Oil supply system, power driving system and aircraft

Abstract

The utility model relates to an oil supply system, a power driving system and an aircraft, the oil supply system is connected with an engine and an oil tank, the oil supply system comprises an oil supply pipeline, a fuel pump and a one-way valve, and the fuel pump and the one-way valve are arranged on the oil supply pipeline between the engine and the oil tank; the multiple fuel pumps and the multiple one-way valves are arranged, the multiple fuel pumps are connected in series, the multiple one-way valves are connected in series, the fuel pumps and the one-way valves are arranged in parallel, and the multiple fuel pumps and the one-way valves are connected through oil supply pipelines. A plurality of fuel pumps and a plurality of one-way valves are arranged in series, the fuel pumps and the one-way valves are arranged in parallel, the fuel pumps and the one-way valves are communicated through oil supply pipelines, and various oil supply channels are formed between the fuel pumps and the one-way valves, so that the situation that a fuel system cannot work normally due to faults of a single fuel pump or one-way valve can be avoided; and the safety and the reliability of the oil supply system are improved.

Description

Technical Field

[0001] The utility model relates to the technical field of flight equipment, in particular to an oil supply system, a power drive system and an aircraft. Background Technique

[0002] Aircraft, especially unmanned helicopters, can use solid batteries, fuel generators, hybrid fuel and electricity, etc. as power sources, so that the unmanned aircraft can perform actions such as takeoff, turning, and landing. However, when using solid batteries, the electric drive motor drives the helicopter rotor to rotate, which is greatly affected by the ambient temperature, and the energy density of the battery is much lower than that of fuel, and the endurance is limited. Therefore, fuel power is still the most widely used power source for helicopters at present.

[0003] For the existing helicopter using a fuel engine as the power source, the fuel tank is placed on the left and right wings, and an oil supply pipeline is set to collect the fuel to the fuel tank, and then transported to the engine, and a set of transmission system is set. However, in the design of this oil supply system, only one circuit is set to transport the fuel to the engine. When the fuel pump in the circuit fails, the fuel system will not be able to supply oil, which will affect the safety and reliability of the aircraft. Content of the Utility Model

[0004] In order to solve the above technical problem that when a single part in the circuit is damaged in the current helicopter using a fuel engine as the power source, the safety and reliability of flight cannot be guaranteed, the utility model provides an oil supply system and an aircraft.

[0005] To achieve the above object, the utility model provides an oil supply system connecting an engine and a fuel tank, including an oil supply pipeline, a fuel pump and a check valve. The fuel pump and the check valve are arranged on the oil supply pipeline between the engine and the fuel tank; a plurality of the fuel pumps and a plurality of the check valves are respectively arranged in series, and the fuel pumps and the check valves are arranged in parallel between them. A plurality of the fuel pumps and the check valves are connected by the oil supply pipeline.

[0006] Further, it further includes a filtering device. One end of the filtering device is connected to the fuel tank through the oil supply pipeline, and the other end is connected to the fuel pump and the check valve through the oil supply pipeline.

[0007] Further, a plurality of the fuel tanks are provided, and the plurality of the fuel tanks are connected to one filtering device through the oil supply pipeline.

[0008] Further, it further includes a ventilation pipeline. An exhaust port is arranged on the engine, and the ventilation pipeline connects the exhaust port and the plurality of fuel tanks.

[0009] Further, the plurality of fuel tanks are interconnected through the ventilation pipeline.

[0010] Further, it further includes a pressure relief valve and a gas valve, and the pressure relief valve and the gas valve are arranged on the ventilation pipeline.

[0011] Further, the engine, the gas valve, the pressure relief valve and the fuel tank are sequentially arranged on the ventilation pipeline, and the gas valve is communicated with the outside air.

[0012] Further, it further includes an oil return pipeline. An oil return port is arranged on the engine, and both ends of the oil return pipeline are respectively communicated with the oil return port and any one of the fuel tanks.

[0013] Another object of this embodiment is to provide a power drive system, and this power drive system is provided with the above-mentioned fuel supply system.

[0014] Another object of this embodiment is to provide an aircraft, and this aircraft is provided with the above-mentioned power drive system and fuel supply system.

[0015] The above technical solution of the present utility model has the following advantages compared with the prior art:

[0016] (1) A plurality of fuel pumps and a plurality of one-way valves are arranged in series, and the fuel pumps and the one-way valves are arranged in parallel, and the plurality of fuel pumps and the one-way valves are communicated through a fuel supply pipeline. A variety of fuel supply channels are formed between the plurality of fuel pumps and the one-way valves. Therefore, it can avoid the failure of the fuel system due to the failure of a single fuel pump or one-way valve, and improve the safety and reliability of the fuel supply system;

[0017] (2) The engine is arranged at the center of gravity of the aircraft, and a plurality of fuel tanks are symmetrically arranged about the center of gravity, avoiding the center of gravity shift caused by fuel consumption, and further affecting the flight stability;

[0018] (3) The exhaust gas discharged from the engine is introduced into the fuel tank through a pressure reducing valve and a gas valve for pressurization, ensuring that the pressure inside and outside the fuel tank is consistent, and avoiding faults such as the deformation of the fuel tank structure caused by the pressure difference. Description of the Drawings

[0019] In order to more clearly illustrate the technical solutions in the embodiments of the present utility model, the following will briefly introduce the drawings required for the description of the embodiments. Obviously, the following drawings are only some embodiments of the present utility model. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0020] Figure 1 It is a schematic diagram of the principle of the fuel supply system of the present utility model;

[0021] Figure 2 It is a layout schematic diagram of the fuel supply system of the present utility model.

[0022] Explanation of the reference numerals in the drawings in the specification: engine -1; fuel tank -2; fuel supply pipeline -3; fuel pump -4; one-way valve -5; filter device -6; ventilation pipeline -7; decompression valve -8; air valve -9; oil return pipeline -10. DETAILED DESCRIPTION

[0023] In order to make the above-mentioned purposes, features and advantages of the utility model more obvious and easy to understand, the specific implementation methods of the utility model are described in detail below in conjunction with the drawings of the specification. Obviously, the described embodiments are part of the embodiments of the utility model, but not all of them. Based on the embodiments of the utility model, all other embodiments obtained by ordinary persons in the field without creative work should fall within the scope of protection of the utility model.

[0024] In the following description, many specific details are set forth to facilitate a full understanding of the present invention, but the present invention may also be implemented in other ways different from those described herein, and those skilled in the art may make similar generalizations without violating the connotation of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0025] Secondly, the term "one embodiment" or "embodiment" as used herein refers to a specific feature, structure or characteristic that may be included in at least one implementation of the present invention. The term "in one embodiment" that appears in different places in this specification does not necessarily refer to the same embodiment, nor does it refer to a separate or selective embodiment that is mutually exclusive with other embodiments.

[0026] The utility model is described in detail with reference to the schematic diagram. When describing the embodiments of the utility model, for the sake of convenience, the cross-sectional diagrams showing the device structure will not be partially enlarged according to the general proportion, and the schematic diagrams are only examples, which should not limit the scope of protection of the utility model. In addition, in actual production, the three-dimensional dimensions of length, width and depth should be included.

[0027] At the same time, in the description of the present invention, it should be noted that the directions or positional relationships indicated by the terms "upper, lower, left, right, inside and outside" are based on the directions or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or component referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as limiting the present invention. In addition, the terms "first, second or third" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0028] Unless otherwise clearly specified and defined in the present utility model, the terms "installation, connection, and coupling" shall be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may also be a mechanical connection, an electrical connection, or a direct connection, or may be indirectly connected through an intermediate medium, or may be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances.

[0029] Embodiment 1

[0030] This embodiment provides an oil supply system, which is applied to an aircraft, especially an unmanned helicopter. Existing unmanned helicopters use multiple power sources such as batteries and fuel to drive the rotor to rotate, so that the unmanned aircraft can perform actions such as takeoff, turning, and landing. However, when using a solid battery as the power source, due to the much lower energy density of the battery than that of fuel, limited by the battery, the weight of the mission payload that the unmanned helicopter can carry is relatively light, and the endurance is limited. In addition, when the battery operates in a high-temperature or low-temperature environment, there is also a risk of reduced endurance, and even explosion may occur; when using a hybrid power source of oil and electricity, two sets of systems, including a rotor system and a hybrid power system of oil and electricity, are configured at both the front and rear ends of the helicopter frame. The two transmission systems result in more structural components and high manufacturing costs. When the two engines operate simultaneously, due to the asynchronous startup and possible differences in rotational speeds of the two engines, the aerodynamic lift generated by the rotor assembly will be inconsistent, resulting in an increase in control difficulty; when using a fuel engine as the power source, for a tandem rotor helicopter, in order to avoid the center of gravity shift caused by fuel consumption, the fuel tank is arranged at the center of gravity of the whole machine, and two sets of engine transmission mechanisms are configured at the front and rear of the frame to control the two rotor assemblies. The two engines will still have an asynchronous problem. Therefore, a single fuel engine can be used as the power source for the rotor assembly. However, in existing helicopters using a single fuel engine, only one set of oil supply circuit and components is provided in the oil supply system. When parts such as the fuel pump in the circuit have problems, it is easy to affect the flight safety and reliability of the aircraft. Therefore, this application proposes a new type of oil supply system to avoid affecting the flight of the aircraft when a single part has problems and ensure flight safety and reliability.

[0031] The following refers to Figures 1 to 2According to an embodiment of the present utility model, a novel fuel supply system is proposed. The fuel supply system includes a fuel supply pipeline 3, a fuel pump 4, and a check valve 5. The fuel in the helicopter fuel tank 2 is supplied to the engine 1 through the fuel supply pipeline 3. The fuel supply pipeline 3 can be made of PU polyurethane material. The PU material has good stability, chemical resistance, and mechanical properties, has smaller compression deformation, and has good heat insulation, sound insulation, earthquake resistance, and anti-toxic properties, ensuring the safe transportation of fuel. A plurality of fuel pumps 4 and check valves 5 are provided on the fuel supply pipeline 3 between the fuel tank 2 and the engine 1. In this embodiment, both the fuel pump 4 and the check valve 5 are provided with 2. The 2 fuel pumps 4 are connected in series, and the 2 check valves 5 are connected in series. Refer to Figure 1 As shown, the 2 fuel pumps 4 and the 2 check valves 5 are arranged in two rows. The fuel pump 4 and the check valve 5 are connected through the fuel supply pipeline 3 to form multiple fuel supply circuits. When a single fuel pump 4 or check valve 5 in the circuit is damaged, the fuel can pass through other circuits to ensure the fuel supply to the engine 1, thereby ensuring the safety and reliability of flight.

[0032] It should be noted that in the actual application process, the fuel pump 4 is connected to the ground station. After the engine 1 is started, the ground station can adjust the rotational speed of the fuel pump 4, thereby realizing the control and adjustment of the fuel output flow rate.

[0033] In one embodiment, the fuel supply system further includes a filtering device 6. One end of the filtering device 6 is connected to the fuel tank 2 through the fuel supply pipeline 3, and the other end is connected to the fuel pump 4 and the check valve 5 through the fuel supply pipeline 3. The filtering device 6 is installed on the fuel supply pipeline 3 between the fuel tank 2 and the engine 1 inlet. In this embodiment, the filtering device 6 can use a fuel filter or other filters that can block particulate matter, water, and impurities in the fuel to filter impurities that may exist in the fuel.

[0034] In one embodiment, a plurality of fuel tanks 2 are provided. The plurality of fuel tanks 2 are connected to a single filtering device 6 through the fuel supply pipeline 3 to filter the fuel supply from the plurality of fuel tanks 2 simultaneously. In this embodiment, the plurality of fuel tanks 2 are symmetrically arranged about the center of gravity of the aircraft. The fuel tanks 2 can be provided with 2. The two fuel tanks 2 are symmetric about the center of gravity of the aircraft, which can avoid the problem of center of gravity shift caused by fuel consumption and ensure the flight stability. Further, it should be noted that the engine 1 is single. The plurality of fuel tanks 2 supply fuel to the same engine 1. The engine 1 is arranged at the center of gravity of the aircraft. Since the weight of the helicopter engine 1 is relatively large, placing it at the center of gravity position of the whole aircraft can avoid the center of gravity shift during flight and ensure the flight stability of the helicopter.

[0035] In one embodiment, the fuel supply system further includes a vent pipe 7, which can also be made of PU polyurethane material. An exhaust port is provided on the engine 1. The vent pipe 7 connects the exhaust port and the fuel tank 2, introducing the gas generated after the combustion of the engine 1 into the fuel tank 2 to ensure the stability of the air pressure in the fuel supply system and avoid the formation of a pressure difference. Further, it should be noted that multiple fuel tanks 2 are interconnected through the vent pipe 7 to ensure the same air pressure among the multiple fuel tanks 2. The fuel supply system further includes a pressure relief valve 8 and a gas valve 9, which are arranged on the vent pipe 7. The gas valve 9 is used to control the discharge of the gas in the fuel tank, and the pressure relief valve 8 reduces the pressure of the gas in the pipeline. Further, the vent pipe 7 has a heat dissipation function and can also dissipate heat from the combustion gas to further achieve a pressure reduction effect.

[0036] In one embodiment, the engine (1), the gas valve (9), the pressure relief valve (8) and the fuel tank (2) are sequentially connected to the vent pipe (7). The gas valve (9) is connected to the outside air. After the gas discharged from the engine 1 is cooled by the vent pipe 3, part of the gas is discharged to the air by the gas valve 9, and part of the gas is decompressed by the pressure relief valve 8 and then discharged into the fuel tank 2 to make the pressure inside and outside the fuel tank 2 consistent, avoiding faults such as deformation of the fuel tank structure caused by the pressure difference.

[0037] In one embodiment, a return oil pipe 10 is further included, which can also be made of PU polyurethane material. A return oil port is provided on the engine 1. The return oil pipe 10 connects the return oil port and the fuel tank 2. The fuel enters the engine 1 for combustion, and the excess fuel that does not participate in the combustion flows back to the fuel tank through the return oil pipe.

[0038] It should be noted that the fuel supply system in this embodiment includes an engine 1, two fuel tanks 2, two fuel pumps 4 and two one-way valves 5. The engine 1, fuel tanks 2, fuel pumps 4 and one-way valves 5 are all connected through a fuel supply pipeline 3. Among them, the fuel supply pipelines 3 connecting the two fuel tanks 2 converge, and a filtering device 6 is arranged on the converged fuel supply pipeline 3. The fuel passing through the filtering device 6 flows through the fuel supply pipeline 3 to the fuel pumps 4 and one-way valves 5. After passing through the fuel pumps 4 and one-way valves 5, the fuel converges and enters the engine 1 from the fuel inlet. The engine 1 starts to burn the fuel. Among them, the unburned fuel returns to the fuel tank through the oil return port of the engine 1. In addition, a large amount of gas is generated during fuel combustion. An exhaust port is provided on the engine 1, and the exhaust port transports the gas to a gas valve 9 through an air pipe 7. The air pipe 7 dissipates heat from the burned gas. The gas valve 9 controls part of the gas to be discharged to the air, and part of the gas is transported to a pressure relief valve 8. The pressure relief valve 8 decompresses the gas, and the decompressed gas is then transported to the two fuel tanks 2 to maintain the pressure balance inside and outside the fuel tanks 2. In this embodiment, the fuel supply pipeline 3 is connected to multiple fuel tanks 2, fuel pumps 4 and one-way valves 5. Therefore, multiple three-way pipe joints can be arranged on the fuel supply pipeline 3 to facilitate the connection of the fuel supply pipeline 3. The fuel supply system provided in this embodiment, by setting multiple fuel pumps 4 and one-way valves 5 and connecting them into multiple fuel supply channels through the fuel supply pipeline 3, so when one fuel pump 4 or one-way valve 5 has a problem, it will still not affect the safe flight of the aircraft, and has reliability.

[0039] Embodiment 2

[0040] Different from the above embodiment, this embodiment provides a power drive system. This power drive system is provided with the above fuel supply system, and the fuel supply system connects the engine 1 and the fuel tank 2 to ensure the stability and safety of the aircraft flight.

[0041] Embodiment 3

[0042] Different from the above embodiment, this embodiment provides an aircraft. This aircraft is provided with the above power drive system or fuel supply system. The aircraft includes at least an engine 1 and a fuel tank 2. The aircraft also includes a frame. The transmitter 1, fuel tank 2 and fuel supply system are all installed on the frame of the aircraft. The fuel supply system connects the fuel tank 2 and the engine 1 to ensure the stability and safety of the aircraft flight.

[0043] Note that the above is only the preferred embodiment of the present utility model and the applied technical principles. Those skilled in the art will understand that the present utility model is not limited to the specific embodiments described herein, and various obvious changes, re-adjustments and substitutions can be made by those skilled in the art without departing from the protection scope of the present utility model. Therefore, although the present utility model has been described in detail through the above embodiments, the present utility model is not limited to the above embodiments. Without departing from the concept of the present utility model, more other equivalent embodiments can be included, and the scope of the present utility model is determined by the scope of the appended claims.

Claims

1. A fuel supply system, connected to an engine (1) and a fuel tank (2), characterized in that: The fuel supply system comprises a fuel supply pipeline (3), a fuel pump (4) and a one-way valve (5), wherein the fuel pump (4) and the one-way valve (5) are arranged on the fuel supply pipeline (3) between the engine (1) and the fuel tank (2); A plurality of the fuel pumps (4) and the one-way valves (5) are provided, the plurality of the fuel pumps (4) and the plurality of the one-way valves (5) are respectively provided in series, the fuel pumps (4) and the one-way valves (5) are provided in parallel, and the plurality of the fuel pumps (4) and the one-way valves (5) are connected via the fuel supply pipeline (3).

2. The oil supply system according to claim 1, characterized in that: It also includes a filter device (6), one end of which is connected to the fuel tank (2) via the fuel supply pipeline (3), and the other end of which is connected to the fuel pump (4) and the one-way valve (5) via the fuel supply pipeline (3).

3. The oil supply system according to claim 2, characterized in that: A plurality of the oil tanks (2) are provided, and the plurality of the oil tanks (2) are connected to one filtering device (6) via the oil supply pipeline (3).

4. The oil supply system according to claim 1, characterized in that: It also comprises a ventilation pipeline (7), an exhaust port is arranged on the engine (1), and the ventilation pipeline (7) is connected with the exhaust port and the oil tank (2).

5. The oil supply system according to claim 4, characterized in that: The multiple oil tanks (2) are interconnected via the ventilation pipeline (7).

6. The oil supply system according to claim 4, characterized in that: It also comprises a decompression valve (8) and an air valve (9), wherein the decompression valve (8) and the air valve (9) are arranged on the ventilation pipeline (7).

7. The oil supply system according to claim 6, characterized in that: The engine (1), the air valve (9), the decompression valve (8) and the oil tank (2) are connected to the ventilation pipeline (7) in sequence, and the air valve (9) is connected to the outside air.

8. The oil supply system according to claim 1, characterized in that: It also comprises an oil return pipeline (10), an oil return port is arranged on the engine (1), and two ends of the oil return pipeline (10) are respectively connected to the oil return port and any one of the oil tanks (2).

9. A power drive system, characterized in that: A fuel supply system comprising the fuel supply system according to any one of claims 1 to 8.

10. An aircraft, characterized in that: It comprises the power drive system of claim 9 or the oil supply system of any one of claims 1 to 8.

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