System for improving supply reliability of fuel system of light sports aircraft

Abstract

The utility model relates to a system for improving the supply reliability of a fuel system of a light sports aircraft, which comprises an aircraft body, a left wing and a right wing are respectively arranged on the left side and the right side of the aircraft body, an engine is arranged at the rear part of the aircraft body, a left fuel tank is fixedly connected in the left wing, a left built-in filter in the left fuel tank is connected with a left fuel supply pipe, and a right fuel tank is fixedly connected in the right wing. A right built-in filter of the right oil tank is connected with a right oil supply pipe, and the tail ends of the right oil supply pipe and the left oil supply pipe are fixedly connected to the fuel reversing valve respectively; an oil inlet pipeline is fixedly connected to the fuel reversing valve, the tail end of the oil inlet pipeline is connected to the engine, and a first fuel conveying pump, a second fuel conveying pump and a fuel bypass valve are arranged on the oil inlet pipeline in parallel. According to the system, the reliability of fuel supply is greatly improved through a double-fuel-pump system, meanwhile, the fuel conveying pump is arranged between the left fuel tank and the right fuel tank, the weight of the left fuel tank and the weight of the right fuel tank can be adjusted, the stability of the gravity center of an aircraft in the flight process is guaranteed, and flight safety and control performance are facilitated.

Description

Technical field:

[0001] The utility model relates to the technical field of auxiliary tooling for installing aircraft canopy glass, and more particularly to a system for improving the supply reliability of a fuel system of a light sports aircraft. Background technology:

[0002] Fuel system reliability is crucial for light sport aircraft (LSA) flight. Existing LSA fuel systems have several shortcomings, including potential interruptions in fuel supply due to a single pump failure during transfer, insufficient fuel supply stability under varying flight attitudes and environmental conditions, and inadequate emergency response capabilities. These issues can impact aircraft safety. Utility model content:

[0003] The purpose of the present utility model is to address the deficiencies of the existing technology and provide a system for improving the fuel supply reliability of a light sport aircraft. The system utilizes a dual fuel pump system to greatly improve fuel supply reliability. A fuel transfer pump is provided between the left and right fuel tanks to balance the weight of the left and right fuel tanks, thereby ensuring a stable center of gravity during flight, which is beneficial to flight safety and controllability.

[0004] A system for improving the fuel supply reliability of a light sport aircraft comprises an aircraft fuselage, with a left wing and a right wing provided on the left and right sides of the fuselage, respectively, and an engine provided at the rear. A left fuel tank is fixedly connected to the left wing, a left internal filter is provided in the left fuel tank, and a left fuel supply pipe is connected to the left internal filter. A right fuel tank is fixedly connected to the right wing, a right internal filter is provided in the right fuel tank, and a right fuel supply pipe is connected to the right internal filter. The ends of the right and left fuel supply pipes are respectively fixedly connected to two fuel inlet ports of a fuel reversing valve. An fuel inlet pipeline is fixedly connected to the fuel outlet port of the fuel reversing valve, and the end of the fuel inlet pipeline is connected to the engine. A first fuel delivery pump, a second fuel delivery pump, and a fuel bypass valve are provided in parallel on the fuel inlet pipeline.

[0005] The engine is connected to an oil return line, the end of which is connected to the left fuel tank; a cooling line is provided on the oil return line, and the cooling line is arranged in the right wing;

[0006] The right oil supply pipe is connected to a balancing oil pipe through a tee, the end of the balancing oil pipe is fixedly connected to the oil return pipe close to the left fuel tank, and the balancing oil pipe is fixedly connected to a third fuel delivery pump.

[0007] Preferably, the fuel reversing valve, the first fuel delivery pump, the second fuel delivery pump, the fuel bypass valve and the third fuel delivery pump are all arranged in the middle of the fuselage, and a firewall is provided between the middle and rear parts of the fuselage.

[0008] Preferably, the return oil line and the balance oil line are both fixedly connected with a one-way valve, the one-way valve on the return oil line allows oil to flow from the engine to the left tank, and the one-way valve on the balance oil line allows oil to flow from the right wing to the left tank.

[0009] Preferably, a high oil level sensor and a low oil level sensor are provided in the left oil tank and the right oil tank, and the left built-in filter and the right built-in filter are respectively located on the lower side of the low oil level sensor;

[0010] The left fuel tank is provided with a left refueling interface on the top and a left oil drain interface on the bottom; the right fuel tank is provided with a right refueling interface on the top and a right oil drain interface on the bottom.

[0011] Preferably, the left and right fuel tanks are both provided with oil level sensing rods.

[0012] Preferably, the first fuel delivery pump, the second fuel delivery pump and the fuel bypass valve constitute a fuel pump group, and fuel filters are fixedly connected to the oil inlet pipelines between the fuel pump group and the fuel reversing valve and between the fuel pump group and the engine.

[0013] Preferably, a fuel cooler is fixedly connected to the oil return pipeline between the left fuel tank and the right wing.

[0014] The beneficial effects of the present invention are:

[0015] 1. The dual fuel pump system greatly improves the reliability of fuel supply and reduces the risk of engine stalling due to fuel pump failure.

[0016] 2. The fuel transfer pump is used to transfer fuel from the right tank to the left tank, which can balance the fuel volume and ensure the stability of the aircraft's center of gravity during flight, which is beneficial to flight safety and control performance. Description of the drawings:

[0017] Figure 1 It is a schematic diagram of the principle of the present utility model.

[0018] In the figure: 1. Fuselage; 2. Left wing; 3. Right wing; 4. Engine; 5. Firewall; 6. Left fuel tank; 7. Right fuel tank; 8. Pressure safety valve; 9. High fuel level sensor; 10. Low fuel level sensor; 11. Left internal filter; 12. Right internal filter; 13. Left fuel supply pipe; 14. Right fuel supply pipe; 15. Fuel reversing valve; 16. Fuel inlet line; 17. First fuel delivery pump; 18. Second fuel delivery pump; 19. Fuel bypass valve; 20. Fuel return line; 21. Equalizing oil pipe; 22. Third fuel delivery pump; 23. Fuel filter; 24. Fuel cooler; 25. Check valve; 26. Fuel level sensing rod. Specific implementation method:

[0019] Example: See Figure 1 As shown, a system for improving the fuel supply reliability of a light sport aircraft includes an aircraft fuselage 1, with a left wing 2 and a right wing 3 provided on the left and right sides of the fuselage 1, respectively, and an engine 4 provided at the rear. A left fuel tank 6 is fixedly connected to the left wing 2, a left internal filter 11 is provided in the left fuel tank 6, and a left fuel supply pipe 13 is connected to the left internal filter 11. A right fuel tank 7 is fixedly connected to the right wing 3, a right internal filter 12 is provided in the right fuel tank 7, and a right fuel supply pipe 14 is connected to the right internal filter 12. The ends of the right fuel supply pipe 14 and the left fuel supply pipe 13 are respectively fixedly connected to two fuel inlet ports of a fuel reversing valve 15; an oil inlet pipeline 16 is fixedly connected to the oil outlet port of the fuel reversing valve 15, the end of the oil inlet pipeline 16 is connected to the engine 4, and a first fuel delivery pump 17, a second fuel delivery pump 18, and a fuel bypass valve 19 are provided in parallel on the oil inlet pipeline 16.

[0020] The engine 4 is connected to a return oil pipeline 20, the end of which is connected to the left fuel tank 6; a cooling pipeline 201 is provided on the return oil pipeline 20, and the cooling pipeline 201 is arranged in the right wing 3. The fuel returning from the engine 4 first passes through the right fuel tank 7, and heat exchange is performed with the fuel in the right fuel tank 7 to cool the returning fuel, and finally flows into the left fuel tank 6.

[0021] The right fuel supply pipe 14 is connected to a balancing oil pipe 21 through a tee. The end of the balancing oil pipe 21 is fixedly connected to the return oil pipe 20 near the left fuel tank 6. A third fuel delivery pump 22 is fixedly connected to the balancing oil pipe 21. The third fuel delivery pump 22 can be used to deliver fuel from the right fuel tank 7 to the left fuel tank 6, thereby achieving oil balance in the two tanks.

[0022] The fuel reversing valve 15, the first fuel delivery pump 17, the second fuel delivery pump 18, the fuel bypass valve 19 and the third fuel delivery pump 22 are all arranged in the middle of the fuselage 1. A firewall 5 is provided between the middle and rear parts of the fuselage 1 to isolate the engine 4.

[0023] Both the return oil line 20 and the balancing oil line 21 are fixedly connected with a one-way valve 25. The one-way valve 25 on the return oil line 20 allows fuel to flow from the engine 4 to the left fuel tank 6, while the one-way valve 25 on the balancing oil line 21 allows fuel to flow from the right wing 3 to the left fuel tank 6. The one-way valve 25 prevents the reverse flow of fuel in the return oil line 20 and the balancing oil line 21. If the third fuel delivery pump 22 is a bidirectional delivery pump, the one-way valve 25 on the return oil line 20 can be eliminated, thereby enabling the mutual transfer of fuel between the left fuel tank 6 and the left fuel tank 7, that is, the fuel in the tank with a higher liquid level is transferred to the tank with a lower liquid level.

[0024] The left fuel tank 6 and the right fuel tank 7 are both provided with a high fuel level sensor 9 and a low fuel level sensor 10, and the left built-in filter 11 and the right built-in filter 12 are respectively located on the lower side of the low fuel level sensor 10; the high fuel level sensor 9 can remind you to stop refueling, and the low fuel level sensor 10 can remind you to refuel.

[0025] The left fuel tank 6 is provided with a left refueling interface 61 at the top and a left oil drain interface 62 at the bottom. The right fuel tank 7 is provided with a right refueling interface 71 at the top and a right oil drain interface 72 at the bottom.

[0026] The left fuel tank 6 and the right fuel tank 7 are both provided with an oil level sensing rod 26, which can detect the oil amount in the left fuel tank 6 and the right fuel tank 7, and determine whether the right fuel tank 7 needs to transport fuel to the left fuel tank 6 based on the oil amount; the left fuel tank 6 and the right fuel tank 7 are both fixedly connected with a pressure safety valve 8.

[0027] The first fuel delivery pump 17, the second fuel delivery pump 18 and the fuel bypass valve 19 constitute a fuel pump group. Fuel filters 23 are fixedly connected to the oil inlet pipes 16 between the fuel pump group and the fuel reversing valve 15 and between the fuel pump group and the engine 4, which can prevent impurities in the fuel from entering the engine 4 and avoid damage to the engine 4.

[0028] A fuel cooler 24 is fixedly connected to the oil return line 20 between the left fuel tank 6 and the right wing 3 , and the fuel cooler 24 can further cool the returning fuel.

[0029] Temperature sensors and heating components are installed in the left and right fuel tanks 6 and 7. Temperature sensors are installed in the fuel system to monitor the fuel temperature in the left and right fuel tanks 6 and 7, respectively. When the fuel temperature is too low, the heating components are activated to prevent the fuel from becoming viscous or even solidifying due to the low temperature, which would affect the extraction and supply of the fuel by the fuel pump unit.

[0030] The heating element is electrically heated and powered by the aircraft's electrical system. Its power and operating time are determined by the fuel temperature and ambient flight temperature. A specialized control algorithm regulates this, ensuring the fuel temperature remains within the appropriate operating range.

[0031] Working Principle: This technical solution is a system to improve the fuel supply reliability of light sport aircraft, which includes the following aspects:

[0032] 1. Dual fuel pump system

[0033] The aircraft utilizes a dual fuel pump configuration (i.e., a first fuel delivery pump 17 and a second fuel delivery pump 18). During normal flight, both pumps operate simultaneously, providing sufficient fuel pressure and flow. If one pump fails, the other pump maintains fuel supply, ensuring the engine does not stall due to a fuel supply interruption. One fuel pump is mounted, while the other is electrically driven. The electrically driven fuel pump is monitored and controlled by a control circuit, which monitors the pump's operating status, such as current and speed, in real time. If an anomaly is detected, the control circuit automatically switches to single-pump operation and issues an alarm to the pilot.

[0034] 2. Fuel transfer and balance

[0035] To ensure balanced fuel transfer between the left and right wing fuel tanks, a third fuel transfer pump 22 is provided in the fuel transfer system. When the liquid level difference between the left and right wing fuel tanks reaches a certain threshold, the third fuel transfer pump 22 starts to transfer fuel from the right tank 7 to the left tank 6 (generally, the amount of fuel in the right tank 7 is much higher than that in the left tank 6), ensuring the stability of the aircraft's center of gravity during flight.

[0036] 3. Emergency operation and protection

[0037] An emergency operation mode is set on the fuel reversing valve 15. In the event of an emergency such as a fuel transfer pump failure, the pilot can switch the fuel supply line to emergency mode by operating the fuel valve. In emergency mode, fuel is directly supplied to the engine from the right fuel tank 7;

[0038] A fuel filter 23 is installed in the fuel system to prevent impurities from entering the fuel pump column and the engine 4. The fuel filter 23 has a blockage detection structure. When the filter blockage reaches a certain level, an alarm is issued to the pilot to replace the filter.

[0039] The embodiments are intended to illustrate the present invention and are not intended to limit the present invention. Any person skilled in the art may modify the embodiments without departing from the spirit and scope of the present invention. Therefore, the scope of protection of the present invention shall be as set forth in the claims of the present invention.

Claims

1. A system for improving the fuel supply reliability of a light sport aircraft, comprising a fuselage (1) of the aircraft, wherein a left wing (2) and a right wing (3) are respectively provided on the left and right sides of the fuselage (1), and an engine (4) is provided at the rear; a left fuel tank (6) is fixedly connected in the left wing (2), a left internal filter (11) is provided in the left fuel tank (6), a left fuel supply pipe (13) is connected to the left internal filter (11); a right fuel tank (7) is fixedly connected in the right wing (3), a right internal filter (12) is provided in the right fuel tank (7), a right fuel supply pipe (14) is connected to the right internal filter (12), the ends of the right fuel supply pipe (14) and the left fuel supply pipe (13) are respectively fixedly connected to two fuel inlet interfaces of a fuel reversing valve (15); an fuel inlet pipeline (16) is fixedly connected to the fuel outlet interface of the fuel reversing valve (15), and the end of the fuel inlet pipeline (16) is connected to the engine (4), characterized in that: A first fuel delivery pump (17), a second fuel delivery pump (18) and a fuel bypass valve (19) are arranged in parallel on the oil inlet pipeline (16); The engine (4) is connected to an oil return pipeline (20), the end of which is connected to the left fuel tank (6); a cooling pipeline (201) is provided on the oil return pipeline (20), and the cooling pipeline (201) is arranged in the right wing (3); The right oil supply pipe (14) is connected to a balancing oil pipe (21) via a tee, the end of the balancing oil pipe (21) is fixedly connected to an oil return pipe (20) near the left oil tank (6), and a third fuel delivery pump (22) is fixedly connected to the balancing oil pipe (21).

2. The system for improving fuel supply reliability of a light sport aircraft according to claim 1, characterized in that: The fuel reversing valve (15), the first fuel delivery pump (17), the second fuel delivery pump (18), the fuel bypass valve (19) and the third fuel delivery pump (22) are all arranged in the middle of the fuselage (1), and a firewall (5) is arranged between the middle and rear parts of the fuselage (1).

3. The system for improving fuel supply reliability of a light sport aircraft according to claim 1, characterized in that: The return oil pipeline (20) and the balance oil pipeline (21) are both fixedly connected with a one-way valve (25). The one-way valve (25) on the return oil pipeline (20) allows oil to flow from the engine (4) to the left oil tank (6), while the one-way valve (25) on the balance oil pipeline (21) allows oil to flow from the right wing (3) to the left oil tank (6).

4. The system for improving fuel supply reliability of a light sport aircraft according to claim 1, wherein: A high oil level sensor (9) and a low oil level sensor (10) are provided in the left oil tank (6) and the right oil tank (7), and a left built-in filter (11) and a right built-in filter (12) are respectively located on the lower side of the low oil level sensor (10); The left oil tank (6) is provided with a left refueling interface (61) at the top and a left oil drain interface (62) at the bottom, and the right oil tank (7) is provided with a right refueling interface (71) at the top and a right oil drain interface (72) at the bottom.

5. The system for improving fuel supply reliability of a light sport aircraft according to claim 4, characterized in that: The left oil tank (6) and the right oil tank (7) are both provided with oil level sensing rods (26).

6. The system for improving fuel supply reliability of a light sport aircraft according to claim 1, characterized in that: The first fuel delivery pump (17), the second fuel delivery pump (18) and the fuel bypass valve (19) constitute a fuel pump group, and a fuel filter (23) is fixedly connected to the oil inlet pipeline (16) between the fuel pump group and the fuel reversing valve (15) and between the fuel pump group and the engine (4).

7. The system for improving fuel supply reliability of a light sport aircraft according to claim 1, wherein: A fuel cooler (24) is fixedly connected to the oil return pipeline (20) between the left fuel tank (6) and the right wing (3).

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