Oil collecting device for large maneuvering overload of unmanned aerial vehicle

Abstract

The utility model belongs to the technical field of unmanned aerial vehicles, and particularly relates to an oil collecting device for large maneuvering overload of an unmanned aerial vehicle, which comprises an oil supply tank, an overload oil tank and a jet pump, the oil supply tank is connected with the overload oil tank through a first pipeline, a first one-way valve is arranged on the first pipeline, and a second one-way valve is arranged on the jet pump. The overload oil tank is connected with an engine through a second pipeline, the jet pump comprises a high-pressure driving fluid inlet, a jetted fluid suction inlet and a fluid outlet, the high-pressure driving fluid inlet is communicated with the second pipeline through a pipeline, and the jetted fluid suction inlet is communicated with the fluid outlet through a pipeline. The injected fluid suction inlet is communicated with the oil supply tank through a pipeline, the fluid outlet is connected with the overload oil tank through a pipeline, and the oil supply tank is provided with an air entraining vent which is connected with an engine through a pipeline. The problem of fuel oil supply of the unmanned aerial vehicle under the working condition of large maneuvering overload is effectively solved.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) technology, and in particular relates to an oil collection device for high-maneuver overload of unmanned aerial vehicles. Background Technology

[0002] During flight, unmanned aerial vehicles (UAVs) often perform a series of large maneuvers (high-angle flight, high-angle dive, high-angle roll) due to the nature of their missions. However, current fuel systems collect fuel from a single tank. When this tank is not fully loaded or when fuel is low in the later stages of flight, it often restricts the UAV's maneuverability to ensure safe operation. This can cause the UAV to lose the opportunity to escape by utilizing its flight attitude when attacked. Utility Model Content

[0003] In view of the shortcomings of the prior art, the purpose of this utility model is to provide an oil collection device for high-maneuver overload of unmanned aerial vehicles.

[0004] To achieve the above objectives, the technical solution adopted is:

[0005] An oil collection device for high-maneuver overload of unmanned aerial vehicles includes a fuel supply tank with a refueling port, an overload tank, and an ejector pump. The fuel supply tank is connected to the overload tank via a first pipeline, which is equipped with a first one-way valve to ensure that the medium can only flow from the fuel supply tank to the overload tank. The overload tank is connected to an engine via a second pipeline. The ejector pump includes a high-pressure driving fluid inlet, an ejected fluid suction inlet, and a fluid outlet. The high-pressure driving fluid inlet is connected to the second pipeline via a pipeline, the ejected fluid suction inlet is connected to the fuel supply tank via a pipeline, and the fluid outlet is connected to the overload tank via a pipeline. The fuel supply tank is equipped with a bleed air vent, which is connected to the engine via a pipeline.

[0006] The beneficial effects of adopting the above technical solution are as follows: the ejector pump (driven by high-pressure fuel from the engine fuel supply line) continuously draws fuel from the fuel supply tank to the overload tank; the first one-way valve allows fuel to flow naturally from the fuel supply tank to the overload tank (driven by the liquid level difference), supplementing the fuel supply through gravity difference, but preventing reverse flow to prevent fuel from flowing back from the overload tank to the fuel supply tank when overloaded. At the same time, the ejector pump can force fuel supply to achieve dual-margin fuel supply; the bleed air vent is used to balance the air pressure in the fuel supply tank, avoiding vacuum or pressure buildup during fuel delivery, and at the same time, the engine bleed air is used to improve the stability of the fuel system.

[0007] Based on the above technical solution, the present invention can be further improved as follows:

[0008] Preferably, the overload tank is located inside the oil supply tank.

[0009] The advantages of adopting the above-mentioned preferred technical solution are that the overload fuel tank can be flexibly installed inside or outside the fuel supply tank to adapt to the spatial layout requirements of different aircraft.

[0010] Preferably, a third pipeline is connected between the upper part of the oil supply tank and the overload tank, and a second check valve is provided on the third pipeline so that the medium can only flow from the overload tank to the oversupply tank.

[0011] The beneficial effect of adopting the above-mentioned preferred technical solution is that it allows the overflow of oil or gas from the overloaded oil tank to return to the oil supply tank, thus avoiding damage to the overloaded oil tank due to full oil or gas accumulation.

[0012] Preferably, the overloaded oil tank is equipped with an oil extractor, which is connected to the second pipeline.

[0013] Preferably, the oil extractor includes a hose, one end of which is connected to the second pipeline, the other end of which is an oil suction port, and a weight is connected to the other end of the hose.

[0014] The beneficial effects of adopting the above-mentioned preferred technical solution are as follows: the hose and the counterweight ensure that the fuel suction port always moves with the fuel level, ensuring that the fuel suction port is submerged in the fuel under any overload condition. Even if the fuel "floats" due to inertia, the counterweight drives the hose to track the fuel position and avoids sucking up empty fuel.

[0015] Preferably, the first pipeline is connected to the bottom of the oil supply tank and the bottom of the overload tank, respectively.

[0016] The advantages of adopting the above-mentioned preferred technical solution are: maximizing the efficiency of fuel supply by gravity difference and reducing fuel residue.

[0017] Preferably, the vent is connected to the upper part of the fuel tank.

[0018] The advantages of adopting the above-mentioned preferred technical solution are: priority is given to venting the gas at the top of the fuel tank, ensuring more sensitive gas pressure balance during fuel delivery.

[0019] Preferably, the filler port is located at the top of the fuel tank.

[0020] The advantages of adopting the above-mentioned preferred technical solution are: it facilitates refueling and reduces the interference of the structure on the internal flow of fuel tank.

[0021] Preferably, the oil delivery rate of the oil inlet is less than the oil supply rate from the oil tank to the overload tank.

[0022] The beneficial effects of adopting the above-mentioned preferred technical solution are: namely, the oil flow rate is greater than the engine consumption, ensuring that the overloaded fuel tank is always full of oil, and the redundant fuel flows back to the fuel supply tank through the second one-way valve to form a cycle.

[0023] Compared with the prior art, the beneficial effects of this utility model are as follows:

[0024] This invention effectively solves the fuel supply problem for unmanned aerial vehicles (UAVs) under high-G maneuvering conditions by employing a forced fuel supply system via an ejector pump, dual one-way valve control, and a dynamic fuel extractor. The ejector pump and gravity fuel supply form a dual-margin fuel supply system, ensuring the fuel tank remains full under overload conditions; the flexible fuel extractor keeps the fuel inlet constantly submerged in fuel; and the one-way valve assembly prevents fuel backflow and maintains pressure balance in the fuel tank. This invention offers advantages such as reliable fuel supply, strong adaptability, and high safety, significantly improving the stability of the fuel system under extreme maneuvering conditions and making it suitable for various high-maneuverability aircraft.

[0025] a) Fuel is continuously supplied to the negative overload tank via the ejector pump; after the fuel pump starts, the system extracts ejector flow from the fuel supply main as the power source for the ejector pump; the ejector pump works continuously, constantly inputting fuel from the fuel supply tank into the negative overload protection tank; the fuel supply flow of the ejector pump is greater than the engine consumption, which can ensure that the negative overload tank is kept full; the fuel exceeding the engine consumption flows back to the fuel supply tank of the wing or fuselage through the negative overload check valve set on the top of the negative overload protection tank;

[0026] b) The anti-overload check valve installed on the top of the anti-overload fuel tank serves to ventilate and prevent fuel overflow during normal flight, preventing air from occupying the space inside and fuel from overflowing and damaging the fuel tank; when an overload occurs during flight, the second check valve is in the closed state, and the fuel remains in the anti-overload fuel tank and will not flow out. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the structure of an oil collection device for high-maneuver overload of unmanned aerial vehicles according to this utility model.

[0028] The attached diagram is labeled as follows: 1. Overload oil tank; 2. First check valve; 3. Oil supply tank; 4. Bleed air vent; 5. Ejector pump; 51. High-pressure drive fluid inlet; 52. Inlet for ejected fluid; 53. Fluid outlet; 6. Second check valve; 8. Oil extractor; 9. First pipeline; 10. Second pipeline; 11. Engine; 12. Third pipeline. Detailed Implementation

[0029] The present invention will be described below with reference to examples. The examples are only used to explain the present invention and are not intended to limit the scope of the present invention.

[0030] In the description of this utility model, it should be noted that the terms "vertical", "up", "down", "horizontal", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0031] In the description of this utility model, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0032] refer to Figure 1 An oil collection device for high-maneuver overload of unmanned aerial vehicles includes an oil supply tank 3 with an oil filling port, an overload tank 1, and an ejector pump 5. The oil supply tank 3 is connected to the overload tank 1 via a first pipeline 9, which is equipped with a first one-way valve 2, allowing the medium to flow only from the oil supply tank 3 to the overload tank 1. The overload tank 1 is connected to an engine 11 via a second pipeline 10. The ejector pump 5 includes a high-pressure driving fluid inlet 51, an ejected fluid suction inlet 52, and a fluid outlet 53. The high-pressure driving fluid inlet 51 is connected to the second pipeline 10 via a pipeline, the ejected fluid suction inlet 52 is connected to the oil supply tank 3 via a pipeline, and the fluid outlet 53 is connected to the overload tank 1 via a pipeline. The oil supply tank 3 is equipped with a bleed air vent 4, which is connected to the engine 11 via a pipeline.

[0033] In a preferred embodiment, the overload tank 1 is located inside the oil supply tank 3.

[0034] In this embodiment, a third pipeline 12 is connected between the upper part of the oil supply tank 3 and the overload tank 1. The third pipeline 12 is equipped with a second one-way valve 6, so that the medium can only flow from the overload tank to the oversupply tank 3.

[0035] In this embodiment, the overloaded oil tank 1 is equipped with an oil extractor 8, which is connected to the second pipeline 10.

[0036] In a preferred embodiment, the oil extractor 8 includes a hose, one end of which is connected to the second pipeline 10, and the other end of which is an oil suction port, and a counterweight is provided at the oil suction port at the other end of the hose.

[0037] In a preferred embodiment, the first pipeline 9 is connected to the bottom of the oil supply tank 3 and the bottom of the overload tank 1, respectively.

[0038] In a preferred embodiment, the air intake port 4 is connected to the upper part of the oil supply tank 3.

[0039] In a preferred embodiment, the filler neck is located at the top of the fuel tank.

[0040] In this embodiment, the oil delivery rate of the oil inlet is less than the oil supply rate from the oil tank to the overload tank 1.

[0041] Working process of unmanned aerial vehicle oil collection device

[0042] Initial preparation stage

[0043] When the aircraft is preparing for takeoff on the ground, fuel is added to the fuel supply tank 3 through the refueling port located on top of the fuel supply tank 3 until the tank reaches the predetermined fuel level. At this time, the fuel in the fuel supply tank 3 is in a static state, and the bleed air vent 4 is connected to the engine 11 to maintain the pressure balance between the inside and outside of the fuel tank.

[0044] The ejector pump 5 is in a standby state, with its high-pressure drive fluid inlet 51, ejected fluid suction inlet 52, and fluid outlet 53 connected to the corresponding pipelines, but it has not yet started working. The weight at the end of the hose of the oil extractor 8 in the overloaded fuel tank 1 hangs down naturally, and the oil suction port is immersed in fuel, waiting for the fuel supply command.

[0045] Normal flight phase

[0046] When the aircraft begins normal flight, engine 11 starts, and the fuel pump also begins to operate. The fuel pump draws fuel from the bottom of the fuel supply tank 3 through the first pipeline 9, and flows to the overload tank 1 via the first one-way valve 2. The first one-way valve 2 ensures that the fuel can only flow in one direction, preventing fuel backflow.

[0047] Simultaneously, the ejector pump 5 also starts, its high-pressure drive fluid inlet 51 drawing ejector fluid from the engine 11 fuel supply main on the second pipeline 10 as a power source. The ejected fluid suction inlet 52 draws fuel from the fuel supply tank 3 and delivers it to the overload tank 1 through the fluid outlet 53. Because the fuel delivery flow rate of the ejector pump 5 is greater than the consumption of the engine 11, the fuel level in the overload tank 1 gradually rises.

[0048] When the fuel level in the overloaded fuel tank 1 reaches a certain height, the fuel flows back to the fuel supply tank 3 through the second one-way valve 6 located at the top of the overloaded fuel tank 1, preventing the fuel tank from overflowing and damaging the tank. At the same time, it also serves to ventilate and maintain the pressure balance in the overloaded fuel tank 1.

[0049] Fuel extractor 8 in overloaded fuel tank 1 delivers fuel to engine 11 through second line 10 under the suction action of fuel pump. The counterweight at the fuel suction port of the hose end of fuel extractor 8 always keeps the fuel suction port submerged in fuel, ensuring that there is always fuel available for extraction even if the fuel level fluctuates during flight, thus ensuring a stable fuel supply to engine 11.

[0050] High-speed overload phase

[0051] When an aircraft performs high-G maneuvers, such as rapid climbs, dives, or sharp turns, the fuel level in the fuel tank will fluctuate violently.

[0052] In this situation, the ejector pump 5 continues to operate, continuously supplying fuel from the fuel supply tank 3 into the overload tank 1, ensuring sufficient fuel in the overload tank 1. Even if fuel level fluctuations cause the fuel level in the fuel supply tank 3 to be lower than the fuel level in the overload tank 1, the one-way valve at the bottom of the overload tank 1 will prevent fuel from flowing out of the overload tank 1, ensuring that fuel is always retained in the overload tank 1, achieving a dual-margin design for fuel supply.

[0053] Meanwhile, under the action of the counterweight, the hose of the fuel extractor 8 moves with the sloshing of the fuel level, ensuring that its fuel inlet is always submerged in the fuel, thus guaranteeing that the engine 11 can continuously and stably obtain fuel and avoiding fuel supply interruption caused by the sloshing of the fuel level.

[0054] If a negative overload occurs during flight, the second one-way valve 6 on top of the overload fuel tank 1 will close to prevent fuel from flowing out of the overload fuel tank 1, ensuring that the fuel remains in the tank, avoiding fuel leakage, and ensuring flight safety.

[0055] End of flight phase

[0056] As the aircraft completes its mission and prepares to land, engine 11 gradually reduces its power, and the fuel pump speed also decreases accordingly. At this time, the fuel level in fuel tank 3 gradually drops, and ejector pump 5 continues to operate, delivering the remaining fuel to overload tank 1 to ensure that engine 11 can still receive a stable fuel supply during landing.

[0057] After the aircraft lands, the fuel pump and ejector pump 5 stop working, and the fuel levels in the fuel supply tank 3 and the overload tank 1 gradually stabilize. At this time, the remaining fuel level in the fuel supply tank 3 can be checked through the refueling port, and refueling can be carried out as needed to prepare for the next flight.

[0058] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A fuel collection device for high-maneuver overload of unmanned aerial vehicles, comprising a fuel supply tank, wherein the fuel supply tank is provided with a refueling port, characterized in that, It also includes an overload tank and an ejector pump. The supply tank is connected to the overload tank via a first pipeline. The first pipeline is equipped with a first check valve, which ensures that the medium can only flow from the supply tank to the overload tank. The overload tank is connected to the engine via a second pipeline. The ejector pump includes a high-pressure driving fluid inlet, an ejected fluid suction inlet, and a fluid outlet. The high-pressure driving fluid inlet is connected to the second pipeline via a pipeline. The ejected fluid suction inlet is connected to the supply tank via a pipeline. The fluid outlet is connected to the overload tank via a pipeline. The supply tank is equipped with a bleed air vent, which is connected to the engine via a pipeline.

2. The oil collection device for high-maneuver overload of unmanned aerial vehicles according to claim 1, characterized in that, The overload tank is located inside the fuel supply tank.

3. The oil collection device for high-maneuver overload of unmanned aerial vehicles according to claim 1 or 2, characterized in that, A third pipeline is connected between the upper part of the oil supply tank and the overload tank. A second check valve is provided on the third pipeline, so that the medium can only flow from the overload tank to the oversupply tank.

4. The oil collection device for high-maneuver overload of unmanned aerial vehicles according to claim 3, characterized in that, The overloaded oil tank is equipped with an oil extractor, which is connected to the second pipeline.

5. The oil collection device for high-maneuver overload of unmanned aerial vehicles according to claim 4, characterized in that, The oil extractor includes a hose, one end of which is connected to the second pipeline, and the other end of which is connected to a weight.

6. The oil collection device for high-maneuver overload of unmanned aerial vehicles according to claim 1, characterized in that, The first pipeline is connected to the bottom of the oil supply tank and the bottom of the overload tank, respectively.

7. The oil collection device for high-maneuver overload of unmanned aerial vehicles according to claim 1, characterized in that, The vent is connected to the upper part of the fuel tank.

8. The oil collection device for high-maneuver overload of unmanned aerial vehicles according to claim 1, characterized in that, The refueling port is located at the top of the fuel tank.

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