provided with the second on the second oil inlet and turns over the check valve, the bottom of second turns over the check valve and rotates with the bottom of second oil inlet and be connected.

Further limited, an included angle between the end face of the second oil inlet and the bottom plate of the oil supply tank is 25-45 degrees.

Further defined, the ratio of the caliber of the first oil inlet to the caliber of the second oil inlet is 1:1.

Further defined, the oil supply pipe is a metal pipe.

Further defined, the ratio of the height of the interior of the oil supply tank to the height of the side plate is 3-4:1.

Further defined, the distance between the second oil inlet and the bottom of the oil supply tank is 10-15 mm.

The utility model has the beneficial effects that:

1. according to the utility model, the negative overload oil tank is arranged at the bottom in the oil supply tank, the gravity check valve is arranged at the top of the negative overload oil tank, the first turning plate check valve is arranged at the side part of the negative overload oil tank, and the gravity check valve and the first turning plate check valve are arranged, so that the oil supply tank can supply oil for the negative overload oil tank when an aircraft is in normal flight, and meanwhile, the oil in the negative overload oil tank can be prevented from flowing into the oil supply tank, the gravity check valve is closed when the aircraft is in negative overload, the oil in the oil supply tank can supply oil to the negative overload oil tank through the first turning plate check valve, the oil supply unit can be used for stably supplying oil to the oil for the negative overload oil tank, and the structure is simple, the cost is low, and the oil supply is stable and reliable when the aircraft is in negative overload.

2. Through setting up first oil inlet and second oil inlet on oil feed pipe, through setting up the downward sloping of second oil inlet port to set up the second on the second oil inlet and turn over the board check valve, make can supply oil simultaneously through first oil inlet and second oil inlet when the aircraft normally flies, the second oil inlet is closed when the burden is overloaded, and the oil pump is the stable oil supply of aircraft through first oil inlet, the stable reliable of oil supply when guaranteeing the aircraft burden and overload.

3. The utility model has simple structure, can be suitable for small unmanned aerial vehicles, can be suitable for manned aircrafts, has wide application range, can ensure stable oil supply of aircrafts in the case of negative overload, and has strong reliability.

Drawings

FIG. 1 is a schematic view of the structure of the negative overload fuel tank of the present utility model in a middle position of the fuel supply tank;

FIG. 2 is a schematic diagram of the overall structure of FIG. 1;

in the figure: 10-an oil supply tank; 20-a negative overload oil tank; 21-top plate; 22-side plates; 30-a gravity check valve; 40-branch pipes; 41-a second flap check valve; 50-an oil supply pipe; 51-a first oil inlet; 60-an oil pump; 70-a first flap check valve.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present application more clear, the technical solutions of the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present application. It will be apparent that the described embodiments are some, but not all, of the embodiments of the present application. All other embodiments, which can be made by one of ordinary skill in the art without the benefit of the present disclosure, are intended to be within the scope of the present application based on the described embodiments.

Unless otherwise defined, technical or scientific terms used herein should be given the ordinary meaning as understood by one of ordinary skill in the art to which this application belongs. The terms "first," "second," and the like, as used herein, do not denote any order, quantity, or importance, but rather are used to distinguish one element from another. The word "comprising" or "comprises", and the like, means that elements or items preceding the word are included in the element or item listed after the word and equivalents thereof, but does not exclude other elements or items. The terms "connected" or "connected," and the like, are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect. "upper", "lower", "left", "right", etc. are used merely to indicate relative positional relationships, which may also be changed when the absolute position of the object to be described is changed.

The embodiment provides a negative overload oil supply system of an aircraft, which comprises an oil supply tank 10, a negative overload oil tank 20 arranged in the oil supply tank 10 and an oil supply unit communicated with the negative overload oil tank 20, wherein the oil supply tank 10 is filled with oil firstly during oil filling; the negative overload oil tank 20 is arranged in the oil supply tank 10, the negative overload oil tank 20 can be selectively arranged in the middle position in the oil supply tank 10, and can be selectively connected with any side wall of the oil supply tank 10, and the gravity check valve 30 is arranged at the top of the negative overload oil tank 20, so that oil in the oil supply tank 10 can flow into the negative overload oil tank 20 through the gravity check valve 30 when an aircraft flies normally or is in positive overload flight, and the gravity check valve 30 is in an open state at the moment; meanwhile, a first turning plate one-way valve 70 is arranged on the side part of the negative overload oil tank 20, the first turning plate one-way valve 70 is also arranged in the negative overload oil tank 20, and the first turning plate one-way valve 70 is close to the bottom of the oil supply tank 10. In the flight process of the aircraft, whether in overload or negative overload or normal state, the oil in the oil supply tank 10 can supply oil to the negative overload oil tank 20 through the first flap check valve 70, and meanwhile, the first flap check valve 70 is used for preventing the oil in the negative overload oil tank 20 from being discharged into the oil supply tank 10, so that the negative overload oil tank 20 can supply oil stably, the oil in the negative overload oil tank 20 can be prevented from overflowing, and the stable oil supply of the aircraft in the negative overload state can be ensured.

Specifically, the negative overload oil tank 20 includes a top plate 21 and side plates 22, when the negative overload oil tank 20 is connected with any side wall in the oil supply tank 10, the number of the side plates 22 is three, the three side plates 22 and the top plate 21 simultaneously surround together with the bottom plate and the side wall of the oil supply tank 10 to form the negative overload oil tank 20, at this time, the number of the first flap check valves 70 is three, the three first flap check valves 70 are respectively installed on the three side plates 22, and the gravity check valve 30 is installed on the top plate 21; referring to fig. 1, when the negative overload oil tank 20 is installed at the middle position of the oil supply tank 10, the number of the side plates 22 is four, the four side plates 22 and the top plate 21 are simultaneously surrounded with the bottom plate of the oil supply tank 10 to obtain the negative overload oil tank 20, at this time, four first flap check valves 70 are respectively installed on the four side plates 22, and the gravity check valve 30 is installed on the top plate 21.

The oil supply unit includes an oil supply pipe 50 and an oil pump 60 connected to the oil supply pipe 50, and a head end of the oil supply pipe 50 extends from an outside of the oil supply tank 10 to an inside of the negative overload oil tank 20, preferably the head end of the oil supply pipe 50 extends from a bottom of the oil supply tank 10 to the inside of the negative overload oil tank 20; the oil pump 60 is provided outside the oil supply tank 10, and the oil pump 60 is used to pump out the oil in the negative overload oil tank 20 through the oil supply pipe 50.

The head end of the oil supply pipe 50 is provided with a first oil inlet 51, the end face of the first oil inlet 51 is horizontally arranged, the first oil inlet 51 is opposite to the top plate 21, and oil in the negative overload oil tank 20 can be pumped out through the first oil inlet 51 during positive overload or normal flight, so that the first oil inlet 51 is close to the top of the negative overload oil tank 20 but is not contacted with the negative overload oil tank, the oil supply pipe 50 is also provided with a branch pipe 40, the branch pipe 40 is communicated with the oil supply pipe 50, the branch pipe 40 is provided with a second oil inlet, the second oil inlet is positioned below the first oil inlet 51, the second oil inlet is close to the bottom of the oil supply tank 10, for example, the distance between the second oil inlet and the bottom of the oil supply tank 10 is 10-15 mm, and therefore oil can be sufficiently supplied when the oil quantity of the negative overload oil tank 20 is small; the second oil inlet faces the bottom of the oil supply tank 10, an included angle of 25-45 degrees exists between the second oil inlet and the bottom of the oil supply tank 10, for example, 30 degrees can be selected, meanwhile, a second turning plate one-way valve 41 is installed on the second oil inlet, the bottom of the second turning plate one-way valve 41 is rotationally connected with the bottom of the second oil inlet, the second turning plate one-way valve 41 turns upwards when an aircraft is in negative overload, the second oil inlet is blocked, at the moment, the first oil inlet 51 stably supplies oil to the aircraft through an oil pump 60 when the aircraft is in negative overload, and the oil inflow of the first oil inlet 51 is related to the oil consumption of the aircraft; by arranging the second turning plate one-way valve 41, the condition that the second oil inlet is communicated with the atmosphere to suck air due to the fact that the liquid level below the oil in the negative overload oil tank 20 is raised is avoided, so that the oil supply requirement of an aircraft is met, and the stable and reliable oil supply of the aircraft during the negative overload is ensured.

The ratio of the caliber of the first oil inlet 51 to the caliber of the second oil inlet is 1:1, the oil supply pipe 50 is a metal pipe, the second turning plate one-way valve 41, the first turning plate one-way valve 70 and the gravity one-way valve 30 are all made of metal materials, and the ratio of the height of the inside of the oil supply tank 10 to the height of the side plate 22 is 3-4:1, and can be 4:1.

The above is an embodiment of the present application. The foregoing embodiments and the specific parameters in the embodiments are only for clearly describing the verification process of the application, and are not intended to limit the scope of the application, which is defined by the claims, and all equivalent structural changes made by applying the descriptions and the drawings of the application are included in the scope of the application.

Claims

1. An aircraft negative overload oil supply system is characterized by comprising an oil supply tank (10), a negative overload oil tank (20) arranged inside the oil supply tank (10) and an oil supply unit communicated with the negative overload oil tank (20); the negative overload oil tank (20) is located at the bottom of the oil supply tank (10), a gravity check valve (30) is arranged at the top of the negative overload oil tank (20), and a first turning plate check valve (70) is arranged on the side wall of the negative overload oil tank (20).

2. Aircraft negative overload oil supply system according to claim 1, characterized in that the side wall of the negative overload oil tank (20) is connected or disconnected with the side wall of the oil supply tank (10).

3. The aircraft negative overload oil supply system according to claim 2, wherein when the side wall of the negative overload oil tank (20) is connected with the side wall of the oil supply tank (10), the negative overload oil tank (20) comprises a top plate (21) and three side plates (22), one top plate (21) and three side plates (22) are connected with the bottom of the oil supply tank (10) and any side wall of the oil supply tank (10) to form the negative overload oil tank (20), the gravity check valves (30) are arranged on the top plate (21), the number of the first turning plate check valves (70) is three, and the three first turning plate check valves (70) are respectively arranged on the three side plates (22).

4. The aircraft negative overload oil supply system according to claim 2, wherein when the side wall of the negative overload oil tank (20) is not connected with the side wall of the oil supply tank (10), the negative overload oil tank (20) comprises a top plate (21) and four side plates (22), one top plate (21) and four side plates (22) are connected with the bottom of the oil supply tank (10) to form the negative overload oil tank (20), the gravity check valves (30) are arranged on the top plate (21), the number of the first turning plate check valves (70) is four, and the four first turning plate check valves (70) are respectively arranged on the four side plates (22).

5. The aircraft negative overload oil supply system according to claim 3 or 4, wherein the oil supply unit comprises an oil supply pipe (50) and an oil pump (60) connected with the oil supply pipe (50), the oil pump (60) is arranged on the outer side of the oil supply tank (10), the outer side of the oil supply tank (10) is extended to the inside of the negative overload oil tank (20) from the head end of the oil supply pipe (50), a first oil inlet (51) is formed in the head end of the oil supply pipe (50), the first oil inlet (51) is opposite to the top plate (21), a branch pipe (40) communicated with the oil supply pipe (50) is arranged on the oil supply pipe (50), a second oil inlet is formed in the branch pipe (40), the second oil inlet is located below the first oil inlet (51), the end face of the second oil inlet is obliquely arranged relative to the bottom plate of the oil supply tank (10), the second oil inlet is opposite to the bottom of the oil supply tank (10), a second flap one-way valve (41) is arranged on the second oil inlet, and the bottom of the second flap valve (41) is rotatably connected with the bottom end of the second oil inlet.

6. The aircraft negative overload oil supply system according to claim 5, wherein an angle between an end face of the second oil inlet and a bottom plate of the oil supply tank (10) is 25 ° to 45 °.

7. The aircraft negative overload oil supply system of claim 6, wherein the ratio of the bore of the first oil inlet (51) to the bore of the second oil inlet is 1:1.

8. The aircraft negative overload oil supply system of claim 7, wherein the oil supply pipe (50) is a metal pipe.

9. The aircraft negative overload oil supply system of claim 7, wherein the ratio of the height of the interior of the oil supply tank (10) to the height of the side panels (22) is 3-4:1.

10. The aircraft negative overload oil supply system according to claim 7, wherein the distance between the second oil inlet and the bottom of the oil supply tank (10) is 10-15 mm.