Flight test platform oil system

Abstract

A flight test platform oil circuit system that can effectively improve reliability as a whole has the characteristics of anti-bubble oil supply circuit and high efficiency and fuel saving in the refueling circuit. The flight test platform oil circuit system includes a main oil tank formed with an overflow port and a plurality of anti-bubble oil tanks connected in parallel with the main oil tank. The main oil tank is formed with a plurality of oil delivery ports for connecting to the plurality of anti-bubble oil tanks respectively, and each anti-bubble oil tank has three connecting ports for connecting to the corrosion-resistant pipes of the main oil tank, the fuel use end and the fuel supply end, and a corrosion-resistant external joint is installed on it. When supplying oil to the fuel use end, the fuel is pumped from the main oil tank to each anti-bubble oil tank, and then enters the fuel use end from each anti-bubble oil tank. When refueling from the fuel supply end, the fuel is added to the anti-bubble oil tank, and enters the main oil tank after the anti-bubble oil tank is filled. After the main oil tank is filled, the excess fuel returns to the fuel supply end from the overflow port of the main oil tank through the oil circuit, and the refueling is stopped when the feedback signal output by the overflow valve is received.

Description

Technical Field

[0001] The present invention relates to the field of unmanned aerial vehicle oil circuit system design in unmanned aerial vehicle system design, and more specifically, the present invention relates to an oil circuit system of a flight test platform (such as a unmanned aerial vehicle). Background Art

[0002] Aircraft flutter model flight test is a hot topic in the study of aircraft flutter characteristics and is becoming increasingly important in the pre-development process of aircraft. Model flight test is carried out by free flight of unmanned aerial vehicles. The design technology of unmanned aerial vehicle system determines the quality of flight test.

[0003] The oil circuit system is an important part of the UAV system, which realizes the function of continuous and reliable oil supply to the engine. Anti-bubble, sealing, and corrosion resistance are important performance indicators of UAV oil circuit design. Anti-bubble is to prevent the engine from abnormal or stopping due to air bubbles and uneven oil absorption. Corrosion resistance is to prevent the oil circuit system from corroding the oil pipes and joints due to fuel leakage. Sealing is to prevent fuel leakage due to changes in the pressure difference between the inside and outside of the fuel tank and environmental vibration during the flight of the UAV.

[0004] Traditional UAV oil circuit systems focus on improving single performance indicators such as anti-bubble, sealing, or corrosion resistance, but the overall reliability of the oil circuit system has not been effectively improved.

[0005] Therefore, how to design a product that takes into account multiple performance indicators such as anti-bubble, sealing and corrosion resistance, effectively improves the reliability of the oil circuit system as a whole and has the characteristics of anti-bubble in the oil supply circuit and efficient and fuel-saving in the refueling circuit, has become a technical problem that needs to be solved urgently. Summary of the invention

[0006] The present invention is made to solve the above-mentioned prior art, and its purpose is to provide a flight test platform oil circuit system that can effectively improve the reliability as a whole, and has the characteristics of anti-bubble, sealing and corrosion resistance, and has the characteristics of anti-bubble in the oil supply circuit and high efficiency and fuel saving in the refueling circuit.

[0007] In order to solve the above-mentioned purpose, the present invention provides a flight test platform oil circuit system, characterized in that the flight test platform oil circuit system includes a main oil tank formed with an overflow port and a plurality of anti-bubble oil tanks connected in parallel with the main oil tank, the main oil tank is formed with a plurality of oil delivery ports for respectively connecting with the plurality of anti-bubble oil tanks, each of the anti-bubble oil tanks has three connecting ports for connecting with the corrosion-resistant pipelines of the main oil tank, the fuel use end and the fuel supply end, and corrosion-resistant external joints are installed on the three connecting ports. When the flight test platform oil circuit system supplies oil to the fuel use end, the fuel is pumped from the main oil tank to each anti-bubble oil tank, and then enters the fuel use end from each anti-bubble oil tank. When the flight test platform oil circuit system refuels from the fuel supply end, the fuel is added to the anti-bubble oil tank, and enters the main oil tank after the anti-bubble oil tank is full. After the main oil tank is full, the excess fuel returns to the fuel supply end from the overflow port of the main oil tank through the oil circuit, and the refueling is stopped when the feedback signal output by the overflow valve is received.

[0008] According to the structure as described above, compared with the existing UAV oil circuit system, the flight test platform oil circuit system of the present invention takes into account multiple technical indicators such as bubble prevention, sealing, corrosion resistance, etc. and has been verified by experiments, and has higher reliability, and has the characteristics of bubble prevention in the oil supply circuit and efficient and fuel-saving in the refueling circuit, and has good practical effects on the flight test of UAVs.

[0009] When supplying fuel, the corrosion-resistant internal joints of the main fuel tank and the anti-bubble fuel tank 120 are always below the fuel level due to gravity, thereby avoiding the suction of bubbles and achieving anti-bubble. On the other hand, when refueling, it can be controlled by a simple control method, and the oil circuit refueling efficiency is high.

[0010] At the same time, the oil pipes, external joints and internal joints in the oil system of the flight test platform are made of corrosion-resistant materials and have good sealing properties.

[0011] Preferably, when the flight test platform oil circuit system supplies oil to the fuel using end, the overflow port is not sealed, and when the flight test platform oil circuit system is refueled from the fuel supply end, the fuel entering the main fuel tank reaches a specified liquid level, and excess fuel flows out from the overflow port of the main fuel tank and returns to the fuel supply end through the fuel return pipe.

[0012] Particularly, the anti-bubble oil tank is provided with an oil tank cover, and three connecting ports are provided on the oil tank cover.

[0013] Among them, the three connecting ports are the refueling port connected to the fuel output pipe on the fuel supply end, the anti-bubble tank oil delivery port connected to the anti-bubble tank oil delivery pipe on the fuel use end, and the main tank oil delivery port connected to the main tank oil delivery pipe on the main tank. When the flight test platform oil circuit system supplies fuel to the fuel use end, the refueling port is in a sealed state.

[0014] In the present invention, it is particularly preferred that after the oil circuit system of the flight test platform is built and passes the pressurization sealing test, the vibration sealing test and the corrosion resistance test, it is arranged on the main load-bearing structure of the fuselage along the fuselage axis of the flight test platform, and the oil circuit system of the flight test platform is symmetrical about the fuselage axis.

[0015] According to the above-described structure, since the design of the flight test platform oil circuit system can be verified in advance through various performance tests (pressurization seal test, vibration seal test and corrosion resistance test) before being installed on the flight test platform (such as a drone), reliability can be effectively improved.

[0016] In addition, the fuel consumption end is an engine, and the engine is arranged on a wing of the flight test platform that is symmetrical about the fuselage axis. Wherein, the main fuel tank is arranged near the center of gravity of the flight test platform.

[0017] According to the structure as described above, since the oil circuit system of the flight test platform can adopt a structural form in which the main fuel tank and multiple anti-bubble fuel tanks are connected in parallel, and the main fuel tank is arranged near the center of gravity, it can be ensured that the center of gravity position is not affected by the amount of fuel in the main fuel tank.

[0018] Preferably, a plurality of anti-bubble oil tanks are arranged on the tail side of the main oil tank in a manner facing each other relative to the fuselage axis.

[0019] On the other hand, the fuel supply end is a fuel container, and the fuel in the fuel container is refueled into the oil circuit system of the flight test platform through a gas station, and refueling from the fuel container is stopped upon receiving a feedback signal output by an overflow valve arranged in the gas station. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 1 is a schematic structural diagram of an oil system of a flight test platform according to an embodiment of the present invention.

[0021] Figure 2 Schematic diagram of an oil tank (anti-bubble oil tank) in an oil system of a flight test platform according to an embodiment of the present invention.

[0022] Figure 3 Schematic diagram of an oil supply circuit of an oil system of a flight test platform according to an embodiment of the present invention.

[0023] Figure 4 Schematic diagram of a refueling circuit of an oil system of a flight test platform according to an embodiment of the present invention.

[0024] (Explanation of symbols)

[0025] 10 flight test platform;

[0026] 11, 12 engines;

[0027] 100 Flight test platform oil system;

[0028] 110 Main fuel tank;

[0029] 111 Overflow;

[0030] 112 Spare fuel filler cap;

[0031] 113 oil outlet;

[0032] 120 Anti-bubble fuel tank;

[0033] 121 Fuel tank cap;

[0034] 122 Fuel filler;

[0035] 124 Main fuel tank oil inlet;

[0036] 123 Anti-bubble oil tank oil inlet;

[0037] 200 fuel containers;

[0038] 300 gas stations;

[0039] 310 Oil pump;

[0040] 320 flow sensor;

[0041] 330 Fuel detector;

[0042] 340 Relief valve;

[0043] P1 main fuel tank oil delivery pipe;

[0044] P2a, P2b anti-bubble tank oil delivery pipe;

[0045] P3 fuel output pipe;

[0046] P4 fuel return pipe;

[0047] T1 corrosion resistant external joint;

[0048] T2 corrosion resistant nipple;

[0049] M: main load-bearing structure of the fuselage;

[0050] CL Fuselage axis. DETAILED DESCRIPTION

[0051] Below, refer to Figures 1 to 4 A flight test platform oil system 100 according to an embodiment of the present invention will be described.

[0052] (Schematic structure)

[0053] First, combine Figure 1 and Figure 2 , a schematic structure of a flight test platform oil circuit system 100 according to an embodiment of the present invention is described.

[0054] like Figure 1 As shown, a flight test platform oil system 100 according to an embodiment of the present invention includes a main oil tank 110 and a plurality of (in this embodiment, for example, two) anti-bubble oil tanks 120 .

[0055] The main oil tank 110 is a normal pressure oil tank, and the anti-bubble oil tank 120 is a sealed oil tank. The main oil tank 110 and the anti-bubble oil tank 120 are hard oil tanks made of HDPE plastic with an operating temperature of -20 to 110°C.

[0056] The main oil tank 110 has two covers formed on its upper end, namely, an overflow port 111 and a spare oil filling port cover 112. A plurality of oil delivery ports 113 (equal to the number of the anti-bubble oil tanks 120, in this embodiment, for example, two) for connecting to the plurality of anti-bubble oil tanks 120 are formed on the side of the main oil tank 110.

[0057] In addition, if Figure 2 As shown, each anti-bubble oil tank 120 is installed with a tank cap 121, and the tank cap 121 has three connecting ports, namely a refueling port 122 connected to the fuel output pipe P3 on the fuel container 200 (or the gas station 300) as the fuel supply end, an anti-bubble oil tank oil delivery port 123 connected to the anti-bubble oil tank oil delivery pipes P2a, P2b on the engines 11, 12 as the fuel use end, and a main oil tank oil delivery port 124 connected to the main oil tank oil delivery pipe P1 on the main oil tank 110. The three connecting ports are all installed with corrosion-resistant external joints T1 through sealing gaskets (not shown).

[0058] The oil pipe is made of polyamide with an inner diameter of 5 mm, a working temperature of -30 to 80°C, and a working pressure of -0.95 to 15 bar. The material of the corrosion-resistant external joint T1 is nickel-plated brass, and the corrosion resistance level is 3-strong corrosion. In addition, the sealing gasket is made of fluorine rubber.

[0059] (Oil supply circuit)

[0060] Next, combine Figure 3 , an oil supply circuit of the flight test platform oil system 100 according to an embodiment of the present invention is described.

[0061] like Figure 3 As shown, the fuel in the main tank 110 (at the main tank oil delivery port 124) enters into the multiple anti-bubble tanks 120 respectively via the main tank oil delivery pipe P1, and then (at the anti-bubble tank oil delivery port 123) enters into the fuel use end (engines 11, 12) respectively via the anti-bubble tank oil delivery pipes P2a, P2b.

[0062] Figure 1 The overflow port 111 of the main fuel tank 110 shown is not sealed, and is used to keep the main fuel tank 110 consistent with the flight environment pressure, while the refueling ports 122 of the plurality of anti-bubble fuel tanks 120 are in a sealed state.

[0063] (Refueling circuit)

[0064] Next, combine Figure 4 , a refueling circuit of a flight test platform oil system 100 according to an embodiment of the present invention is described.

[0065] like Figure 4 As shown, the fuel in the fuel container 200 serving as the fuel supply end enters into the plurality of bubble-proof oil tanks 120 via the oil pump 310, the flow sensor 320, and the fuel detector 330 in the oil station 300 via the fuel output pipe P3 (at the refueling port 122). After the bubble-proof oil tank 120 is filled, the fuel enters into the main oil tank 110 via the main oil tank oil delivery pipe P1 (at the main oil tank oil delivery port 124) until the fuel reaches the specified liquid level in the main oil tank 110.

[0066] Excess fuel will flow out from the overflow port 111 of the main fuel tank 110, and flow back to the gas station 300 through the fuel return pipe P4, and then return to the fuel supply end (fuel container 200). The overflow valve 340 arranged in the gas station 300 outputs a feedback signal to stop refueling from the fuel supply end (fuel container 200).

[0067] In other words, when the flight test platform oil circuit system 100 supplies oil to the fuel use end (engines 11, 12), the fuel is pumped from the main oil tank 110 to the anti-bubble oil tank 120, and then enters the fuel use end (engines 11, 12) from the anti-bubble oil tank 120. Figure 3 As shown, the oil extraction pipes (i.e., the components for extracting oil from the main oil tank 110 and the anti-bubble oil tank 120) are respectively connected to the corrosion-resistant inner joint T2 to ensure that the oil pipes are always below the fuel liquid level and prevent bubbles from entering the oil pipes.

[0068] On the other hand, when the flight test platform oil circuit system 100 is refueled from the fuel supply end, the fuel (from the fuel supply end) is added through the refueling port 122 of the anti-bubble tank 120. After the anti-bubble tank 120 is filled, the fuel will enter the main tank 110 until the fuel reaches a specified liquid level in the main tank 110. The excess fuel flows out from the overflow port 111 of the main tank 110, flows through the fuel return pipe P4 through the oil station 300 and then returns to the fuel container 200. The overflow valve 340 outputs a feedback signal to stop refueling from the fuel container 200. Figure 3 and Figure 4 As shown, the main oil tank 110, the anti-bubble oil tank 120 and the oil extraction pipes in the fuel container 200 are respectively connected to the corrosion-resistant inner joint T2.

[0069] The material of the corrosion-resistant inner joint T2 is high alloy steel, and the corrosion resistance grade is 4-extremely strong corrosion.

[0070] Thus, the flight test platform oil circuit system 100 of one embodiment of the present invention is built. However, after the flight test platform oil circuit system 100 is built, it must undergo a pressurization seal test, a vibration seal test, and a corrosion resistance test. Only after each test is passed can the flight test platform oil circuit system 100 be installed on the flight test platform (e.g., a drone) 10 for use. At this time, the flight test platform oil circuit system 100 is arranged on the main load-bearing structure M of the fuselage, for example, along the fuselage axis CL from the head to the tail of the flight test platform (e.g., a drone) 10, and is located between the wings of the flight test platform (e.g., a drone) 10 (engines 11 and 12 are provided on the wings as fuel-using ends, respectively).

[0071] More specifically, if Figure 1 As shown, the flight test platform oil circuit system 100 is symmetrical about the fuselage axis CL, the main fuel tank 110 is connected in parallel with a plurality of (for example, two) anti-bubble fuel tanks 120, and the main fuel tank 110 is arranged near the center of gravity of the flight test platform (for example, a drone) 10, ensuring that the center of gravity position is not affected by changes in the amount of fuel in the main fuel tank 110. In addition, the plurality of (two) anti-bubble fuel tanks 120 are arranged on one side of the tail of the main fuel tank 110 in a manner facing each other relative to the fuselage axis CL, but it is not limited thereto.

[0072] Finally, various performance tests (pressurization sealing test, vibration sealing test and corrosion resistance test) of the oil circuit system 100 of the flight test platform according to an embodiment of the present invention are described.

[0073] (1) Pressurization and sealing test of the oil system 100 of the flight test platform:

[0074] Build a pressurized sealing test system, plug the refueling port 122 of an anti-bubble oil tank 120 with a special plug to seal it, so that the refueling height in the main oil tank 110 exceeds the tank port, and connect another anti-bubble oil tank 120 with a height difference from the anti-bubble oil tank 120, the pressure difference between the two anti-bubble oil tanks 120 is not less than 5Kpa, and apply oil-indicating paste to the three connecting ports (refueling port 122, anti-bubble oil tank oil delivery port 123 and main oil tank oil delivery port 124) of the oil tank cover 121 of each anti-bubble oil tank 120 and below the position of the oil tank cover 121. The main body of the oil-indicating paste is brown and turns red when it comes into contact with oil. Let it stand for at least 24 hours, and observe whether there is leakage at each connection of each oil circuit (oil supply circuit and refueling circuit).

[0075] (2) Vibration sealing test of the oil system 100 of the flight test platform:

[0076] Fix two interconnected anti-bubble oil tanks 120, 120 on the plate with clamps, add oil to the position higher than the oil barrel cover 121, apply oil-indicating paste to the three connecting ports (the refueling port 122, the anti-bubble oil tank oil delivery port 123 and the main oil tank oil delivery port 124) of the oil tank cover 121 of each anti-bubble oil tank 120 and under the position of the oil tank cover 121, and then put the entire flight test platform oil circuit system 100 on the car, simulate the vibration environment on random road conditions for at least 3 hours, and observe whether there is leakage at each connection of each oil circuit (oil supply circuit and refueling circuit).

[0077] (3) Corrosion resistance test of the flight test platform oil system 100:

[0078] Two anti-bubble oil tanks 120, 120 are connected to each other. Apply oil-indicating paste to the three connecting ports (fuel filling port 122, anti-bubble oil tank oil delivery port 123 and main oil tank oil delivery port 124) of the oil tank cap 121 of each anti-bubble oil tank 120 and below the position of the oil tank cap 121, and then add oil above the oil tank cap 121 and leave it to stand for observation. Leave it to stand for at least 72 hours to observe whether the color of the oil pipe changes significantly, whether the material of the oil pipe changes, and whether there is leakage at each joint of each oil circuit (oil supply circuit and refueling circuit).

[0079] According to the structure as described above, compared with the existing UAV oil circuit system, the flight test platform oil circuit system 100 of the present invention takes into account multiple technical indicators such as anti-bubble, sealing, corrosion resistance, etc. and has been verified by experiments, and has higher reliability, which has a good practical effect on the flight test of the UAV.

[0080] In particular, the flight test platform oil circuit system 100 can adopt a structural form in which a main fuel tank 110 is connected in parallel with multiple anti-bubble fuel tanks 120, and the main fuel tank 110 is arranged near the center of gravity to ensure that the center of gravity position is not affected by the amount of fuel in the main fuel tank 110.

[0081] When the flight test platform oil circuit system 100 is supplying oil, the corrosion-resistant inner joint T2 of the main oil tank 110 and the anti-bubble oil tank 120 is always below the fuel liquid level due to gravity, thereby avoiding the inhalation of bubbles and achieving bubble prevention. When the flight test platform oil circuit system 100 is refueling, it can be controlled by a simple control method, and the oil circuit refueling efficiency is high and the fuel saving effect is good.

[0082] At the same time, the oil pipes and the external joints T1 and internal joints T2 in the flight test platform oil circuit system 100 are all made of corrosion-resistant materials and have good sealing properties. The flight test platform oil circuit system 100 is designed to be pre-tested for various performance tests (pressurization sealing test, vibration sealing test and corrosion resistance test) before being installed on the flight test platform (such as a drone) 10, which can improve reliability.

[0083] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

[0084] For example, in the present invention, the case where the overflow port 111 is located at the upper end of the main fuel tank 110 is illustrated, but the present invention is not limited to this. As long as the overflow port 111 is arranged above the specified position of the main fuel tank 110 (that is, the specified liquid level reached by the fuel in the main fuel tank 110), it can also be arranged at the upper position of the left or right side or the front side of the main fuel tank 110.

[0085] In addition, in the present invention, a situation is shown in which the main fuel tank 110 has a spare fuel filler cap 112. Although it has not been described above, the spare fuel filler cap 112 is used to add fuel directly from the fuel supply end without passing through the anti-bubble fuel tank 120, but those skilled in the art should understand that the spare fuel filler cap 112 is not necessary and the spare fuel filler cap 112 may not be provided.

Claims

1. A flight test platform oil circuit system (100), characterized in that: The flight test platform oil circuit system (100) comprises a main oil tank (110) formed with an overflow port (111) and a plurality of anti-bubble oil tanks (120) connected in parallel with the main oil tank (110), wherein the main oil tank (110) is formed with a plurality of oil delivery ports (113) for respectively connecting to the plurality of anti-bubble oil tanks (120), and each of the anti-bubble oil tanks (120) has three communication ports for communicating with the main oil tank (110), a fuel use end, and a fuel supply end through respective corrosion-resistant pipelines, and the three communication ports are provided with corrosion-resistant external joints (T1). When the flight test platform oil circuit system (100) supplies oil to the fuel use end, the fuel is pumped from the main oil tank (110) to each anti-bubble oil tank (120), and then enters the fuel use end from each anti-bubble oil tank (120). When the flight test platform oil circuit system (100) is refueled from the fuel supply end, the fuel is added to the anti-bubble oil tank (120), and after the anti-bubble oil tank (120) is filled, the fuel enters the main oil tank (110). The main oil tank (110), the anti-bubble oil tank (120) and the oil extraction pipe in the fuel supply end are respectively connected to a corrosion-resistant inner joint (T2), and the corrosion-resistant inner joint (T2) is always below the fuel liquid level. After the main fuel tank (110) is filled, the excess fuel returns to the fuel supply end from the overflow port (111) of the main fuel tank (110) through the oil circuit, and refueling is stopped upon receiving a feedback signal output by the overflow valve. After the flight test platform oil circuit system (100) is built and passes a pressurization seal test, a vibration seal test and a corrosion resistance test, it is arranged on the main load-bearing structure (M) of the fuselage along the fuselage axis (CL) of the flight test platform (10). The flight test platform oil circuit system (100) is symmetrical about the fuselage axis (CL).

2. The flight test platform oil circuit system (100) according to claim 1, characterized in that: When the flight test platform oil circuit system (100) supplies oil to the fuel use end, the overflow port (111) is not sealed. When the flight test platform oil circuit system (100) is refueled from a fuel supply end, the fuel entering the main fuel tank (110) reaches a specified liquid level, and excess fuel flows out from the overflow port (111) of the main fuel tank (110) and returns to the fuel supply end via a fuel return pipe (P4).

3. The flight test platform oil circuit system (100) according to claim 1, characterized in that: The anti-bubble oil tank (120) is provided with an oil tank cover (121). Three communication ports are installed on the oil tank cover (121).

4. The flight test platform oil circuit system (100) according to claim 1, characterized in that: The three connecting ports are a refueling port (122) connected to a fuel output pipe (P3) on the fuel supply end, an anti-bubble tank oil delivery port (123) connected to an anti-bubble tank oil delivery pipe (P2a, P2b) on the fuel use end, and a main tank oil delivery port (124) connected to a main tank oil delivery pipe (P1) on the main tank (110). When the flight test platform oil circuit system (100) supplies oil to the fuel use end, the oil filling port (122) is in a sealed state.

5. The flight test platform oil circuit system (100) according to claim 1, characterized in that: The fuel consumption end is an engine (11, 12), The engines (11, 12) are arranged on wings of the flight test platform (10) symmetrically about the fuselage axis (CL).

6. The flight test platform oil circuit system (100) according to claim 5, characterized in that: The main fuel tank (110) is arranged near the center of gravity of the flight test platform (10).

7. The flight test platform oil circuit system (100) according to claim 5, characterized in that: A plurality of anti-bubble oil tanks (120) are arranged on one side of the tail of the main oil tank (110) in a manner facing each other relative to the fuselage axis (CL).

8. The flight test platform oil circuit system (100) according to any one of claims 1 to 7, characterized in that: The fuel supply end is a fuel container (200), The fuel in the fuel container (200) is refueled into the flight test platform oil circuit system (100) through the oil station (300), and refueling from the fuel container (200) is stopped upon receiving a feedback signal output by an overflow valve (340) disposed in the oil station (300).

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